CN103470400B - Design method of an air-breathing hypersonic vehicle exhaust nozzle with controllable inlet and outlet shapes - Google Patents
Design method of an air-breathing hypersonic vehicle exhaust nozzle with controllable inlet and outlet shapes Download PDFInfo
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Abstract
Description
技术领域technical field
本发明涉及一种进出口形状可控的吸气式高超声速飞行器排气喷管的设计方法，属于高超声速排气喷管技术领域。The invention relates to a design method of an air-breathing hypersonic aircraft exhaust nozzle with controllable inlet and outlet shapes, and belongs to the technical field of hypersonic exhaust nozzles.
背景技术Background technique
以超燃冲压发动机为动力的高超声速飞行器以其高速飞行的特性，在军事和民用方面都具有诱人的应用前景，是目前航空航天领域的研究热点。其吸气式高超声速推进系统主要由进气道(含隔离段)、燃烧室和排气系统等关键部件组成。其中，排气系统是高超声速吸气式推进系统中的重要组成部分，其性能好坏直接影响甚至决定了整个推进系统的性能。特别是在高超声速飞行器的推进系统当中，尽管流管进出口的冲量很大，但是其差值即发动机的净推力很小，一般认为净推力大小只有进出口冲量的十分之一量级。另外还要求其与飞行器的流道相匹配且与机身高度一体化。因此，高超飞行器排气喷管的设计与常规的设备喷管设计不同，它要求在满足飞行器几何约束的同时，还要提供优异的气动性能，这是一个带约束的最优化问题。Due to its high-speed flight characteristics, hypersonic vehicles powered by scramjet engines have attractive application prospects in both military and civilian applications, and are currently a research hotspot in the aerospace field. Its air-breathing hypersonic propulsion system is mainly composed of key components such as air intake (including isolation section), combustion chamber and exhaust system. Among them, the exhaust system is an important part of the hypersonic air-breathing propulsion system, and its performance directly affects or even determines the performance of the entire propulsion system. Especially in the propulsion system of a hypersonic vehicle, although the impulse at the inlet and outlet of the flow tube is large, the difference, that is, the net thrust of the engine is very small. It is generally believed that the net thrust is only one-tenth of the impulse at the inlet and outlet. In addition, it is also required to match the flow channel of the aircraft and be highly integrated with the fuselage. Therefore, the design of the exhaust nozzle of hypervehicle aircraft is different from that of conventional equipment nozzles. It is required to provide excellent aerodynamic performance while satisfying the geometric constraints of the aircraft. This is a constrained optimization problem.
最早对这个问题进行研究的是Guderley和Hantsch，他们研究在一定的喷管长度和出口背压的条件下，能产生最大推力的喷管型面设计理论，该方法使用变分法。由于Guderley和Hantsch使用的求解方法太复杂，直到Rao把这种方法简化才获得了广泛的应用。在俄罗斯，Shmyglevsky独立提出了这种最大推力喷管设计方法，被称为Shmyglevsky喷管。Rao提出的这种方法设计的推力喷管能对锥形喷管的性能产生较大的改进，因此在火箭发动机上得到了广泛的应用。Guderley and Hantsch were the first to study this problem. They studied the nozzle profile design theory that can produce the maximum thrust under the condition of certain nozzle length and outlet back pressure. This method uses the variational method. Because the solution method used by Guderley and Hantsch was too complicated, it was not widely used until Rao simplified this method. In Russia, Shmyglevsky independently proposed this maximum thrust nozzle design method, known as the Shmyglevsky nozzle. The thrust nozzle designed by the method proposed by Rao can greatly improve the performance of the conical nozzle, so it has been widely used in rocket engines.
但是Rao方法主要针对二维或轴对称构型的喷管。对于高超声速飞行器来说，为了满足推进系统与机体的一体化的必然要求，使得飞行器后机身充当排气系统的部分膨胀面，因此它对整个飞行器的配平和控制产生很大的影响，处理不好就会对其飞行安全造成重大的威胁。这个问题在常规的航空发动机、冲压发动机和火箭发动机的喷管中并不突出，因此相关的研究也很少，但在高超声速飞行器中，则具有重要的研究价值。为获得发动机最佳的总体性能，要求随飞行状态变化，喷管膨胀比也要相应改变，在定几何前提下，最佳的喷管形式是非对称喷管(SERN)。而随着高超声速技术的发展及矩形燃烧室研究的深入，采用圆形或椭圆形燃烧室的三维流道超燃冲压发动机，因其与采用常规矩形燃烧室的发动机相比具有相当的优越性，近年来逐渐受到关注。所以对于以这类推进系统为动力的飞行器而言，其喷管不再是二元或轴对称构型，而是更加复杂的三维空间曲面。因此复杂进口和出口的非对称三维空间喷管设计面临新的挑战，需要解决圆形或椭圆形进口扩张到复杂出口的变截面设计问题。而且，作为高超声速推进系统用喷管，除了满足几何约束外还需提供优异的气动性能。However, the Rao method is mainly aimed at nozzles with two-dimensional or axisymmetric configurations. For a hypersonic vehicle, in order to meet the inevitable requirements of the integration of the propulsion system and the airframe, the rear fuselage of the aircraft acts as a part of the expansion surface of the exhaust system, so it has a great impact on the trim and control of the entire aircraft. If it is not good, it will cause a major threat to its flight safety. This problem is not prominent in the nozzles of conventional aero-engines, ramjet engines and rocket engines, so there are few related studies, but it has important research value in hypersonic vehicles. In order to obtain the best overall performance of the engine, it is required that the expansion ratio of the nozzle should be changed accordingly with the change of the flight state. Under the premise of fixed geometry, the best nozzle form is the asymmetrical nozzle (SERN). With the development of hypersonic technology and the in-depth research on rectangular combustion chambers, the three-dimensional channel scramjet with circular or oval combustion chambers has considerable advantages compared with engines with conventional rectangular combustion chambers. , has gradually attracted attention in recent years. Therefore, for an aircraft powered by this type of propulsion system, its nozzle is no longer a binary or axisymmetric configuration, but a more complex three-dimensional space surface. Therefore, the design of asymmetric three-dimensional space nozzles with complex inlets and outlets faces new challenges, and it is necessary to solve the problem of variable cross-section design that expands from circular or elliptical inlets to complex outlets. Moreover, as a nozzle for a hypersonic propulsion system, in addition to meeting geometric constraints, it also needs to provide excellent aerodynamic performance.
现有的设计方法大都是针对有一定对称性的三维喷管构型，并且大都基于直接几何过渡方法。国内刘宇等人对塞式喷管中常用的圆转方喷管设计方法进行了比较和总结，并提出了一种新的三维型面直接生成方法。而专门针对超燃冲压发动机进出口形状约束下的圆转方尾喷管设计方法，只有卢鑫基于密切思想做过一些尝试，但是这种方法对于强约束条件下的喷管设计存在一定困难，而且当喷管中的三维特性太强时，密切流片之间的参数存在较大梯度，密切的理论基础是不牢固的。因此，在强几何约束条件下探索新的高超飞行器圆转方喷管设计方法是非常有必要的。Most of the existing design methods are aimed at the three-dimensional nozzle configuration with certain symmetry, and most of them are based on the direct geometric transition method. Domestic Liu Yu et al. compared and summarized the design methods of circular to square nozzles commonly used in plug nozzles, and proposed a new method for direct generation of three-dimensional profiles. Only Lu Xin has made some attempts to design the round-to-square tail nozzle under the shape constraints of the scramjet inlet and outlet, but this method has certain difficulties in nozzle design under strong constraints. Moreover, when the three-dimensional characteristics in the nozzle are too strong, there is a large gradient in the parameters between the close flow sheets, and the close theoretical basis is not firm. Therefore, it is very necessary to explore new design methods for circular-to-square nozzles of hypervehicles under strong geometric constraints.
发明内容Contents of the invention
本发明针对现有技术的不足，提供一种进出口形状可控的吸气式高超声速飞行器排气喷管的设计方法，以设计出一种固定几何，能够产生最大推力，进、出口形状可控制的吸气式高超声速飞行器排气喷管。Aiming at the deficiencies in the prior art, the present invention provides a design method of an air-breathing hypersonic aircraft exhaust nozzle with controllable inlet and outlet shapes, so as to design a fixed geometry that can generate the maximum thrust, and the shape of the inlet and outlet can be controlled. Controlled air-breathing hypersonic vehicle exhaust nozzle.
为实现以上的技术目的，本发明将采取以下的技术方案：For realizing above technical purpose, the present invention will take following technical scheme:
一种进出口形状可控的吸气式高超声速飞行器排气喷管的设计方法，包括以下步骤：(1)选定基准流场——以轴对称最大推力环形流场为基准流场；所述轴对称最大推力环形流场包括流场进口和流场出口，流场进口和流场出口的内环通过回转母线连接，而流场进口和流场出口的外环通过流场膨胀回转壁面连接，流场膨胀回转壁面能够在气流膨胀加速过程中产生最大推力，另外，基准流场的流场进口和流场出口满足以下条件：在流场进口，待设计排气喷管的进口能够分别与回转母线、流场膨胀回转壁面的内壁相切；在流场出口，待设计排气喷管的出口能够分别与回转母线、流场膨胀回转壁面的内壁相切；(2)分别获取第一过渡喷管、第二过渡喷管——第一过渡喷管的获取步骤：首先，在流场进口的流场膨胀回转壁面与回转母线之间设置第一过渡喷管的进口，该第一过渡喷管的进口尺寸与待设计排气喷管的进口尺寸一致，接着，以该第一过渡喷管的进口为流线起点，通过流线追踪至基准流场的流场出口，获得第一过渡喷管的出口以及连接在第一过渡喷管的进口、出口之间的三维膨胀型面，所述第一过渡喷管的出口能够分别与回转母线、流场膨胀回转壁面的内壁相切；第二过渡喷管的获取步骤：首先，在流场出口的流场膨胀回转壁面与回转母线之间设置第二过渡喷管的出口，该第二过渡喷管的出口尺寸与待设计排气喷管的出口尺寸一致，接着，以该第二过渡喷管的出口为流线起点，通过流线追踪至基准流场的流场进口，获得第二过渡喷管的进口以及连接在第二过渡喷管的进口、出口之间的三维膨胀型面，所述第二过渡喷管的进口能够分别与回转母线、流场膨胀回转壁面的内壁相切；(3)通过混合函数S(y)对第一过渡喷管、第二过渡喷管相应位置处的流线坐标进行加权处理，即可获得待设计排气喷管；其中：S(y)＝S1(y)(1-f(x))+S2(y)f(x)；式中：xs、xe分别为XOY坐标系中，流场进口和流场出口的x坐标，x的取值在xs、xe之间；S1(y)为x坐标对应位置处的第一过渡喷管的流线y坐标，S2(y)为x坐标对应位置处的第二过渡喷管的流线y坐标，S(y)为x坐标对应位置处，经过混合函数加权后的流线y坐标；所述的XOY坐标系，其X轴沿基准流场的轴对称回转中心线设置，而Y轴则为与X轴相垂直的线，原点O为X轴、Y轴相交点。A design method of an air-breathing hypersonic vehicle exhaust nozzle with controllable inlet and outlet shapes, including the following steps: (1) Selecting a reference flow field——taking the axisymmetric maximum thrust annular flow field as the reference flow field; The axisymmetric maximum thrust annular flow field includes the flow field inlet and the flow field outlet, the inner ring of the flow field inlet and the flow field outlet is connected by a rotary busbar, and the outer ring of the flow field inlet and the flow field outlet is connected by the flow field expansion rotary wall , the flow field expands and the rotating wall can generate the maximum thrust during the process of airflow expansion and acceleration. In addition, the flow field inlet and flow field outlet of the reference flow field meet the following conditions: at the flow field inlet, the inlet of the exhaust nozzle to be designed can be connected to The rotary busbar and the inner wall of the expansion rotary wall of the flow field are tangent; at the outlet of the flow field, the outlet of the exhaust nozzle to be designed can be tangent to the rotary busbar and the inner wall of the expansion rotary wall of the flow field respectively; (2) respectively obtain the first transition Nozzle, the second transition nozzle—the first transition nozzle acquisition steps: first, the inlet of the first transition nozzle is set between the flow field expansion rotary wall surface at the inlet of the flow field and the rotary bus bar, the first transition nozzle The inlet size of the pipe is consistent with the inlet size of the exhaust nozzle to be designed. Then, taking the inlet of the first transition nozzle as the starting point of the streamline, the flow field outlet of the reference flow field is traced by the streamline to obtain the first transition nozzle. The outlet of the pipe and the three-dimensional expansion surface connected between the inlet and the outlet of the first transition nozzle, the outlet of the first transition nozzle can be respectively tangent to the inner wall of the rotary generatrix and the expansion rotary wall of the flow field; the second Steps for obtaining the transition nozzle: firstly, set the outlet of the second transition nozzle between the flow field expansion revolving wall surface and the revolving generatrix at the outlet of the flow field, the outlet size of the second transition nozzle is the same as that of the exhaust nozzle to be designed The size of the outlet is the same, and then, taking the outlet of the second transition nozzle as the starting point of the streamline, the flow field inlet of the reference flow field is traced by the streamline, and the inlet of the second transition nozzle and the outlet connected to the second transition nozzle are obtained. The three-dimensional expansion surface between the inlet and the outlet, the inlet of the second transition nozzle can be respectively tangent to the inner wall of the rotary generatrix and the expansion rotary wall of the flow field; (3) through the mixing function S(y) to the first transition The streamline coordinates at the corresponding positions of the nozzle and the second transition nozzle are weighted to obtain the exhaust nozzle to be designed; where: S(y)=S 1 (y)(1-f(x))+ S 2 (y)f(x); where: x s and x e are the x-coordinates of the flow field inlet and flow field outlet in the XOY coordinate system respectively, and the value of x is between x s and x e ; S 1 (y) is the first The y-coordinate of the streamline of the transition nozzle, S 2 (y) is the y-coordinate of the streamline of the second transition nozzle at the position corresponding to the x-coordinate, and S(y) is the streamline weighted by the mixing function at the position corresponding to the x-coordinate Line y coordinates; in the XOY coordinate system, the X axis is set along the axisymmetric rotation center line of the reference flow field, while the Y axis is a line perpendicular to the X axis, and the origin O is the intersection point of the X axis and the Y axis.
进一步地，所述待设计排气喷管的进口呈圆形、椭圆形或者矩形设置，待设计排气喷管的出口呈圆形、椭圆形或者矩形设置。Further, the inlet of the exhaust nozzle to be designed is arranged in a circular, elliptical or rectangular shape, and the outlet of the exhaust nozzle to be designed is arranged in a circular, elliptical or rectangular shape.
作为上述方案的进一步改进，本发明所述回转母线为可变中心体母线。As a further improvement of the above solution, the revolving generatrix of the present invention is a variable central body generatrix.
根据以上的技术方案，相对于现有技术，本发明具有以下的优点：According to above technical scheme, with respect to prior art, the present invention has following advantage:
本发明以轴对称最大推力环形流场为基准流场，分别以待设计排气喷管的进口尺寸、出口尺寸在基准流场的进口、出口对应设置第一过渡喷管的进口、第二过渡喷管的出口，再以第一过渡喷管的进口为流线起点，通过流线追踪的方式在基准流场的出口获得第一过渡喷管的出口以及连接在第一过渡喷管进口、出口之间的三维膨胀型面；以该第二过渡喷管的出口为流线起点，通过流线追踪至基准流场的流场进口，获得第二过渡喷管的进口以及连接在第二过渡喷管的进口、出口之间的三维膨胀型面，并采用混合函数加权平均第一过渡喷管、第二过渡喷管相应位置处的流线坐标，即可获得待设计排气喷管。由此可知，本发明所述的待设计排气喷管为在设计过程中喷管进、出口尺寸可控的无粘条件下的高超声速排气喷管，同时，该排气喷管能够产生最大推力。In the present invention, the axisymmetric maximum thrust annular flow field is used as the reference flow field, and the inlet and the second transition of the first transition nozzle are respectively set at the inlet and outlet of the reference flow field according to the inlet size and outlet size of the exhaust nozzle to be designed. The outlet of the nozzle, and then take the inlet of the first transition nozzle as the starting point of the streamline, obtain the outlet of the first transition nozzle at the outlet of the reference flow field by means of streamline tracing and connect the inlet and outlet of the first transition nozzle The three-dimensional expansion surface between; take the outlet of the second transition nozzle as the starting point of the streamline, trace the streamline to the flow field inlet of the reference flow field, obtain the inlet of the second transition nozzle and connect to the second transition nozzle The exhaust nozzle to be designed can be obtained by using the three-dimensional expansion surface between the inlet and outlet of the pipe, and using the mixing function to weight the streamline coordinates at the corresponding positions of the first transition nozzle and the second transition nozzle. It can be seen that the exhaust nozzle to be designed in the present invention is a hypersonic exhaust nozzle under non-viscous conditions with controllable nozzle inlet and outlet dimensions during the design process, and at the same time, the exhaust nozzle can generate maximum thrust.
附图说明Description of drawings
图1是轴对称膨胀基准流场示意图。Figure 1 is a schematic diagram of an axisymmetric expansion reference flow field.
图2是在轴对称膨胀基准流场中，由进口圆形追踪获得的三维膨胀型面示意图。Fig. 2 is a schematic diagram of a three-dimensional expansion profile obtained by circular tracing of an inlet in an axisymmetric expansion reference flow field.
图3是在轴对称膨胀基准流场中，由出口矩形追踪获得的三维膨胀型面示意图。Fig. 3 is a schematic diagram of a three-dimensional expansion profile obtained by tracing an outlet rectangle in an axisymmetric expansion reference flow field.
图4是进口为圆形、出口为方形的吸气式高超声速飞行器排气喷管示意图。Fig. 4 is a schematic diagram of an air-breathing hypersonic vehicle exhaust nozzle with a circular inlet and a square outlet.
图中：1是轴对称环形基准流场外环半径、2是轴对称环形基准流场内环半径、3是轴对称基准流场出口内环半径、4是轴对称基准流场出口外环半径、5是回转母线、6是轴对称基准流场的膨胀回转壁面、7是轴对称回转中心线、8是第一过渡喷管的进口、9是在基准流场中通过第一过渡喷管的进口追踪获得的第一过渡喷管的出口、10是在基准流场中通过第二过渡喷管的出口流线追踪获得的第二过渡喷管的进口、11为第二过渡喷管的出口、12是待设计排气喷管进口、13为待设计排气喷管出口。In the figure: 1 is the radius of the outer ring of the axisymmetric annular reference flow field, 2 is the radius of the inner ring of the axisymmetric annular reference flow field, 3 is the radius of the inner ring of the outlet of the axisymmetric reference flow field, and 4 is the radius of the outer ring of the outlet of the axisymmetric reference flow field , 5 is the revolving generatrix, 6 is the expansion revolving wall surface of the axisymmetric reference flow field, 7 is the axisymmetric revolving center line, 8 is the inlet of the first transition nozzle, and 9 is the passage through the first transition nozzle in the reference flow field The outlet of the first transition nozzle obtained by inlet tracking, 10 is the inlet of the second transition nozzle obtained by tracing the outlet streamline of the second transition nozzle in the reference flow field, 11 is the outlet of the second transition nozzle, 12 is the inlet of the exhaust nozzle to be designed, and 13 is the outlet of the exhaust nozzle to be designed.
具体实施方式Detailed ways
附图非限制性地公开了本发明所涉及优选实施例的结构示意图；以下将结合附图详细地说明本发明的技术方案。The accompanying drawings disclose, without limitation, the structural schematic diagrams of the preferred embodiments involved in the present invention; the technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings.
本发明所述进出口形状可控的吸气式高超声速飞行器排气喷管的设计方法，包括以下步骤：(1)选定基准流场——以轴对称最大推力环形流场为基准流场；如图1所示，本发明所述轴对称最大推力环形流场包括流场进口和流场出口，流场进口和流场出口的内环通过回转母线连接，该回转母线为轴对称变半径中心体结构，而流场进口和流场出口的外环通过流场膨胀回转壁面连接，流场膨胀回转壁面能够在气流膨胀加速过程中产生最大推力，另外，基准流场的流场进口和流场出口满足以下条件：在流场进口，待设计排气喷管的进口能够分别与回转母线、流场膨胀回转壁面的内壁相切；在流场出口，待设计排气喷管的出口能够分别与回转母线、流场膨胀回转壁面的内壁相切，附图2-4设计出的是一种进口圆形、出口方形的排气喷管；(2)分别获取第一过渡喷管、第二过渡喷管——第一过渡喷管的获取步骤：首先，在流场进口的流场膨胀回转壁面与回转母线之间设置第一过渡喷管的进口，该第一过渡喷管的进口尺寸与待设计排气喷管的进口尺寸一致，接着，以该第一过渡喷管的进口为流线起点，通过流线追踪至基准流场的流场出口，获得第一过渡喷管的出口以及连接在第一过渡喷管的进口、出口之间的三维膨胀型面，如图2所示，所述第一过渡喷管的出口能够分别与回转母线、流场膨胀回转壁面的内壁相切；第二过渡喷管的获取步骤：首先，在流场出口的流场膨胀回转壁面与回转母线之间设置第二过渡喷管的出口，该第二过渡喷管的出口尺寸与待设计排气喷管的出口尺寸一致，接着，以该第二过渡喷管的出口为流线起点，通过流线追踪至基准流场的流场进口，获得第二过渡喷管的进口以及连接在第二过渡喷管的进口、出口之间的三维膨胀型面，如图3所示，所述第二过渡喷管的进口能够分别与回转母线、流场膨胀回转壁面的内壁相切；(3)通过混合函数S(y)对第一过渡喷管、第二过渡喷管相应位置处的流线坐标进行加权处理，即对每一个横坐标对应位置处的第一过渡喷管、第二过渡喷管流线纵坐标进行加权处理，即可获得如图4所示的待设计排气喷管；其中：S(y)＝S1(y)(1-f(x))+S2(y)f(x)；式中：xs、xe分别为XOY坐标系中，流场进口和流场出口的x坐标，x的取值在xs、xe之间；S1(y)为x坐标对应位置处的第一过渡喷管的流线y坐标，S2(y)为x坐标对应位置处的第二过渡喷管的流线y坐标，S(y)为x坐标对应位置处，经过混合函数加权后的流线y坐标；所述的XOY坐标系，其X轴沿基准流场的轴对称回转中心线设置，而Y轴则为与X轴相垂直的线，原点O为X轴、Y轴相交点。The design method of the air-breathing hypersonic vehicle exhaust nozzle with controllable inlet and outlet shapes of the present invention comprises the following steps: (1) Selecting a reference flow field——taking the axisymmetric maximum thrust annular flow field as the reference flow field ; As shown in Figure 1, the axisymmetric maximum thrust annular flow field of the present invention includes a flow field inlet and a flow field outlet, and the inner rings of the flow field inlet and the flow field outlet are connected by a rotary busbar, and the rotary busbar is an axisymmetric variable radius The center body structure, while the outer ring of the flow field inlet and flow field outlet is connected by the flow field expansion and rotation wall, the flow field expansion and rotation wall can generate the maximum thrust during the process of air expansion and acceleration. In addition, the flow field inlet and flow field of the reference flow field The outlet of the field satisfies the following conditions: at the inlet of the flow field, the inlet of the exhaust nozzle to be designed can be tangent to the rotary busbar and the inner wall of the expansion rotary wall of the flow field; at the outlet of the flow field, the outlet of the exhaust nozzle to be designed can be respectively It is tangent to the inner wall of the rotary busbar and the expansion rotary wall of the flow field. What is designed in accompanying drawings 2-4 is a kind of exhaust nozzle with a circular inlet and a square outlet; (2) obtain the first transition nozzle, the second transition nozzle respectively Transition nozzle—the acquisition steps of the first transition nozzle: firstly, the inlet of the first transition nozzle is set between the flow field expansion rotary wall surface of the flow field inlet and the rotary generatrix, and the inlet size of the first transition nozzle is the same as The size of the inlet of the exhaust nozzle to be designed is the same, then, take the inlet of the first transition nozzle as the starting point of the streamline, trace the streamline to the flow field outlet of the reference flow field, and obtain the outlet of the first transition nozzle and the connection The three-dimensional expansion profile between the inlet and the outlet of the first transition nozzle, as shown in Figure 2, the outlet of the first transition nozzle can be tangent to the inner wall of the rotary generatrix and the expansion rotary wall of the flow field respectively; Steps for obtaining the second transition nozzle: firstly, set the outlet of the second transition nozzle between the flow field expansion revolving wall surface of the flow field outlet and the revolving generatrix, the outlet size of the second transition nozzle is the same as that of the exhaust nozzle to be designed The size of the outlet of the second transition nozzle is the same, and then, taking the outlet of the second transition nozzle as the starting point of the streamline, the flow field inlet of the reference flow field is traced through the streamline, and the inlet of the second transition nozzle and the connection point of the second transition nozzle are obtained. The three-dimensional expansion profile between the inlet and the outlet, as shown in Figure 3, the inlet of the second transition nozzle can be tangent to the inner wall of the rotary generatrix and the flow field expansion rotary wall respectively; (3) through the mixing function S (y) Weighting the streamline coordinates at the corresponding positions of the first transition nozzle and the second transition nozzle, that is, the longitudinal direction of the streamline coordinates of the first transition nozzle and the second transition nozzle The coordinates are weighted to obtain the exhaust nozzle to be designed as shown in Figure 4; where: S(y)=S 1 (y)(1-f(x))+S 2 (y)f(x ); where: x s and x e are the x-coordinates of the flow field inlet and flow field outlet in the XOY coordinate system respectively, and the value of x is between x s and x e ; S 1 (y) is the first The y-coordinate of the streamline of the transition nozzle, S 2 (y) is the y-coordinate of the streamline of the second transition nozzle at the position corresponding to the x-coordinate, and S(y) is the streamline weighted by the mixing function at the position corresponding to the x-coordinate Line y coordinates; in the XOY coordinate system, the X axis is set along the axisymmetric rotation center line of the reference flow field, while the Y axis is a line perpendicular to the X axis, and the origin O is the intersection point of the X axis and the Y axis.
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