CN117738814B - Variable flow path wide speed range engine with blade tip fan and series compressor - Google Patents
Variable flow path wide speed range engine with blade tip fan and series compressor Download PDFInfo
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- CN117738814B CN117738814B CN202410190213.9A CN202410190213A CN117738814B CN 117738814 B CN117738814 B CN 117738814B CN 202410190213 A CN202410190213 A CN 202410190213A CN 117738814 B CN117738814 B CN 117738814B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention provides a variable flow path wide speed domain engine with a blade tip fan and a series compressor, which comprises the following components: the outlet of the medium-pressure compressor is connected with the inner duct and the inner outer duct; a first flow regulating valve which is arranged at the inlet of the inner duct and the inner outer duct and can switch the open and closed states of the inner duct and the inner outer duct; the high-pressure compressor is arranged in the inner duct; the main combustion chamber, the inner duct and the inner outer duct are connected with an inlet of the main combustion chamber, and the main combustion chamber is arranged at the downstream position of the high-pressure compressor; the outlet of the main combustion chamber is connected with the inner duct and the inner outer duct; a high pressure turbine with blade tips is disposed in the inner duct and the inner outer duct and downstream of the main combustor. The air flow, the supercharging ratio and the circulating working mode of the engine can be flexibly changed by utilizing the conversion of the flow paths, so that the efficient work of the engine in a wide-speed domain is realized, and the requirement of the hypersonic aircraft on the thrust is met.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a variable flow path wide-speed-range engine with a blade tip fan and a series-connected air compressor.
Background
Hypersonic aircrafts are a strategic development direction in the future aerospace field, and the most challenging is the propulsion technology to achieve hypersonic flight. Hypersonic propulsion systems include both rocket-like and air-breathing types. The rocket engine needs to be provided with fuel and oxidant, the propellant accounts for a large percentage of the weight during taking off and launching, the specific impulse is small, and the flying cost is very high; the air suction type engine acquires the oxidant from the atmosphere, and has high specific impulse, good safety, high reliability and good economy. The turbine engine with high Mach number (Mach number is more than 3.5) is becoming a new research hot spot in the field of hypersonic propulsion at home and abroad, and can make up for the gap between the upper limit of the Mach number of the conventional turbine engine with 2-2.5 and the lower limit of the Mach number of the scramjet/scramjet engine with 3.5-6. The biggest technical challenges faced by the development of high mach number turbine engines are the high temperature problems caused by the high mach number operating conditions, the increase of the flying speed causes the temperature of the whole compression system to increase, and in order to ensure the service life and durability of the engine, the materials of the compressor are required to be more highly demanded, so that the high temperature resistant components capable of effectively and permanently working under the high temperature environment need to be developed, but the breakthrough progress can be made in a very short time. Therefore, there is a need to consider how to meet the thrust requirements of hypersonic aircraft under existing material temperature constraints on the overall layout of the engine. In addition, when the flying speed reaches Ma3.0, the temperature of the inlet of the engine can reach above 600K, which has adverse effect on the thermodynamic cycle of the engine, the conversion speed of the engine can be greatly reduced, and the air flow sucked by the engine is reduced, so that the thrust is reduced. Therefore, it is necessary to consider how to improve the flow capacity of the engine in the overall layout of the engine.
Disclosure of Invention
In view of the above, the invention provides a variable flow path wide speed area engine with a blade tip fan and a series compressor, so as to realize the purpose of high-efficiency work of the engine in the wide speed area.
The technical scheme of the invention is as follows: a variable flow path wide speed range engine with a tip fan and a tandem compressor, comprising: the outlet of the medium-pressure compressor is connected with the inner duct and the inner outer duct; a first flow regulating valve which is arranged at the inlet of the inner duct and the inner outer duct and can switch the open and closed states of the inner duct and the inner outer duct; the high-pressure compressor is arranged in the inner duct; the main combustion chamber, the inner duct and the inner outer duct are connected with an inlet of the main combustion chamber, and the main combustion chamber is arranged at the downstream position of the high-pressure compressor; the outlet of the main combustion chamber is connected with the inner duct and the inner outer duct; a high pressure turbine with blade tips is disposed in the inner duct and the inner outer duct and downstream of the main combustor.
Further, a second flow regulating valve is arranged at the connection part of the inner duct and the inlet of the main combustion chamber, and the second flow regulating valve can control the open-close state of the inner duct at the downstream part of the main combustion chamber.
Further, the variable flow path wide speed range engine with the blade tip fan and the series compressor also comprises a variable geometry low pressure turbine which is connected with the outlets of the inner duct and the inner outer duct.
Further, the variable flow path wide speed range engine with the blade tip fan and the serial gas compressor comprises a main duct, an outlet of the main duct is connected with an inlet of the medium-pressure gas compressor, and the main duct is sequentially provided with a first-stage fan and a second-stage fan along the gas flow direction.
Further, the variable flow path wide speed range engine with the blade tip fan and the series compressor further comprises a first outer duct, the first outer duct is coaxially arranged on the outer side of the inner outer duct, and an inlet of the first outer duct is connected with an outlet of the main duct.
Further, the variable flow path wide speed range engine with the blade tip fan and the series air compressor further comprises a punching duct, wherein the punching duct is arranged on the outer sides of the main duct and the first outer duct.
Further, the variable flow path wide-speed-domain engine with the blade tip fan and the serial compressors further comprises a second outer duct, the second outer duct is coaxially arranged on the outer side of the main duct and located on the inner side of the punching duct, an inlet of the second outer duct can be connected with the punching duct, an outlet of the second outer duct is connected with an inlet of the first outer duct, the blade tip fan is arranged in the second outer duct, and the position of the blade tip fan corresponds to the position of the second stage fan.
Further, a third flow regulating valve is arranged at the inlet of the second outer duct, and the third flow regulating valve can switch the open-close states of the second outer duct and the punching duct.
Further, a fourth flow regulating valve is arranged at the inlet of the main duct, and the fourth flow regulating valve can control the opening and closing of the main duct.
Further, the variable flow path wide speed range engine with the blade tip fan and the serial gas compressor further comprises an afterburner and a tail nozzle which are sequentially arranged, wherein the inlet of the afterburner is communicated with the outlet of the punching culvert, the outlet of the inner outer culvert and the outlet of the first outer culvert.
Compared with the prior art, the at least one technical scheme adopted by the invention has the beneficial effects that at least the beneficial effects comprise: according to the embodiment of the invention, the air flow, the supercharging ratio and the circulating working mode of the engine can be flexibly changed by utilizing the conversion of the flow paths, so that the efficient work of the engine in a wide-speed domain is realized, and the requirement of the hypersonic aircraft on the thrust is met.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic overall structure of an embodiment of the present invention;
FIG. 2 is a schematic illustration of a first mode of operation in an embodiment of the invention;
FIG. 3 is a schematic illustration of a second mode of operation in an embodiment of the invention;
fig. 4 is a schematic diagram of a third mode of operation in an embodiment of the invention.
Reference numerals in the drawings: 10. a medium pressure compressor; 11. a first flow rate regulating shutter; 12. a high pressure compressor; 13. a main combustion chamber; 14. a high pressure turbine with a blade tip; 15. a second flow rate regulating shutter; 16. a variable geometry low pressure turbine; 17. a rear variable area bypass ejector; 20. a main duct; 21. a first stage fan; 22. a second stage fan; 23. a fourth flow regulating valve; 30. a first outer duct; 40. a second outer duct; 41. a blade tip fan; 42. a third flow rate adjustment valve; 50. punching the duct; 51. a fifth flow regulating valve; 61. a combustion chamber; 62. a tail nozzle; 91. an inner duct; 92. an inner outer duct.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present application with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. The application may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
As shown in fig. 1, the embodiment of the invention provides a variable flow path wide speed range engine with a blade tip fan and a series compressor, which comprises a medium pressure compressor 10, a first flow regulating valve 11, a main combustion chamber 13 of a high pressure compressor 12 and a high pressure turbine 14 with a blade tip. The outlet of the intermediate pressure compressor 10 is connected with an inner duct 91 and an inner outer duct 92; the first flow regulating valve 11 is provided at the inlet of the inner duct 91 and the inner outer duct 92 and is capable of switching the open and closed states of the inner duct 91 and the inner outer duct 92; the high-pressure compressor 12 is disposed inside the inner duct 91; the inner duct 91 and the inner outer duct 92 are connected with the inlet of the main combustion chamber 13, and the main combustion chamber 13 is arranged at the downstream position of the high-pressure compressor 12; the outlet of the main combustion chamber 13 is connected with an inner duct 91 and an inner outer duct 92; the high pressure turbine 14 with blade tips is disposed in the inner duct 91 and the inner outer duct 92 at a position downstream of the main combustion chamber 13.
According to the embodiment of the invention, the air flow, the supercharging ratio and the circulating working mode of the engine can be flexibly changed by utilizing the conversion of the flow paths, so that the efficient work of the engine in a wide-speed domain is realized, and the requirement of the hypersonic aircraft on the thrust is met.
The second flow regulating valve 15 is provided at the junction of the inner duct 91 and the inner outer duct 92 with the inlet of the main combustion chamber 13, and the second flow regulating valve 15 can control the open and closed state of the inner outer duct 92 at the downstream of the main combustion chamber 13.
The provision of the first flow rate regulating shutter 11 and the second flow rate regulating shutter 15 allows flexible changing of the open and closed states of the corresponding ducts, thereby changing the gas flow direction.
The variable flow path wide speed range engine with a bladed fan and a tandem compressor also includes a variable geometry low pressure turbine 16 connected to the outlets of both the inner bypass 91 and the inner outer bypass 92. The variable geometry low pressure turbine 16 is correspondingly matched with the flow regulating valve, so that the air flow of the engine, the supercharging ratio and the circulating working mode can be flexibly changed.
The variable flow path wide-speed-range engine with the blade tip fan and the series-connected air compressors comprises a main duct 20, an outlet of the main duct 20 is connected with an inlet of the medium-pressure air compressor 10, and the main duct 20 is sequentially provided with a first-stage fan 21 and a second-stage fan 22 along the air flow direction.
The variable flow path wide speed range engine with a bladed fan and a tandem compressor further includes a first outer duct 30, a stamped duct 50, and a second outer duct 40. The first outer duct 30 is coaxially disposed outside the inner outer duct 92, and an inlet of the first outer duct 30 is connected to an outlet of the main duct 20. The punched duct 50 is disposed outside the main duct 20 and the first outer duct 30. The second outer duct 40 is coaxially arranged at the outer side of the main duct 20 and is positioned at the inner side of the punching duct 50, an inlet of the second outer duct 40 can be connected with the punching duct 50, an outlet of the second outer duct 40 is connected with an inlet of the first outer duct 30, a blade tip fan 41 is arranged in the second outer duct 40, and the position of the blade tip fan 41 corresponds to the position of the second stage fan 22.
The invention can ensure that the flow passage of the blade tip fan 41 is not higher than that of the first stage fan 21 through reasonable design, thereby not increasing the windward area of the engine additionally.
Preferably, the tip fan 41 is a short row of rotor blades attached to the periphery of the second stage fan 22, with individually adjustable stator blades in front of the rotor blades, and a row of stationary stator blades behind the rotor blades for turning the direction of airflow in an axial direction.
The middle-pressure compressor 10 and the high-pressure compressor 12 of the variable flow path wide-speed-range engine with the blade tip fan 41 and the serial compressors are positioned in an engine inner duct 91 and are connected in series on a high-pressure rotor, a first flow regulating valve 11 is arranged between the middle-pressure compressor 10 and the high-pressure compressor 12, an inner outer duct 92 is arranged on the periphery of the high-pressure compressor 12, when the first flow regulating valve 11 is opened, air flows at the outlet of the middle-pressure compressor 10 all enter the high-pressure compressor 12, and when the first flow regulating valve 11 is closed, air flows at the outlet of the middle-pressure compressor 10 all enter the inner outer duct 92.
The high-pressure turbine 14 with the blade tip consists of an inlet guide vane and a movable blade, wherein a shoulder is arranged between the inlet guide vane and the movable blade and is used for being matched with the second flow regulating valve 15 to realize the large-scale regulation of the converted flow of the inlet of the high-pressure turbine.
In the embodiment of the present invention, the inlet of the second outer duct 40 is provided with a third flow adjusting valve 42, and the third flow adjusting valve 42 can switch the open/closed states of the second outer duct 40 and the punched duct 50.
Further, a fourth flow regulating valve 23 is disposed at the inlet of the main duct 20, and the fourth flow regulating valve 23 can control the opening and closing of the main duct 20.
The embodiment of the present invention further includes a fifth flow regulating valve 51, which is disposed at the inlet of the punched duct 50, and can control the overall open/close state of the punched duct 50.
The fourth flow regulating valve 23 is used for closing the fan inlet flow passage at the high mach number, the fifth flow regulating valve 51 is used for opening and closing the punched duct 50, and the third flow regulating valve 42 is used for switching the open and closed states of the second outer duct 40 and the punched duct 50; the adjustable stator vanes of the intermediate pressure compressor 10 are used to adjust the air flow into the inner duct 91 and the adjustable stator vanes of the high pressure compressor 12 are used to adjust the air flow into the high pressure compressor 12. The first flow regulating valve 11 is used for opening and closing an inlet flow passage of the high-pressure compressor 12; the second flow regulating shutter 15 is used for flow regulation of the high-pressure turbine inlet. The adjustable stator vanes of the variable geometry low pressure turbine 16 are used to accommodate flow changes into the low pressure turbine in different modes of the engine; the rear variable area bypass ejector 17 controls the total pressure difference of the inner and outer culvert airflows by adjusting the inner and outer culvert flow areas so as to avoid excessive blending loss.
The variable flow path wide speed range engine with the tip fan and the tandem compressor further comprises an afterburner 61 and a tail nozzle 62 which are sequentially arranged, wherein the inlet of the afterburner 61 is communicated with the outlet of the punching duct 50, the outlet of the inner duct 91, the outlet of the inner outer duct 92 and the outlet of the first outer duct 30.
The adjustment of the throat area of the tail pipe 62 is coordinated with each of the adjustable geometry mechanisms for controlling rotor slip.
As shown in fig. 2, when the engine is operated in the low mach number (about 0 to 2.5 ma) range, the fourth flow regulating valve 23 is opened, the fifth flow regulating valve 51 and the third flow regulating valve 42 are closed, the first flow regulating valve 11 is opened to operate the medium pressure compressor 10 and the high pressure compressor 12 in series, and the second flow regulating valve 15 is closed to adapt the high pressure turbine to the smaller high pressure turbine inlet converted flow, at this time, the engine operates similarly to a conventional twin shaft turbofan engine.
As shown in fig. 3, when the engine works in a higher mach number (about 2.5-4.0 ma) interval, the fourth flow regulating valve 23 is still opened, the fifth flow regulating valve 51 and the third flow regulating valve 42 are opened to ensure that the air inlet channel of the blade tip fan is smooth, the first flow regulating valve 11 is closed to enable the air flow at the outlet of the medium-pressure compressor 10 to directly flow into the main combustion chamber through the inner outer duct 92, so that the temperature at the outlet of the compressor is not higher than the allowable temperature limit value of materials, the load of the high-pressure turbine is reduced to be beneficial to the pressure balance of the inner and outer ducts of the whole machine, and the second flow regulating valve 15 is opened to enable the high-pressure turbine to adapt to the larger converted flow at the inlet of the high-pressure turbine, and at the moment, the engine is increased and pushed by sucking air through the fan with the blade tip;
As shown in fig. 4, when the engine is operating in the higher mach number (4.0 Ma or more) interval, the fourth flow rate adjustment valve 23 is closed, the fifth flow rate adjustment valve 51 is opened, and the third flow rate adjustment valve 42 is closed, at which time the engine operates similarly to a ramjet engine.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the application is subject to the protection scope of the claims.
Claims (5)
1. A wide speed domain engine of variable flow path with tip fan and series compressor, characterized by comprising:
An outlet of the medium-pressure compressor (10) is connected with the inner duct (91) and the inner and outer ducts (92);
A first flow rate regulating valve (11) which is provided at the inlet of the inner duct (91) and the inner outer duct (92) and is capable of switching the open/closed states of the inner duct (91) and the inner outer duct (92);
A high-pressure compressor (12) disposed inside the inner duct (91);
The main combustion chamber (13), the inner duct (91) and the inner outer duct (92) are connected with an inlet of the main combustion chamber (13), and the main combustion chamber (13) is arranged at a downstream position of the high-pressure compressor (12); the outlet of the main combustion chamber (13) is connected with the inner duct (91) and the inner outer duct (92);
A high pressure turbine (14) with blade tips, disposed in the inner duct (91) and the inner outer duct (92) and located downstream of the main combustion chamber (13);
The variable flow path wide-speed-range engine with the blade tip fan and the series-connected air compressors comprises a main duct (20), wherein an outlet of the main duct (20) is connected with an inlet of the medium-pressure air compressor (10), and the main duct (20) is sequentially provided with a first-stage fan (21) and a second-stage fan (22) along the air flow direction;
The variable flow path wide-speed-domain engine with the blade tip fan and the series-connected air compressor further comprises a first outer duct (30), wherein the first outer duct (30) is coaxially arranged at the outer side of the inner outer duct (92), and an inlet of the first outer duct (30) is connected with an outlet of the main duct (20);
the variable flow path wide speed domain engine with the blade tip fan and the series-connected air compressor further comprises a punching duct (50), wherein the punching duct (50) is arranged at the outer sides of the main duct (20) and the first outer duct (30);
The variable flow path wide-speed-domain engine with the blade tip fan and the serial gas compressor further comprises a second outer duct (40), wherein the second outer duct (40) is coaxially arranged at the outer side of the main duct (20) and positioned at the inner side of the punching duct (50), an inlet of the second outer duct (40) can be connected with the punching duct (50), an outlet of the second outer duct (40) is connected with an inlet of the first outer duct (30), a blade tip fan (41) is arranged in the second outer duct (40), and the position of the blade tip fan (41) corresponds to the position of the second-stage fan (22);
The inlet of the second outer duct (40) is provided with a third flow regulating valve (42), and the third flow regulating valve (42) can switch the open and closed states of the second outer duct (40) and the punching duct (50).
2. The variable flow wide speed range engine with a tip fan and a tandem compressor according to claim 1, wherein a second flow regulating valve (15) is arranged at the connection of the inner duct (91) and the inner outer duct (92) with the inlet of the main combustion chamber (13), and the second flow regulating valve (15) can control the opening and closing state of the inner outer duct (92) at the downstream of the main combustion chamber (13).
3. The variable flow wide speed range engine with a bladed fan and a tandem compressor of claim 1 further comprising a variable geometry low pressure turbine (16) connected to outlets of both the inner bypass (91) and the inner outer bypass (92).
4. The variable flow wide speed range engine with the tip fan and the tandem compressor as claimed in claim 1, wherein a fourth flow regulating valve (23) is arranged at the inlet of the main duct (20), and the fourth flow regulating valve (23) can control the opening and closing of the main duct (20).
5. The variable flow wide speed range engine with a tip fan and a tandem compressor according to claim 1, further comprising an afterburner (61) and a tail nozzle (62) which are sequentially arranged, wherein the inlet of the afterburner (61) is communicated with the outlet of the punched duct (50), the outlet of the inner duct (91), the outlet of the inner outer duct (92) and the outlet of the first outer duct (30).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410190213.9A CN117738814B (en) | 2024-02-21 | 2024-02-21 | Variable flow path wide speed range engine with blade tip fan and series compressor |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410190213.9A CN117738814B (en) | 2024-02-21 | 2024-02-21 | Variable flow path wide speed range engine with blade tip fan and series compressor |
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| CN117738814A CN117738814A (en) | 2024-03-22 |
| CN117738814B true CN117738814B (en) | 2024-05-17 |
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| CN117738814A (en) | 2024-03-22 |
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