CN115828523B - Evaluation of composite supercharging matching for aircraft engines and optimization method for high-altitude performance recovery - Google Patents
Evaluation of composite supercharging matching for aircraft engines and optimization method for high-altitude performance recovery Download PDFInfo
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Abstract
本发明公开了一种航空发动机复合增压匹配评价及高空性能恢复优化方法，包括如下步骤：建立第一串联布置仿真模型和第二串联布置仿真模型；运行两个仿真模型,改变海拔高度环境，得到不同海拔高度下的多个系统性能评价指标的具体数值；建立多个模糊评价隶属度函数，并将具体数值对应代入模糊评价隶属度函数得到隶属度函数值；建立性能模糊评估矩阵，赋予系统性能评价指标一定权重，获得评价矩阵，计算得到两个仿真模型的评价得分；根据评价得分确定最优的串联布置仿真模型，对最优的串联布置仿真模型的高空性能恢复参数进行优化。本发明弥补了顶置气门二冲程航空活塞发动机关于高空工况的增压匹配评价以及高空性能恢复参数优化研究的空白。
The present invention discloses a method for evaluating the composite supercharging matching of an aero-engine and optimizing the high-altitude performance recovery, comprising the following steps: establishing a first series arrangement simulation model and a second series arrangement simulation model; running the two simulation models, changing the altitude environment, and obtaining specific values of multiple system performance evaluation indicators at different altitudes; establishing multiple fuzzy evaluation membership functions, and correspondingly substituting specific values into the fuzzy evaluation membership functions to obtain membership function values; establishing a performance fuzzy evaluation matrix, assigning certain weights to the system performance evaluation indicators, obtaining an evaluation matrix, and calculating the evaluation scores of the two simulation models; determining the optimal series arrangement simulation model according to the evaluation score, and optimizing the high-altitude performance recovery parameters of the optimal series arrangement simulation model. The present invention fills the gap in the research on supercharging matching evaluation and high-altitude performance recovery parameter optimization of overhead valve two-stroke aero-piston engines for high-altitude working conditions.
Description
Technical Field
The invention relates to the technical field of aero-piston engines, in particular to a composite supercharging matching evaluation and high-altitude performance recovery optimization method for an aero-engine.
Background
The aviation piston engine is a power device widely applied to general aviation aircrafts and unmanned aerial vehicles. Under the background of the large trend of electrodynamic technology, the existing aviation piston engine still has the advantages of strong endurance, higher flight limit rise and the like compared with the pure electric power, particularly has great development potential in a medium power range, and has the advantages of good fuel economy, relatively low manufacturing and using cost, relatively convenient maintenance and the like compared with an aviation turbine engine. The long endurance and high load carrying capacity requirements of aircraft place higher demands on the weight and power-to-weight ratio of aviation piston engines.
Because two-stroke engines do not work at twice the frequency of four strokes, two-stroke aviation piston engines take a significant advantage of the power-to-power ratio over four strokes. The two-stroke of the overhead valve is a new arrangement form of the two-stroke aviation piston engine, the PV2S ventilation system structure is close to that of the four-stroke aviation piston engine, no air port structure is arranged, the air inlet valve and the air outlet valve are arranged on the cylinder cover, and the two-stroke overhead valve is applied to the aviation piston engine, so that the two-stroke aviation piston engine has great attention in various power fields due to the potential of reducing oil consumption and carbon emission and improving the heat efficiency, can keep the traditional advantages of high two-stroke power, good torque uniformity and the like, has the new advantages of low lubricating oil consumption, flexible and controllable air distribution phase and the like, and has wide prospect.
Supercharging is a major approach to recovering intake pressure and power losses of two-stroke aviation piston engines at high altitudes, including the use of a supercharger driven by a crankshaft or motor, a turbocharger driven by exhaust gases, and the like, with most two-stroke aviation piston engines employing turbocharging, and at higher altitudes employing two-stage turbocharging or a turbo-machinery compound supercharging. The high-altitude supercharging not only directly influences the circulating air inflow in the ventilation process, but also determines the air inflow and exhaust pressure and temperature boundary of ventilation so as to influence the ventilation performance, otherwise, the exhaust gas and exhaust temperature control in the ventilation process has larger influence on the efficiency and the available work of the turbine of the turbocharger. Because of the strong coupling relationship between supercharging and ventilation, the performance of supercharging and ventilation is very sensitive to the change of the working condition parameters of the engine and the change of the environment caused by the working height, and good ventilation and supercharging matching are key technologies for ensuring the high-altitude performance of the two-stroke engine.
For the overhead valve two-stroke aviation piston engine, a relatively large positive pressure difference needs to be established between an air inlet passage and an air outlet passage to ensure sufficient air inflow and high air charging efficiency, so that the supercharging of the overhead valve two-stroke aviation piston engine is a precondition for ensuring the normal operation of the overhead valve two-stroke aviation piston engine, and in the current research, a supercharging system matched with the overhead valve two-stroke aviation piston engine comprises three types of single-stage mechanical supercharging, single-stage turbocharging and turbo-mechanical composite supercharging. Single-stage turbocharging for overhead valve two-stroke aviation piston engines has proven to be unstable, especially at low rotational speeds.
The compound supercharging is used for the overhead valve two-stroke aviation piston engine, the arrangement scheme of the compound supercharging is provided for overcoming the defect of matching single-stage machinery or turbocharging, the compound supercharging can be divided into two forms of series connection and parallel connection, the parallel connection form (the air inlet simultaneously enters a compressor for machinery and turbocharging) has smaller requirements on the flow range of the supercharger, but the compressor is easy to surge under low load. In the single turbocharging mode, the mechanical power consumption at high altitude is too large, in the compound turbocharging mode, because of the parallel shunting effect, the MAP flow ranges of the two compressors can be smaller, but if the air piston engine is required to be lifted, the MAP has to be designed into a compressor with larger pressure rise, the MAP shows a narrow and high moment shape, the design difficulty of the compressor impeller is increased, the pressure and the flow of two intake air flows are easy to be different at high altitude, the unstable flow of the air flows flowing through a turbocharger is caused, the surge is easy to occur, the parallel arrangement scheme is not suitable for matching the air piston engine at high altitude, the total pressure ratio of the turbocharging and the mechanical single-stage pressure ratio is low, the combined work of the turbocharging and the mechanical single-stage pressure ratio is favorable for realizing higher total pressure ratio, when the air piston engine is required to be lifted at low rotation speed, the combined work of the turbocharging and the mechanical single-stage pressure ratio is improved, the pressure ratio is more favorable for matching the air piston engine at high rotation speed or the air piston engine is more than the low rotation speed, and the air piston engine is suitable for matching with the high pressure consumption of the air piston engine at high rotation speed and the high speed. The parallel arrangement is only used if the two-stroke overhead valve aeropiston engine arrangement is limited to this form.
The turbine and machinery series connection composite supercharging scheme can combine the advantages of two turbine and machinery supercharging systems to improve the ventilation and power performance of the overhead valve two-stroke aviation piston engine, but the research on the scheme is less at present, and particularly the research on a parameter optimization method related to the supercharging matching evaluation and the high-altitude performance recovery of the overhead valve two-stroke aviation piston engine is blank at present.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems existing in the prior art. Therefore, the invention aims to provide a composite supercharging matching evaluation and high-altitude performance recovery optimization method for an aeroengine, which fills up the study blank of the supercharging matching evaluation and high-altitude performance recovery parameter optimization method for the overhead valve two-stroke aeropiston engine with respect to the high-altitude working condition.
The method for evaluating the composite supercharging matching of the aeroengine and recovering and optimizing the high-altitude performance comprises the following steps:
The method comprises the steps of S1, establishing a first serial arrangement simulation model and a second serial arrangement simulation model, wherein the first serial arrangement simulation model and the second serial arrangement simulation model comprise an aeroengine, a composite supercharging system and an environment module, the composite supercharging system is used for supercharging the aeroengine, the composite supercharging system comprises a mechanical supercharger and a turbocharger which are arranged in series, and the environment module is used for simulating environments with different altitudes;
s2, operating the first serial arrangement simulation model and the second serial arrangement simulation model, and changing the altitude environment to obtain specific numerical values of a plurality of system performance evaluation indexes of the first serial arrangement simulation model and the second serial arrangement simulation model at different altitudes;
S3, establishing a plurality of fuzzy evaluation membership functions corresponding to a plurality of system performance evaluation indexes one by one according to the performance range of the aeroengine, and substituting specific numerical values of the system performance evaluation indexes of the obtained first serial arrangement simulation model and the second serial arrangement simulation model under different altitudes into the plurality of fuzzy evaluation membership functions correspondingly to obtain membership function values of the first serial arrangement simulation model and the second serial arrangement simulation model;
S4, establishing performance fuzzy evaluation matrixes comprising a first series arrangement simulation model and a second series arrangement simulation model under different altitudes, comprehensively analyzing the importance degrees of a plurality of system performance evaluation indexes, endowing the system performance evaluation indexes with certain weights, combining the corresponding weights of the system performance evaluation indexes with the performance fuzzy evaluation matrixes, finally obtaining a plurality of evaluation matrixes under different altitudes, substituting the obtained membership function values into the plurality of evaluation matrixes, and calculating to obtain evaluation scores of the first series arrangement simulation model and the second series arrangement simulation model under different altitudes;
And S5, determining an optimal serial arrangement simulation model according to the evaluation score, and optimizing high-altitude performance recovery parameters of the optimal serial arrangement simulation model.
According to the method for evaluating the composite supercharging matching of the aeroengine and recovering and optimizing the high-altitude performance, on one hand, the first serial arrangement simulation model and the second serial arrangement simulation model are operated under the high-altitude simulation working conditions of different altitudes, the influence of different serial arrangement supercharging schemes on the system performance under the high-altitude working conditions is obtained, the fuzzy evaluation membership function, the performance fuzzy evaluation matrix and the evaluation matrix are sequentially introduced to comprehensively, comprehensively and quantitatively evaluate the system performance of different serial arrangement supercharging schemes under the high-altitude working conditions, and therefore the effect of quantitatively evaluating the difference between the first serial arrangement simulation model and the second serial arrangement simulation model is achieved, and an omnibearing and systematic evaluation system for the composite supercharging scheme of the aeropiston engine is established. On the other hand, the high-altitude performance recovery parameters of the optimal serial arrangement simulation model are optimized, so that the optimal serial arrangement simulation model can reach an optimal high-altitude running state, and the gap of high-altitude parameter optimization of the existing aviation piston engine under the condition of compound pressure increase is filled.
According to some embodiments of the invention, the aeroengine is an overhead valve two-stroke aeropiston engine.
According to some embodiments of the invention, the plurality of system performance evaluation metrics includes an effective fuel consumption rate, a ventilation process charging efficiency, a duty cycle of a supercharger's work-consuming active power, a supercharger compressor efficiency, a turbocharger compressor efficiency.
According to some embodiments of the present invention, the method for evaluating the composite boost matching and the high altitude performance recovery and optimization of the aero-engine further comprises changing the rotation speed of the aero-engine, and then performing steps S2, S3 and S4 in a circulating manner to obtain the evaluation scores of the first serial arrangement simulation model and the second serial arrangement simulation model at different rotation speeds and different altitudes.
According to some embodiments of the invention, the fuzzy evaluation membership functions corresponding to the system performance evaluation indexes one by one are trapezoidal distribution functions.
According to some embodiments of the invention, the optimizing the high altitude performance recovery parameter of the optimal serial arrangement simulation model in the step S5 includes the following steps:
s501, operating an optimal serial arrangement simulation model, and sequentially changing the altitude environment, the supercharging ratio distribution ratio of the mechanical supercharger to the turbocharger and the rotating speed of the aeroengine to obtain the compressor efficiency data of the mechanical supercharger and the compressor efficiency data of the turbocharger under different altitudes, different supercharging ratio distribution ratios and different rotating speeds of the engine;
S502, considering that the mechanical booster compressor and the turbocharger compressor are both operated in a high-efficiency range far from the surge and blocking boundary, analyzing the mechanical booster compressor efficiency and the turbocharger compressor efficiency data obtained in the step S501, and obtaining the most reasonable booster ratio distribution ratio of the low-altitude area and the high-altitude area.
According to some embodiments of the invention, the optimizing the high altitude performance recovery parameter of the optimal serial arrangement simulation model in step S5 further includes the following steps:
S503, running an optimal serial arrangement simulation model, sequentially changing the altitude environment, the supercharging ratio distribution ratio of the mechanical supercharger and the turbocharger and the rotating speed of the aeroengine, and measuring to obtain capturing rate and ventilation efficiency data of the aeroengine ventilation process at different altitudes, different supercharging ratio distribution ratios and different engine rotating speeds;
And S504, on the premise that the mechanical supercharger compressor and the turbocharger compressor are required to work in a high-efficiency range, taking the capture rate and the ventilation efficiency of the air exchange process of the aeroengine into consideration, analyzing the capture rate and the ventilation efficiency data obtained in the step S503 to obtain the most reasonable supercharging ratio distribution ratio of the low-altitude interval and the high-altitude interval.
According to some embodiments of the invention, the optimizing the high altitude performance recovery parameter of the optimal serial arrangement simulation model in step S5 further includes the following steps:
S505, operating an optimal serial arrangement simulation model, and sequentially changing the air distribution phase and the altitude environment of the aeroengine to obtain capture rate and ventilation efficiency data of the air exchange process of the aeroengine under different air distribution phases and different altitude environments;
S506, analyzing the capture rate and the ventilation efficiency data of the ventilation process obtained in the step S505 by taking the ventilation efficiency as the most important index, and determining the most suitable distribution phase under different altitudes.
According to some embodiments of the invention, the optimizing the high altitude performance recovery parameter of the optimal serial arrangement simulation model in step S5 further includes the following steps:
and S507, optimizing the length of the exhaust manifold and the volume of an exhaust cavity of the aeroengine, so that the constant pressure turbocharging mode is converted into the pulse turbocharging mode, and the charging efficiency and the capturing rate of the ventilation process of the aeroengine reach higher levels.
According to some embodiments of the invention, the method for evaluating the composite supercharging matching of the aeroengine and optimizing the high-altitude performance recovery further comprises the steps of comparing the optimized optimal serial arrangement simulation model with the optimized serial arrangement simulation model before optimization, and in practice, performing test bed experiments on the aeroengine and the composite supercharging system before and after the high-altitude performance recovery parameter optimization.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
The foregoing and/or additional aspects and advantages of the invention will become apparent and may be better understood from the following description of embodiments taken in conjunction with the accompanying drawings in which:
fig. 1 is a flow chart of an aeroengine composite boost matching evaluation and high altitude performance recovery optimization method according to an embodiment of the invention.
FIG. 2 is a flow chart of optimizing high-altitude performance recovery parameters of an optimal series arrangement simulation model in an embodiment of the present invention.
Fig. 3 is a schematic structural diagram of an aeroengine and a composite supercharging system in a first series arrangement simulation model in an embodiment of the present invention.
Fig. 4 is a schematic structural diagram of an aeroengine and a composite supercharging system in a second series arrangement simulation model in an embodiment of the present invention.
Fig. 5 is a data comparison graph of evaluation scores of a first serial arrangement simulation model (a composite supercharging scheme a) and a second serial arrangement simulation model (a composite supercharging scheme B) in different altitudes under the working condition that the rotation speed of an aero-engine is 2400 r/min.
Fig. 6 is a data comparison graph of evaluation scores of a first serial arrangement simulation model (a composite supercharging scheme a) and a second serial arrangement simulation model (a composite supercharging scheme B) in different altitudes under the working condition that the rotation speed of an aero-engine is 2100 r/min.
Fig. 7 is a data comparison graph of evaluation scores of a first serial arrangement simulation model (a composite supercharging scheme a) and a second serial arrangement simulation model (a composite supercharging scheme B) in different altitudes under the working condition that the rotation speed of an aero-engine is 1800 r/min.
Reference numerals:
an overhead valve two-stroke aviation piston engine 1, a supercharger 2, a first control unit 201, a bypass valve 202;
a turbocharger 3, an exhaust valve 301, a second control unit 302, and an intercooler 4.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.
The method for evaluating the composite boost matching and optimizing the high-altitude performance recovery of the aero-engine is described below with reference to fig. 1 to 7.
As shown in fig. 1, the method for evaluating composite boost matching and optimizing high-altitude performance recovery of an aeroengine according to the embodiment of the invention comprises the following steps:
The method comprises the steps of S1, establishing a first serial arrangement simulation model and a second serial arrangement simulation model, wherein the first serial arrangement simulation model and the second serial arrangement simulation model comprise an aero-engine, a composite supercharging system and an environment module, the composite supercharging system is used for supercharging the aero-engine, the composite supercharging system comprises a mechanical supercharger 2 and a turbocharger 3 which are arranged in series, and the environment module is used for simulating environments with different altitudes;
s2, operating the first serial arrangement simulation model and the second serial arrangement simulation model, and changing the altitude environment to obtain specific numerical values of a plurality of system performance evaluation indexes of the first serial arrangement simulation model and the second serial arrangement simulation model at different altitudes;
S3, establishing a plurality of fuzzy evaluation membership functions corresponding to a plurality of system performance evaluation indexes one by one according to the performance range of the aeroengine, and substituting specific numerical values of the system performance evaluation indexes of the obtained first serial arrangement simulation model and the second serial arrangement simulation model under different altitudes into the plurality of fuzzy evaluation membership functions correspondingly to obtain membership function values of the first serial arrangement simulation model and the second serial arrangement simulation model;
S4, establishing performance fuzzy evaluation matrixes comprising a first series arrangement simulation model and a second series arrangement simulation model under different altitudes, comprehensively analyzing the importance degrees of a plurality of system performance evaluation indexes, endowing the system performance evaluation indexes with certain weights, combining the corresponding weights of the system performance evaluation indexes with the performance fuzzy evaluation matrixes, finally obtaining a plurality of evaluation matrixes under different altitudes, substituting the obtained membership function values into the plurality of evaluation matrixes, and calculating to obtain evaluation scores of the first series arrangement simulation model and the second series arrangement simulation model under different altitudes;
And S5, determining an optimal serial arrangement simulation model according to the evaluation score, and optimizing high-altitude performance recovery parameters of the optimal serial arrangement simulation model.
Specifically, a first series arrangement simulation model and a second series arrangement simulation model are established. The first serial arrangement simulation model and the second serial arrangement simulation model both accord with the specific structure, the system arrangement form and the related power performance requirement of the aviation piston engine, and the first serial arrangement simulation model and the second serial arrangement simulation model can be established by adopting engine performance analysis commercial software or self-programming. Preferably, the GT-Power software which is widely applied can be selected for establishment, and the established first serial arrangement simulation model and the established second serial arrangement simulation model are both one-dimensional simulation models.
The first serial arrangement simulation model and the second serial arrangement simulation model both comprise an aeroengine, a composite supercharging system and an environment module, wherein the aeroengine is an aeropiston engine, the aeroengine comprises a cylinder system, a crank connecting rod system and an exhaust system, the composite supercharging system comprises a mechanical supercharger 2 and a turbocharger 3 which are arranged in series, and the composite supercharging system is used for supercharging the aeroengine, namely supercharging the air inlet of the aeroengine, so that a relatively large positive pressure difference is established between an air inlet passage and an exhaust passage. The environment module is used for simulating different altitude environments, the environment module is arranged in the composite supercharging system and the exhaust system, and parameters such as pressure, temperature and humidity under different altitude environments can be input into the environment module, so that the requirements of simulation of different altitude working conditions of the aviation piston engine are met. It will be appreciated that the series arrangement of the supercharger 2 and the turbocharger 3 in the composite supercharging system of the first series arrangement simulation model and the second series arrangement simulation model is different.
Fig. 3 is a schematic structural diagram of an aeroengine and a composite supercharging system in a first series arrangement simulation model in an embodiment of the present invention. Fig. 4 is a schematic structural diagram of an aeroengine and a composite supercharging system in a second series arrangement simulation model in an embodiment of the present invention. As shown in fig. 3 and 4, the supercharger 2 is driven by a crankshaft of an aviation piston engine, the transmission ratio can be adjusted through the first control unit 201, the adjustment of the rotating speed and the supercharging ratio of the supercharger 2 can be realized, the intercooler 4 is connected between the supercharger 2 and the turbocharger 3 and used for cooling the supercharged gas temperature to increase the air inflow, the supercharger 2 is arranged in parallel with the bypass valve 202, the supercharger 2 comprises a supercharger compressor, the bypass valve 202 is used for assisting in adjusting the flow and the supercharging ratio of the supercharger 2, and the supercharging ratio of the supercharger 2 is defined as the ratio of the pressure after the two paths of gas of the bypass valve 202 and the supercharger 2 are combined to the ambient pressure. The turbocharger 3 is arranged in parallel with an exhaust valve 301, the turbocharger 3 comprising a turbocharger compressor, the exhaust valve 301 being arranged to control the amount of exhaust gas flowing through the turbocharger 3, the exhaust valve 301 being controlled by a second control unit 302 to control the rotational speed and the boost ratio of the turbocharger 3.
The structural parameters of each part in the first serial arrangement simulation model and the second serial arrangement simulation model are determined or equivalent values thereof by referring to the design drawing of a specific prototype (entity machine), for example, the section of an air inlet and outlet passage of an aviation piston engine is not circular in practice, and the diameters of the air inlet and outlet passages in the first serial arrangement simulation model and the second serial arrangement simulation model take values corresponding to the equivalent sections. In the cylinder system, the number and diameter values of the nozzle orifices of the oil injector module are determined according to an actual oil injector, the circulating oil injection quantity is determined according to the load of the aero-engine, and the oil injection advance angle takes an optimized value obtained through simulation and test. The temperature values of the wall surfaces of the cylinder body, including the cylinder sleeve, the piston top and the cylinder head, are measured according to tests. And adopting Woschni model to calculate heat transfer condition of high-temperature gas and ventilation flow to cylinder wall and piston so as to make the calculated heat transfer quantity have good consistency with actual measurement value. The in-cylinder combustion model adopts a Wiebe combustion model, the detailed description of a spraying process is not needed, and only the circulating oil injection quantity is needed to be provided in the calculation process, so that the accuracy of the first serial arrangement simulation model and the second serial arrangement simulation model in the aspects of power performance, ventilation initiation and composite supercharging boundary condition simulation is ensured. In the modeling of the crank connecting rod system, the weight and size data of the parts such as the crank shaft, the connecting rod and the piston are all derived from the measurement data of the real parts, and the motion rule, the effective compression ratio and the like of the piston are also verified through the test of the real aeroengine.
Since the operation state of the aviation piston engine is unstable when only the turbocharger 3 is in operation, the operation modes of the series scheme are that the turbocharger 2 is started to operate first and the turbocharger 3 is operated later.
And operating the first serial arrangement simulation model and the second serial arrangement simulation model, and changing the altitude environment, namely inputting parameters such as pressure, temperature, humidity and the like under different altitude environments into an environment module to obtain specific values of a plurality of system performance evaluation indexes of the first serial arrangement simulation model and the second serial arrangement simulation model under different altitudes, so that the system performance of the first serial arrangement simulation model and the second serial arrangement simulation model under the high altitude state can be researched. For example, the first serial arrangement simulation model and the second serial arrangement simulation model are operated at the altitude of 2000m, specific numerical values of a plurality of system performance evaluation indexes are recorded or calculated, and the simulation is circularly carried out for a plurality of times within the altitude range of 2000m-8000 m. At this time, the aeroengines in the first serial arrangement simulation model and the second serial arrangement simulation model are operated at the same rotation speed and load, for example, the rotation speed is 2100r/min or 2400r/min or 1800r/min, the load is 100%, and the composite supercharging system is operated at the same supercharging ratio distribution ratio, for example, 5:5.
The multiple system performance evaluation indexes are determined according to the application characteristics of the composite supercharged aviation piston engine and the performance requirements of each height. Specifically, for example, the plurality of system performance evaluation indicators may be an effective fuel consumption rate/(g/kw·h), a duty ratio of the mechanical supercharger to the effective power/%, a ventilation process charging efficiency/-, a turbocharger compressor efficiency/%, and a mechanical supercharger compressor efficiency/%. The method comprises the steps of determining the energy consumption requirement of a mechanical supercharger, determining the energy consumption requirement of the mechanical supercharger, determining the intervention degree of the turbocharging by the mechanical supercharger, determining the energy consumption requirement of the composite supercharging system, determining the air charging efficiency of the air charging process, and evaluating the comprehensive air charging performance of the aeropiston engine at high altitude after the intervention of the composite supercharging system, wherein the effective fuel consumption rate is used for evaluating the fuel economy of the aeropiston engine at high altitude, the duty ratio of the power consumption occupied by the mechanical supercharger can reflect the energy consumption requirement of the mechanical supercharger and the intervention degree of the turbocharging from the side surface, and the air charging efficiency of the air charging process is used for evaluating the performance of two compressors of the composite supercharging system and the high altitude safety boundary respectively.
According to the performance range of the aeroengine, a plurality of fuzzy evaluation membership functions corresponding to a plurality of system performance evaluation indexes one by one are established, specific numerical values of the system performance evaluation indexes of the obtained first serial arrangement simulation model and the second serial arrangement simulation model under different altitudes are substituted into the fuzzy evaluation membership functions correspondingly, and membership function values of the first serial arrangement simulation model and the second serial arrangement simulation model are obtained. For example, the set of system performance evaluation indexes is x= [ x 1,x2,x3,x4,x5 ] = [ effective fuel consumption rate/(g/kW.h), the duty ratio of the mechanical booster to occupy the effective power/%, the charging efficiency/-, the compressor efficiency/%, and the compressor efficiency/% ] of the turbocharger, and the set of system performance evaluation indexes is assumed to have a corresponding normalized evaluation index for any element x in the domain U (research range), then the set of system performance evaluation indexes is called fuzzy set on the domain U, then f (x) is defined as the membership degree of x to f, and when the value of x changes in the domain U, f (x) becomes a function called the fuzzy evaluation membership degree function of f. The fuzzy evaluation membership function f (x) with the value interval of [0,1] has the characteristics that the degree of f is larger as the value is closer to 1, and the performance corresponding to the system performance evaluation index value is better, that is, the fuzzy evaluation membership function can normalize the specific numerical value of each system performance evaluation index.
A performance fuzzy evaluation matrix, e.g. a performance fuzzy evaluation matrix α i, comprising a plurality of fuzzy evaluation membership functions of a first series arrangement simulation model and a second series arrangement simulation model at different altitudes is established, wherein i represents the different altitudes, e.g. 2000m when i=2 and 8000m when i=8. And comprehensively analyzing the importance degrees of the system performance evaluation indexes, and giving a certain weight to the system performance evaluation indexes. For example, the weight coefficient of the effective fuel consumption rate is set to 0.3, the weight coefficient of the duty ratio of the work consumption occupied by the supercharger is set to 0.1, the weight coefficient of the charging efficiency in the ventilation process is set to 0.3, the weight coefficient of the compressor efficiency of the turbocharger is set to 0.15, and the weight coefficient of the compressor efficiency of the supercharger is set to 0.15.
And combining the corresponding weights of the system performance evaluation indexes with the performance fuzzy evaluation matrix to finally obtain a plurality of evaluation matrixes at different altitudes. Such as the evaluation matrix R i＝[0.3,0.1,0.3,0.15,0.15]·αi. And substituting the obtained membership function values into a plurality of evaluation matrixes correspondingly, calculating to obtain evaluation scores of the first serial arrangement simulation model and the second serial arrangement simulation model under different altitudes, and determining the optimal serial arrangement simulation model according to the evaluation scores. Therefore, the invention can achieve the effect of quantitatively evaluating the difference between the first serial arrangement simulation model and the second serial arrangement simulation model, and establishes an omnibearing and systematic evaluation system aiming at the composite supercharging scheme of the aviation piston engine.
And optimizing the high-altitude performance recovery parameters of the optimal serial arrangement simulation model, so that the optimal serial arrangement simulation model can reach an optimal high-altitude running state. According to the invention, the high-altitude performance recovery parameters of the optimal serial simulation model are optimized, so that the blank of high-altitude parameter optimization of the existing aviation piston engine under the condition of composite pressure increase is filled.
According to the method for evaluating the composite supercharging matching of the aeroengine and recovering and optimizing the high-altitude performance, on one hand, the first serial arrangement simulation model and the second serial arrangement simulation model are operated under the high-altitude simulation working conditions of different altitudes, the influence of different serial arrangement supercharging schemes on the system performance under the high-altitude working conditions is obtained, the fuzzy evaluation membership function, the performance fuzzy evaluation matrix and the evaluation matrix are sequentially introduced to comprehensively, comprehensively and quantitatively evaluate the system performance of different serial arrangement supercharging schemes under the high-altitude working conditions, and therefore the effect of quantitatively evaluating the difference between the first serial arrangement simulation model and the second serial arrangement simulation model is achieved, and an omnibearing and systematic evaluation system for the composite supercharging scheme of the aeropiston engine is established. On the other hand, the high-altitude performance recovery parameters of the optimal serial arrangement simulation model are optimized, so that the optimal serial arrangement simulation model can reach an optimal high-altitude running state, and the gap of high-altitude parameter optimization of the existing aviation piston engine under the condition of compound pressure increase is filled.
According to some embodiments of the present invention, prior to quantitatively analyzing the first tandem arrangement simulation model and the second tandem arrangement simulation model, due to differences between different aviation piston engines, such as two-cylinder four-cylinder, V-arrangement in-line arrangement, etc., a preferred arrangement scheme of components in the first tandem arrangement simulation model and the second tandem arrangement simulation model needs to be formulated from corresponding aviation piston engine structures, system arrangements, etc.
According to some embodiments of the invention, the aeroengine is an overhead valve two-stroke aeropiston engine 1. The invention is favorable for more objectively and comprehensively matching the most suitable composite supercharging system scheme for the overhead valve two-stroke aviation piston engine 1, optimizing the high-altitude performance recovery parameter of the most suitable composite supercharging system scheme and laying a foundation for the practical application of the overhead valve two-stroke aviation piston engine 1.
According to some embodiments of the present invention, the plurality of system performance evaluation indexes include an effective fuel consumption rate, an air charging efficiency in a ventilation process, a duty ratio of power occupied by work consumed by a mechanical booster, a compressor efficiency of the mechanical booster, and a compressor efficiency of the turbo booster, and the above five indexes can perform omnibearing evaluation on a composite supercharging system scheme of the overhead valve two-stroke aviation piston engine 1. Thus, the invention establishes an omnibearing and systematic evaluation system for the overhead valve two-stroke aviation piston engine 1.
According to some embodiments of the invention, further comprising varying the rotational speed of the aero-engine, and then looping through steps S2, S3 and S4 to obtain the evaluation scores of the first and second series arrangement simulation models at different rotational speeds and at different altitudes. Therefore, the invention not only can obtain the influence of the first serial arrangement scheme and the second serial arrangement scheme on the system performance under the working conditions of different altitudes, but also can obtain the influence of the first serial arrangement scheme and the second serial arrangement scheme on the system performance under the working conditions of different rotating speeds, thereby being beneficial to evaluating the first serial arrangement scheme and the second serial arrangement scheme more fully.
For example, the first series arrangement simulation model may include a structure as shown in fig. 3 in which the turbocharger 2 is a low-pressure stage and the turbocharger 3 is a high-pressure stage, and the second series arrangement simulation model may include a structure as shown in fig. 4 in which the turbocharger 3 is a low-pressure stage and the turbocharger 2 is a high-pressure stage. Fig. 5-7 illustrate evaluation scores of the first series arrangement simulation model and the second series arrangement simulation model under different altitude conditions and different rotational speed conditions. Wherein the composite boosting scheme a corresponds to a first series arrangement simulation model including the structure shown in fig. 3, and the composite boosting scheme B corresponds to a second series arrangement simulation model including the structure shown in fig. 4.
According to some embodiments of the present invention, the plurality of fuzzy evaluation membership functions corresponding to the plurality of system performance evaluation indexes one to one are trapezoidal distribution functions. Here, the trapezoidal distribution function is adopted to establish the fuzzy evaluation membership function, so that the use effect is good and the calculation is convenient.
Specifically, the smaller the effective fuel consumption rate of the aero-engine after the composite supercharging is, the better the fuel economy is represented, so that the fuzzy evaluation membership function of the effective fuel consumption rate selects a smaller trapezoidal distribution, and for a certain overhead valve two-stroke aero-piston engine 1, the fuzzy evaluation membership function of the effective fuel consumption rate x 1 is established by considering the full altitude fuel consumption range as follows:
The smaller the duty ratio of the mechanical booster power consumption occupation effective power is, the larger the benefit of supercharging is reflected, so that the fuzzy evaluation membership function of the duty ratio of the mechanical booster power consumption occupation effective power is also selected to be in a small trapezoidal distribution, and for a certain overhead valve two-stroke aviation piston engine 1, the fuzzy evaluation membership function of the mechanical booster power consumption occupation effective power x 2 is established by referring to the change of the duty ratio of the mechanical booster power consumption occupation effective power x 2 in a full altitude range as follows:
The higher the charging efficiency is, the better the high altitude ventilation performance of the composite supercharging matched overhead valve two-stroke aviation piston engine 1 is, and as a performance index, the larger and better performance index, the larger trapezoidal distribution should be selected, and for a certain overhead valve two-stroke aviation piston engine 1, the fuzzy evaluation membership function of the charging efficiency x 3 is established by referring to the charging efficiency change range of the full altitude, as follows:
the larger the efficiency of the turbocharger compressor is, the better the performance state of the compressor is reflected, the larger trapezoidal distribution is selected, and for a certain overhead valve two-stroke aviation piston engine 1, the fuzzy evaluation membership function of the efficiency x 4 of the turbocharger compressor is established by referring to the efficiency range of each altitude operation point on a MAP chart as follows:
The larger the efficiency of the compressor of the supercharger is, the better the performance state of the compressor is reflected, the larger trapezoidal distribution is selected, and for a certain overhead valve two-stroke aviation piston engine 1, the fuzzy evaluation membership function of the efficiency x 5 of the compressor of the supercharger is established by referring to the efficiency range of each altitude operation point on a MAP chart as follows:
and correspondingly substituting the specific numerical values of the system performance evaluation indexes of the obtained first serial arrangement simulation model and the second serial arrangement simulation model under different altitudes into the fuzzy evaluation membership functions to obtain membership function values of the first serial arrangement simulation model and the second serial arrangement simulation model.
Correspondingly, the performance fuzzy evaluation matrix comprising a plurality of fuzzy evaluation membership functions of the first serial arrangement simulation model and the second serial arrangement simulation model at different elevations is established. Specifically, for example, the performance blur estimation matrix α i at a certain height is as follows:
Wherein i represents altitude, if i=2, the operation condition of altitude of 2000m is represented, a represents a first series arrangement simulation model, and B represents a second series arrangement simulation model, so that the first column in the matrix represents membership function values of a plurality of fuzzy evaluation membership functions corresponding to a plurality of system performance evaluation indexes of the first series arrangement simulation model one by one under a certain altitude condition, and the second column in the matrix represents membership function values of a plurality of fuzzy evaluation membership functions corresponding to a plurality of system performance evaluation indexes of the second series arrangement simulation model one by one under a certain altitude condition.
According to some embodiments of the present invention, as shown in fig. 2, optimizing the high altitude performance recovery parameter of the optimal serial placement simulation model in step S5 includes the steps of:
S501, running an optimal serial arrangement simulation model, and sequentially changing the altitude environment, the supercharging ratio distribution ratio of the mechanical supercharger 2 and the turbocharger 3 and the rotating speed of the aeroengine, wherein the altitude range can be 2000m-8000m, the supercharging ratio distribution ratio can be 4:6, 4.5:5.5, 5:5, 5.5:4.5 and 6:4, and the rotating speed can be 2100r/min, 2400r/min and 1800r/min, so that the compressor efficiency and the compressor efficiency data of the mechanical supercharger at different altitudes, different supercharging ratio distribution ratios and different engine rotating speeds can be obtained. Specifically, the pressure ratio of the turbocharger 2 is controlled by the gear ratio and the bypass valve 202 in combination, the pressure ratio of the turbocharger 3 is regulated by the exhaust valve 301, and the distribution of the pressure ratios of the turbocharger 3 and the turbocharger 2 can be achieved by the above regulation. The overhead valve two-stroke aviation piston engine 1 has little turbine work available due to low exhaust gas temperature, and the exhaust valve 301 of the turbocharger 3 is usually opened little or not so as to ensure that the exhaust gas energy is sufficiently recovered, and the distribution of the pressure ratio is controlled mainly by adjusting the pressure ratio of the supercharger 2.
S502, considering that the mechanical booster compressor and the turbocharger compressor are both operated in a high-efficiency range far from the surge and blocking boundary, analyzing the mechanical booster compressor efficiency and the turbocharger compressor efficiency data obtained in the step S501, and obtaining the most reasonable booster ratio distribution ratio of the low-altitude area and the high-altitude area. It will be appreciated that steps S501 and S502 are used to optimize the ratio of the supercharger 2 and the turbocharger 3 so that both the supercharger compressor and the turbocharger compressor operate at high efficiency.
The invention selects the most reasonable supercharging ratio distribution proportion between the low altitude area and the high altitude area through screening, so that the mechanical supercharger compressor and the turbocharger compressor work in a high efficiency range far away from surge and blocking boundaries in the whole altitude range, and the operation of the aviation piston engine can meet high safety and airworthiness compliance.
According to some embodiments of the present invention, as shown in fig. 2, optimizing the high altitude performance recovery parameter of the optimal serial placement simulation model in step S5 further includes the following steps:
S503, running an optimal serial arrangement simulation model, and sequentially changing the altitude environment, the supercharging ratio distribution ratio of the mechanical supercharger 2 and the turbocharger 3 and the rotating speed of the aeroengine, wherein for example, the altitude range can be changed within the range of 2000m-8000m, the supercharging ratio distribution ratio can be 4:6, 4.5:5.5, 5:5, 5.5:4.5 and 6:4, and the rotating speed can be 2100r/min, 2400r/min and 1800r/min, so that the capturing rate and the ventilation efficiency data of the aeroengine ventilation process under different altitudes, different supercharging ratio distribution ratios and different engine rotating speeds can be measured;
And S504, on the premise that the mechanical supercharger compressor and the turbocharger compressor are required to work in a high-efficiency range, the capture rate and the ventilation efficiency of the air exchange process of the aeroengine are required to be in a high level, and the capture rate and the ventilation efficiency data obtained in the step S503 are analyzed to obtain the most reasonable supercharging ratio distribution ratio of the low-altitude area and the high-altitude area. It will be appreciated that steps S503 and S504 serve to continue to optimize the boost ratio split ratio so that the aero-piston engine achieves as good a ventilation performance as possible. For the overhead valve two-stroke aviation piston engine 1, the main goal of the supercharging ratio distribution should be the power performance recovery under each altitude working condition, while the overhead valve two-stroke aviation piston engine 1 power recovery mainly comes from the recovery of the ventilation performance, so that the ventilation performance is optimized as one of the goals of the supercharging ratio distribution.
According to some embodiments of the present invention, as shown in fig. 2, optimizing the high altitude performance recovery parameter of the optimal serial placement simulation model in step S5 further includes the following steps:
And S505, operating an optimal serial arrangement simulation model, and sequentially changing the air distribution phase and the altitude environment of the aeroengine to obtain the capture rate and the ventilation efficiency data of the air exchange process of the aeroengine under different air distribution phases and different altitude environments. Specifically, for example, the valve timing may be In126/239、Ex101/208;In136/249、Ex101/208;In146/259、Ex101/208;In126/239、Ex111/218;In136/249、Ex111/218;In146/259、Ex111/218;In126/239、Ex121/228;In136/249、Ex121/228;In146/259、Ex121/228; where "In" represents the intake phase and "Ex" represents the exhaust phase, with the altitude range being 0-8000m.
And S506, taking the ventilation efficiency as the most important index, namely, the higher the ventilation efficiency is, the better the ventilation efficiency is, analyzing the capture rate and the ventilation efficiency data of the ventilation process obtained in the step S505, and determining the most suitable valve timing under different altitudes. The air distribution phase is optimized under different altitudes, so that the air exchange efficiency under different altitudes is optimal, and the recovery of the high-altitude performance of the overhead valve two-stroke aviation piston engine 1 is facilitated. Compared with other two-stroke aviation piston engines, the overhead valve two-stroke aviation piston engine 1 has a great characteristic that the valve timing is freely adjustable, so that the optimization of the valve timing in high-altitude operation is also a key of compound supercharging matching. The valve timing optimization value changes with altitude to a certain extent, and the valve overlap angle has a significant effect on the high altitude ventilation characteristics, so that the most suitable valve timing under different altitudes needs to be determined. The overhead valve two-stroke aviation piston engine 1 can change the valve overlap angle by changing the reference position of the camshaft in the case of valve train mechanical cam profile determination.
According to some embodiments of the present invention, as shown in fig. 2, optimizing the high altitude performance recovery parameter of the optimal serial placement simulation model in step S5 further includes the following steps:
and S507, optimizing the length of an exhaust manifold and the volume of an exhaust cavity of the aero-engine, so that the constant-pressure turbocharging mode is converted into the pulse turbocharging mode, and the charging efficiency and the capturing rate of the ventilation process of the aero-engine reach higher levels.
Both the compound supercharging system and the ventilation process are more sensitive to the structural parameters of the exhaust system due to the intervention of the turbocharger 3. For the application of the turbocharger 3 to the overhead valve two-stroke aviation piston engine 1, if a constant pressure turbocharging scheme is adopted, part of exhaust energy is lost in order to maintain the stability of pressure in front of a turbine, the utilization rate of the exhaust energy is low, and the temperature in front of the turbine is obviously reduced due to the increase of short circuit in a high-altitude working condition, which is more unfavorable for the smaller turbine work corresponding to the ventilation of the overhead valve two-stroke aviation piston engine 1, but if pulse turbocharging is adopted, namely the volume of an exhaust system is reduced, the exhaust rapidly enters the turbine to expand and do work to reduce throttling loss, the pulse energy in a free exhaust stage can be fully utilized for the ventilation process of the overhead valve two-stroke aviation piston engine 1, the comprehensive recovery rate of the exhaust energy is higher, so that part of compressor work is improved, on the other hand, the pulse supercharging scheme is adopted, the pressure fluctuation in an exhaust manifold is large, the control of the reflected compression wave of the pulse turbine system can be realized through the structural parameter adjustment of the exhaust system, the short circuit mainly occurs at the end stage of the scavenging phase, the reflected wave can be controlled to reach the exhaust port at the end stage, the instant, the exhaust system can be effectively restrained at the moment, the fresh air inlet is greatly, and the fresh air can be trapped in the condition of the air system is more than the condition of the air, and the air-filled condition is more high compared with the composite condition, and the air-filled condition is captured by the composite condition, and the air charging system.
The main structural parameters of the exhaust system, which affect the performance of the pulse turbine system and the moment when the reflected compression wave reaches the exhaust valve, are the length of the exhaust manifold before the contracted section of the exhaust pipe and the volume of the exhaust cavity before the turbine, and inappropriate structural parameter values may lead to the advance of the moment when the compression wave reaches, if the moment (about bottom dead center) when the exhaust valve is opened greatly and efficient scavenging is in progress, exhaust gas is prevented from being discharged and fresh charge enters the cylinder, so that the residual amount of exhaust gas in the cylinder is obviously increased.
Therefore, when the composite supercharging is matched, structural parameters of the exhaust system of the overhead valve two-stroke aviation piston engine 1 are optimized, reflected compression waves can be controlled, and ventilation performance (inflation efficiency and capture rate) is improved, so that the recovery of the high-altitude performance of the overhead valve two-stroke aviation piston engine 1 is facilitated. In addition, the exhaust system structural parameters are adjusted to a pulse supercharging state and take appropriate values, so that the common improvement of the ventilation performance and the composite supercharging system performance of the overhead valve two-stroke aviation piston engine 1 can be realized.
In the step of optimizing the high-altitude performance recovery parameters of the optimal serial arrangement simulation model, the invention gradually optimizes the distribution proportion of the supercharging ratio, the distribution phase and the structural parameters of the exhaust system from the factors with larger influence to the factors with smaller influence by sequentially optimizing the distribution proportion of the supercharging ratio, the distribution phase and the structural parameters of the exhaust system, and finally forms the comprehensive optimization method of the overhead valve two-stroke aviation piston engine 1 which is matched with the composite supercharging under the high-altitude working condition, thereby effectively overcoming the defects of single high-altitude performance recovery parameter optimization method, blank high-altitude parameter optimization under the composite supercharging and the like of the existing aviation piston engine only in the parameter performance analysis of the ground fixed state.
According to some embodiments of the invention, the optimized optimal serial arrangement simulation model is compared with the optimized serial arrangement simulation model before optimization, and in practice, test bed experiments are performed on the aero-engine and the composite supercharging system before and after the high-altitude performance recovery parameter optimization. It can be understood that structural parameters and operation parameters of the aero-engine and the composite supercharging system before and after the optimization of the high-altitude performance recovery parameters in practice are consistent with those of the optimal serial arrangement simulation model before and after the optimization, so that data obtained by a test bed experiment in practice can be compared with calculation data of the optimal serial arrangement simulation model before and after the optimization to verify the accuracy of the optimization method.
In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the spirit and scope of the invention as defined by the appended claims and their equivalents.
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