CN111042949B - A wide speed range ejector nozzle integrated with aircraft and design method - Google Patents

A wide speed range ejector nozzle integrated with aircraft and design method Download PDF

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Publication number
CN111042949B
CN111042949B CN201911133988.8A CN201911133988A CN111042949B CN 111042949 B CN111042949 B CN 111042949B CN 201911133988 A CN201911133988 A CN 201911133988A CN 111042949 B CN111042949 B CN 111042949B
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nozzle
ejector nozzle
ejector
main
intake valve
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CN111042949A (en
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黄河峡
张可心
殷世玲
赵磊
谭慧俊
雷鸣
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Nanjing University of Aeronautics and Astronautics
Beijing Power Machinery Institute
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Nanjing University of Aeronautics and Astronautics
Beijing Power Machinery Institute
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

本发明公开了一种与飞行器一体化的宽速域引射喷管及设计方法，并给出了引射喷管的设计流程以及各关键设计参数的最佳取值范围，包括：引射喷管喉道面积、引射喷管喉道位置、引射喷管扩张段尾缘角、第三流路辅助进气门最大旋转角度、主喷管长度等。基于本设计方法设计的引射喷管，其可在宽速域范围内有效匹配涡轮基组合循环发动机，增强引射喷管主流与次流之间剪切层内流体的动量掺混，降低飞行器在低马赫数状态下的底部阻力并满足引射喷管出口面积的调节需求，大大简化引射喷管的调节作动机构，使得飞行器与发动机在宽速域范围内的性能均得到大幅度提升。

Figure 201911133988

The invention discloses a wide-speed range ejector nozzle integrated with an aircraft and a design method, and provides the design process of the ejector nozzle and the optimal value range of each key design parameter, including: ejector nozzle Pipe throat area, injection nozzle throat position, trailing edge angle of the expansion section of the injection nozzle, maximum rotation angle of the auxiliary intake valve of the third flow path, length of the main nozzle, etc. The ejector nozzle designed based on this design method can effectively match the turbine-based combined cycle engine in a wide speed range, enhance the momentum mixing of the fluid in the shear layer between the main flow and the secondary flow of the ejector nozzle, and reduce the speed of the aircraft. The bottom resistance in the low Mach number state meets the adjustment requirements of the ejector nozzle outlet area, greatly simplifies the adjustment and actuation mechanism of the ejector nozzle, and greatly improves the performance of the aircraft and the engine in a wide speed range. .

Figure 201911133988

Description

Wide-speed-range injection spray pipe integrated with aircraft and design method
Technical Field
The invention belongs to the technical field of fluid transmission and control, and relates to a digital switch type inertia hydraulic converter and a working method thereof.
Background
At present, Combined power devices of hypersonic aircrafts mainly comprise two types, namely RBCC (Rocket Based Combined Cycle Engine) and TBCC (Turbine Based Combined Cycle Engine). Compared with RBCC, the TBCC has the characteristics of horizontal take-off and landing, repeated use, good economy, good safety, small technical risk, capability of using conventional carbon-hydrogen fuel and the like, has better engineering application prospect, and is a key technical field for competitive competition of military and strong countries in the world.
As the TBCC exhaust nozzle needs to work in a large falling pressure ratio range from the take-off state to the normal cruising state, the typical exhaust nozzle with the first Mach 0-4 grade has the falling pressure ratio of 60+, the change amplitude of the passing mass flow is large, and the expansion ratio is changed from 2 in the take-off state to 15-20 in the supersonic cruising state, so that the adjustment of the throat and the expansion ratio of the exhaust nozzle needs to be realized through a variable geometry structure. There have been developments including: the adjustable tail-nozzle pipe technical scheme of multiple hinge adjustable structure, urceolus wall translation and various mechanical types such as centre body rotation, though mechanical type regulation can satisfy the regulation of throat area and exit area, but mechanical structure is very complicated, and reliability, life are limited, and need increase a large amount of actuating mechanism, increased aircraft control system's complexity and total weight of structure undoubtedly, for this, urgent need develop the tail-nozzle pipe governing system that the adaptability is stronger, the regulation mode is simpler.
In contrast, the pneumatic jet nozzle adjusting method is simple in structure, easy to implement, free of additional resistance and a feasible technical scheme. The jet nozzle utilizes high-speed jet flow to jet overflow from a boundary layer of an air inlet or gas (secondary flow) from a cooling flow path and an outer bypass from a secondary flow path, and further shear and mix kinetic energy with high-speed gas (primary flow) flowing out of the main jet pipe, so that the kinetic energy of the fluid of the secondary flow is improved, and the fluid of the primary flow and the fluid of the secondary flow jointly flows out of the jet nozzle to improve the thrust. The jet nozzle can also bring other benefits to the design of the aircraft, for example, if the air inlet channel directly overflows to the outside of the aircraft, overflow resistance is generated, but if the scheme of the jet nozzle is adopted, the overflow is jet accelerated after passing through the jet nozzle, certain thrust is generated, and in addition, the regulation requirement of the outlet area can be greatly reduced through the displacement effect of secondary flow on the main flow, so that the outlet actuation system is greatly simplified. However, although the jet nozzle has been used in engineering, the design method of the jet nozzle for the combined engine is not disclosed, and the key technical problem is how to achieve efficient organization of the main and secondary flows or the sufficient mixing between the main and secondary flows and the tertiary flows under a wide range of conditions through pneumatic design and how to avoid the problem of over-expansion of the jet nozzle in a low mach number state.
Disclosure of Invention
In order to solve the problems, the invention discloses a wide-speed-range injection nozzle integrated with an aircraft and a design method thereof, and solves the technical problems of efficiently organizing main and secondary flows or fully mixing the main and secondary flows and tertiary flows under a wide range of conditions through pneumatic design and avoiding over-expansion of a tail nozzle under a low Mach number state.
In order to achieve the aim, the wide-speed-range injection nozzle integrated with the aircraft provided by the invention adopts the following technical scheme:
a wide velocity range ejector nozzle integrated with an aircraft, comprising: the jet nozzle comprises a contraction main nozzle, a secondary flow channel surrounding the contraction main nozzle and a jet nozzle sleeve positioned behind the secondary flow channel; the rear end of the contraction main nozzle is contracted inwards to form a hollow circular truncated cone; the injection nozzle sleeve surrounds the rear part of the shrinkage main nozzle, and the rear section of the injection nozzle sleeve is hinged with a plurality of outlet area adjusting sheets which are annularly arranged; the outlet surrounded by the outlet area adjusting sheet is the final outlet of the injection spray pipe; the outlet area adjusting sheet rotates inwards from a hinge point of the outlet area adjusting sheet and the sleeve of the injection spray pipe to reduce the outlet area; and the rear end of the outer wall of the secondary flow passage is hinged with a third flow passage auxiliary inlet valve, the third flow passage auxiliary inlet valve is positioned between the rear end of the outer wall of the secondary flow passage and the front end of the injection spray pipe sleeve, and when the third flow passage auxiliary inlet valve is closed, the rear end of the third flow passage auxiliary inlet valve is connected with the front end of the injection spray pipe sleeve.
Furthermore, in a low-Mach-number flight state, the third flow path assists the intake valve to be opened, the outlet area adjusting sheet is folded inwards to reduce the outlet area, and at the moment, the jet nozzle generates thrust jointly by the main flow injected in the contracted main nozzle, the secondary flow injected in the secondary flow path and the third flow path fluid from the third flow path auxiliary intake valve; in a supersonic flight state, the third flow path assists the air inlet valve to be closed, the outlet area adjusting sheet is turned outwards to be flat, and the thrust in the injection nozzle is generated by the main flow and the secondary flow.
Further, the third flow path assists the intake valve in turning inward when opened.
Furthermore, a limiter is arranged on the outer side of the outlet area adjusting sheet, so that the outer wall surface of the outlet area adjusting sheet is horizontal to the outer wall surface of the injection nozzle sleeve when the outlet area adjusting sheet is in the maximum expansion state.
The design method of the wide-speed-range injection spray pipe adopts the following technical scheme, and comprises the following steps:
(1) designing parameters of the injection spray pipe are subjected to dimensionless reduction by contracting the diameter D of the inlet of the main spray pipe, so that the designing parameter values are dimensionless quantities, and the origin of coordinates of the injection spray pipe is defined as the position O of the center of a circle of the inlet section of the main spray pipe;
(2) determining the size of the converging primary nozzle of the eductor nozzle, comprising: diameter D of outlet of main nozzlepAnd a main nozzle length L, wherein the outlet diameter DpCalculated based on a flow formula according to the engine flow under the condition that the outlet is caused to reach a critical state; selecting the length L of the main nozzle by setting the dimensionless length of the main nozzle, namely the value range of L/D is 0.20-0.27;
(3) the profile parameters of the induction nozzle sleeve include: diameter D of sleeve throat of injection nozzletAnd an axial distance L from the outlet of the main nozzlet-LpThe throat position of sleeve of jet nozzle is determined, and the distance (L) between throat and outlet of main nozzlet-Lp)/DpThe value range of (a) is-0.06-0.04; on the basis of determining the position of the throat, the dimensionless diameter D of the sleeve throat of the injection nozzletThe value range of the/D is 1.09-1.12, and the diameter D of the throat of the sleeve of the injection nozzle is determinedt，；
(4) Profile parameters of the outlet area adjustment flap include: the tail edge angle beta ranges from 4 degrees to 8 degrees;
(5) the opening degree of the auxiliary intake valve of the third flow path is: the maximum rotation angle alpha is 25-30 degrees if the sub-stream channel is in a backflow state; if the sub-flow channel is downstream, the value range of the maximum rotation angle alpha of the auxiliary inlet valve of the third flow channel is 5-15 degrees;
(6) integrating design parameters of the injection nozzle, performing iterative adjustment in the value range, returning to the step (2) to perform value again in the value range of the dimensionless length L/D of the main nozzle if the thrust performance of the injection nozzle does not reach the standard, wherein the value taking method is to increase a value taking interval from the lower limit each time, the value taking interval of the parameter is 0.01, and entering the step (3) if the thrust performance is improved; distance (L) between the throat and the outlet of the main nozzle given in step (3)t-Lp)/DpThe value is re-taken within the value taking range, the starting point is the lower limit, and the value taking interval is 0.01; on the premise of ensuring the improvement of the thrust performance, the dimensionless diameter D of the sleeve throat of the injection nozzle is sequentially settThe value of the angle/D, the tail edge angle beta and the maximum rotation angle alpha is re-taken within the corresponding value range, the starting point refers to the upper limit and the lower limit mentioned in the steps (3), (4) and (5), and the value intervals are respectively 0.05, 0.5 degrees and 3 degrees; in the design process, if the thrust performance cannot be improved by the value of a certain parameter, the value is continuously taken according to the value taking method until the thrust performance is improved to some extent, the next parameter is optimized, and the optimized parameters are sequentially overlapped to generate the final pneumatic profile of the injection nozzle.
Further, the airflow in the secondary flow channel (2) is in a positive direction, namely, downstream, and the airflow is discharged from the right side of the channel; when the flow is found to be in the reverse direction in an experiment or simulation, the maximum rotation angle of the intake valve (3) is assisted by increasing the third flow path until the flow direction of the gas flow in the sub-flow path (2) is in the forward direction.
Further, when the third flow path auxiliary intake valve (3) is closed, the third flow path auxiliary intake valve is completely attached to the injection nozzle sleeve (4), namely, no gap exists between the third flow path auxiliary intake valve (3) and the injection nozzle sleeve (4), and alpha is always greater than or equal to 0.
Furthermore, the contraction section is designed by adopting a spline curve, the throat part adopts circular arc smooth transition, and the expansion section adopts various straight generatrices or multiple curves; the expansion section bus equation is: a is2*Δx2+a3*Δx3+a4*Δx4Wherein, Δ x and Δ y are respectively the horizontal and vertical coordinate spacing, and Δ y is (2 y-D)t)/(D-Dt),Δx＝(x-Lt)/(Le-Lt)，a2、a3、a4Is the coefficient of an equation, DtIs the diameter of the sleeve throat of the injection nozzle, D is the diameter of the outlet of the injection nozzle, and LtJet nozzle sleeve throat position, LeFor the total length of the injection spray pipe, included angles between tangents of the expansion section bus at the starting point and the end point and the horizontal direction are respectively theta1、θ2Wherein theta1＝0°，θ2Self-setting: given that the desired expansion rate of the gas stream is substantially equivalent before and after, a2＝-0.5tanθ2*(Le-Lt)+2.5，a3＝-1，a4＝0.5tanθ2*(Le-Lt) -0.5; if a large initial expansion rate is desired, a is given2＝0，a3＝4-tanθ2*(Le-Lt)，a4＝tanθ2*(Le-Lt) -3; if a smaller initial expansion rate is desired, a is given2＝6-0.5tanθ2*(Le-Lt)，a3＝-8，a4＝0.5tanθ2*(Le-Lt)+3
Compared with the prior art, the invention has the following beneficial effects:
the ejector nozzle designed based on the design method can effectively match a turbine-based combined cycle engine in a wide speed domain range, enhances momentum mixing of fluid in a shear layer between a main flow and a secondary flow of the ejector nozzle, reduces bottom resistance of an aircraft in a low Mach number state, meets the adjusting requirement of the outlet area of the ejector nozzle, greatly simplifies an adjusting and actuating mechanism of the ejector nozzle, and greatly improves the performance of the aircraft and the engine in the wide speed domain range. The method provides a feasible design method for developing the injection boosting mechanism research and the engine ground test research of the TBCC combined cycle engine.
Drawings
FIG. 1 is a schematic view of the wide velocity range ejector nozzle of the present invention integrated with an aircraft.
Fig. 2 is a pneumatic profile diagram of the wide-speed-range ejector nozzle in a state where Ma is equal to 0.
Fig. 3 is a pneumatic profile diagram of a wide-speed-range ejector nozzle in a state of Ma ═ 4.
Fig. 4 is a flow field structure diagram of the wide-speed-range ejector nozzle obtained through numerical simulation in a state where Ma is 0.
Fig. 5 is a flow field structure diagram of the wide-speed-range ejector nozzle obtained through numerical simulation in a state where Ma is 4.
Detailed Description
Example one
Referring to fig. 1, this embodiment is an embodiment of a wide velocity range ejector nozzle integrated with an aircraft. This wide speed territory draws spouts includes: the jet nozzle comprises a contracted main nozzle 1, a secondary flow channel 2 surrounding the contracted main nozzle 1 and a jet nozzle sleeve 4 positioned behind the secondary flow channel 2. The main spray pipe 1 and the injection spray pipe sleeve 4 are both annular, and the secondary flow channel 2 surrounds the contracted main spray pipe 1 to form an annular channel. The rear end of the contraction main nozzle 1 is contracted inwards to form a hollow circular truncated cone; the injection nozzle sleeve 4 surrounds the rear part of the shrinkage main nozzle, and the rear section of the injection nozzle sleeve is hinged with a plurality of outlet area adjusting blades 7 which are annularly arranged; the outlet surrounded by the outlet area adjusting sheet is the final outlet of the injection spray pipe; the outlet area adjusting sheet rotates inwards from the hinged point of the outlet area adjusting sheet and the sleeve of the injection spray pipe, so that the outlet area is reduced. And the rear end of the outer wall of the secondary flow passage is hinged with a third flow passage auxiliary inlet valve 3, the third flow passage auxiliary inlet valve is positioned between the rear end of the outer wall of the secondary flow passage and the front end of the injection spray pipe sleeve, and when the third flow passage auxiliary inlet valve is closed, the rear end of the third flow passage auxiliary inlet valve is connected with the front end of the injection spray pipe sleeve. And a limiter 5 is arranged on the outer side of the outlet area adjusting sheet 7, so that the outer wall surface 12 of the outlet area adjusting sheet 7 is horizontal to the outer wall surface of the injection nozzle sleeve 4 when the outlet area adjusting sheet is in the maximum expansion state.
In a low-Mach-number flight state, the third flow path auxiliary intake valve 3 is opened, the outlet area adjusting sheet 7 is folded inwards to reduce the outlet area, and at the moment, the jet nozzle generates thrust jointly by the main flow 8 injected in the contracted main nozzle 1, the secondary flow 9 injected in the secondary flow channel 2 and the third flow path 10 fluid from the third flow path auxiliary intake valve 3; in a supersonic flight state, the third flow path assists the closing of the intake valve 3, the outlet area adjusting sheet 7 is turned outwards and leveled, and the thrust in the pilot nozzle is generated by the main flow 8 and the secondary flow 9. The third flow path assists the intake valve 3 to fold inward when opened.
Example two
The second embodiment discloses a pneumatic design method of the wide-speed-range injection nozzle in the first embodiment. Referring to fig. 1, the working condition of this embodiment is the design state (Ma is 4) and the main flow pressure drop ratio is 60, and the detailed implementation steps of this embodiment designed by the method of the present invention will be described below.
(1) Determining the size of the contraction main nozzle 1 by combining the overall demand, wherein the research range of the dimensionless length (L/D) of the contraction main nozzle is 0.20-0.61, and taking 6 sample points in the range to obtain the following research results: with the reduction of the dimensionless length of the contracted main nozzle, the thrust coefficient of the injection nozzle is gradually increased, and the variation range of the corresponding thrust coefficient is 0.949-0.907; the optimal value range of the dimensionless length (L/D) of the contraction main nozzle 1 is 0.20-0.27, and if the injection nozzle is required to have better thrust performance, the lower limit is selected as far as possible; if it is desired that the area adjustment range of the main nozzle is large, the upper limit is taken. The contracted main nozzle 1 of this example takes a dimensionless length of 0.20.
(2) Determining the diameter D of the throat of the sleeve 4 of the ejector nozzle while keeping the L/D constanttAxial distance (L) from the main nozzle outlett-Lp)/DpThe research range is-0.06-0.51, 6 sample points are taken in the range, and the thrust coefficient is obtained through research (L)t-Lp)/DpThe thrust coefficient is increased and gradually reduced, and the variation range of the corresponding thrust coefficient is 0.956-0.950; preferred distance (L) of throat from exit of main nozzlet-Lp)/DpThe value range of (A) is-0.06-0.04, this example (L)t-Lp)/DpTake-0.06.
(3) Maintain L/D, (L)t-Lp)/DpDetermining the dimensionless diameter (D) of the throat of the sleeve 4 of the ejector nozzle without changingt/D) in a range of 0.98 to 1.12,taking 6 sample points in the range, and researching to obtain a thrust coefficient with DtThe thrust coefficient is gradually increased by increasing the/D, and the variation range of the corresponding thrust coefficient is 0.933-0.935; non-dimensional diameter (D) of throat of sleeve 4 of ejector nozzletThe optimal value range of the/D) is 1.09-1.12, and the throat position of the ejector nozzle sleeve 4 of the embodiment is 1.12.
(4) Maintain L/D, (L)t-Lp)/Dp、DtDetermining the tail edge angle beta of the expansion section of the sleeve 4 of the injection nozzle without changing D, wherein the research range is 4-20 degrees, taking 5 sample points in the range, and obtaining that the thrust coefficient is gradually reduced along with the increase of beta through research, wherein the corresponding thrust coefficient change range is 0.957-0.953; the optimal value range of the tail edge angle beta of the expansion section of the injection nozzle 4 is 4-8 degrees, and the tail edge angle of the expansion section of the injection nozzle 4 in the embodiment is 4 degrees.
(5) Keeping the profile parameters unchanged, determining the maximum rotation angle alpha of the auxiliary inlet valve 3 of the third flow path, wherein the research range is 5-30 degrees, taking 6 sample points in the range, and obtaining through research: if the sub-stream channel 2 is in a backflow state, the thrust coefficient is increased along with the increase of alpha, the variation range of the thrust coefficient is 0.608-0.732, the preferred value range of alpha is 25-30 degrees, and the lower limit is taken as far as possible; if the sub-stream channel 2 is in a downstream state, the thrust coefficient is reduced along with the increase of alpha, the variation range of the thrust coefficient is 0.974-0.759, the preferred value range of alpha is 5-15 degrees, and the upper limit is taken as far as possible; the third flow path of the present embodiment assists the intake valve 3 to rotate at a maximum rotation angle α of 5 ° in the forward flow state and 30 ° in the return flow state.
(6) The expansion section bus of the injection nozzle sleeve 4 is determined, the performance improvement is mainly targeted in the embodiment, the expansion section adopts a plurality of curves, and the expansion section bus equation is as follows: a is2*Δx2+a3*Δx3+a4*Δx4Wherein Δ y ═ 2y-Dt)/(D-Dt),Δx＝(x-Lt)/(Le-Lt) The included angles between the tangent lines of the expansion section generatrix at the starting point and the end point and the horizontal direction are respectively theta1、θ2，θ10 °, θ in the present embodiment2Take 10 degrees and Le-LtWhen the expansion rate of the gas flow is expected to be basically equal to the front and back of the expansion rate of the gas flow, the coefficient of the bus equation can be obtained by a simultaneous bus equation and a tangent equation of a bus end point as follows: a is2＝2.4515，a3＝-1，a4＝-0.4515。
(7) Integrating the optimal values of the design parameters in the process to generate a profile of the ejector nozzle, wherein the thrust coefficient of the ejector nozzle in the embodiment under the design state (Ma is 4) is 0.961.
The pneumatic scheme of the ejector nozzle based on the invention is shown in fig. 2 and 3, and the flow structure of the ejector nozzle is obtained by using the numerical simulation result, as shown in fig. 4 and 5. In the numerical simulation, when Ma is 0, the main flow drop pressure ratio is 2.16, and the sub flow drop pressure ratio is 0.987; when Ma is 4, the major flow drop pressure ratio is 60.7, and the minor flow drop pressure ratio is 7.1. It can be seen from fig. 4 and 5 that there is no large-scale backflow region in the flow field, the flow field of the primary and secondary flows is uniform, and the free shear layer is fully developed. The thrust coefficients corresponding to the two states are 0.947 and 0.961 respectively. The above results show that the design method of the present invention achieves the intended goal and is feasible.
In addition, the present invention has many specific implementations and ways, and the above description is only a preferred embodiment of the present invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be construed as the protection scope of the present invention.

Claims (7)

1.一种与飞行器一体化的宽速域引射喷管的设计方法，其特征在于，该与飞行器一体化的宽速域引射喷管包括：收缩主喷管(1)、围绕收缩主喷管(1)的次流通道(2)、位于次流通道(2)后方的引射喷管套筒(4)；收缩主喷管(1)的后端向内收缩为中空的圆台状；引射喷管套筒(4)围绕于收缩主喷管的后方，引射喷管套筒的后段铰接有若干成环状排布的出口面积调节片(7)；该出口面积调节片围成的出口即为引射喷管的最终出口；出口面积调节片自与引射喷管套筒铰接点向内转动而减小出口面积；1. a design method of a wide-speed range ejector nozzle integrated with an aircraft, it is characterized in that, this wide-speed range ejector nozzle integrated with the aircraft comprises: shrinking the main nozzle (1), surrounding the shrinking main nozzle. The secondary flow channel (2) of the nozzle (1), the ejection nozzle sleeve (4) located behind the secondary flow channel (2); the rear end of the shrinking main nozzle (1) shrinks inwardly into a hollow truncated cone shape ; The ejection nozzle sleeve (4) surrounds the rear of the shrinking main nozzle, and the rear section of the ejection nozzle sleeve is hinged with a number of annularly arranged outlet area adjustment pieces (7); the outlet area adjustment piece The enclosed outlet is the final outlet of the ejector nozzle; the outlet area adjustment piece rotates inward from the hinge point with the ejector nozzle sleeve to reduce the outlet area; 所述次流通道外壁后端铰接有第三流路辅助进气门(3)，该第三流路辅助进气门位于次流通道外壁后端与引射喷管套筒前端之间，当第三流路辅助进气门关闭时，该第三流路辅助进气门后端与引射喷管套筒前端相连接；The rear end of the outer wall of the secondary flow channel is hinged with a third flow path auxiliary intake valve (3), and the third flow path auxiliary intake valve is located between the rear end of the outer wall of the secondary flow channel and the front end of the ejector nozzle sleeve. When the third flow path auxiliary intake valve is closed, the rear end of the third flow path auxiliary intake valve is connected with the front end of the injection nozzle sleeve; 设计方法包括以下步骤：The design method includes the following steps: (1).引射喷管各设计参数通过收缩主喷管进口直径D无量纲化，使设计参数值均为无量纲量，定义引射喷管的坐标原点为主喷管入口截面圆心位置O；(1) The design parameters of the ejector nozzle are dimensionless by shrinking the inlet diameter D of the main nozzle, so that the design parameter values are all dimensionless quantities, and the coordinate origin of the ejector nozzle is defined. The center position O of the inlet section of the main nozzle ; (2).确定引射喷管的收缩主喷管(1)的尺寸，包括：主喷管出口直径Dp和主喷管长度L，其中出口直径Dp在使出口达到临界状态的情况下根据发动机流量基于流量公式计算得到；通过设置主喷管无量纲长度，即L/D取值范围为0.20～0.27而选择主喷管长度L；(2). Determine the size of the constricted main nozzle (1) of the ejector nozzle, including: the outlet diameter D p of the main nozzle and the length L of the main nozzle, wherein the outlet diameter D p is in the case of making the outlet reach a critical state Calculated based on the flow formula according to the engine flow; by setting the dimensionless length of the main nozzle, that is, the L/D value range is 0.20 ~ 0.27, and the main nozzle length L is selected; (3).引射喷管套筒(4)的型面参数包括：引射喷管套筒(4)喉道直径Dt以及距离主喷管出口的轴向距离Lt-Lp，先确定引射喷管套筒(4)的喉道位置，喉道距主喷管出口距离(Lt-Lp)/Dp的取值范围为-0.06～0.04；在确定了喉道位置的基础上，通过引射喷管套筒(4)喉道无量纲直径Dt/D的取值范围为1.09～1.12而确定引射喷管套筒(4)的喉道直径Dt；(3). The profile parameters of the ejector nozzle sleeve (4) include: the throat diameter D t of the ejector nozzle sleeve (4) and the axial distance L t -L p from the main nozzle outlet. Determine the position of the throat of the ejector nozzle sleeve (4), the distance between the throat and the outlet of the main nozzle (L t -L p )/D p ranges from -0.06 to 0.04; On the basis, the throat diameter D t of the ejector nozzle sleeve (4) is determined by the value range of the dimensionless diameter D t /D of the ejector nozzle sleeve (4) throat being 1.09-1.12; (4).出口面积调节片(7)的型面参数包括：尾缘角β，β取值范围为4°～8°；(4). The profile parameters of the outlet area adjusting sheet (7) include: the trailing edge angle β, and the value of β ranges from 4° to 8°; (5).第三流路辅助进气门(3)的开度为：最大旋转角度α，若次流通道处于回流状态，最大旋转角度α的取值范围为25°～30°；若次流通道(2)为顺流，第三流路辅助进气门(3)最大旋转角度α的取值范围为5°～15°；(5). The opening degree of the auxiliary intake valve (3) of the third flow path is: the maximum rotation angle α. If the secondary flow path is in the backflow state, the value range of the maximum rotation angle α is 25°～30°; The flow channel (2) is downstream, and the value range of the maximum rotation angle α of the third flow channel auxiliary intake valve (3) is 5° to 15°; (6).整合引射喷管的设计参数，在上述取值范围内进行迭代调整，如果引射喷管的推力性能未达标，返回步骤(2)在给出的主喷管无量纲长度(L/D)的取值范围内重新取值，取值方法为从下限开始每次增加一个取值间隔，该参数的取值间隔为0.01，若推力性能有所提升，进入步骤(3)；在步骤(3)给出的喉道距主喷管出口距离(Lt-Lp)/Dp取值范围内重新取值，起点为下限，取值间隔为0.01；在保证推力性能提升的前提下，依次对引射喷管套筒(4)喉道无量纲直径Dt/D、尾缘角β、最大旋转角度α在对应的取值范围内重新取值，起点分别参照步骤(3)、(4)、(5)提到的上下限，取值间隔分别为0.05、0.5°、3°；在上述设计过程中，若某参数的取值不能改善推力性能，则依照上述取值方法继续取值，直至推力性能有所提升再进入下一参数的优化，依次叠加各个优化后的参数，即可生成引射喷管最终的气动型面。(6) Integrate the design parameters of the ejector nozzle, and perform iterative adjustment within the above range of values. If the thrust performance of the ejector nozzle fails to meet the standard, return to step (2) at the given dimensionless length of the main nozzle ( Re-evaluate the value within the value range of L/D), and the value-taking method is to increase a value interval from the lower limit each time, and the value interval of this parameter is 0.01. If the thrust performance is improved, go to step (3); Re-value within the range of the distance between the throat and the main nozzle outlet (L t -L p )/D p given in step (3), the starting point is the lower limit, and the value interval is 0.01; Under the premise, the dimensionless diameter D t /D, the trailing edge angle β, and the maximum rotation angle α of the throat of the ejector nozzle sleeve (4) are re-valued in the corresponding value ranges, and the starting points refer to step (3) respectively. ), (4), (5) mentioned upper and lower limits, the value interval is 0.05, 0.5°, 3° respectively; in the above design process, if the value of a certain parameter cannot improve the thrust performance, the value according to the above The method continues to take the value until the thrust performance is improved, and then enters the optimization of the next parameter, and superimposes each optimized parameter in turn to generate the final aerodynamic profile of the ejector nozzle. 2.根据权利要求1所述的设计方法，其特征在于，在低马赫数飞行状态下，第三流路辅助进气门(3)开启，出口面积调节片(7)向内折以减小出口面积，此时引射喷管由收缩主喷管(1)内喷射的主流(8)、次流通道(2)内喷射的次流(9)和自第三流路辅助进气门(3)第三流路(10)流体共同产生推力；在超声速飞行状态下，第三流路辅助进气门(3)关闭，出口面积调节片(7)向外转平，引射喷管内的推力由主流(8)与次流(9)产生。2. The design method according to claim 1, characterized in that, under the low Mach number flight state, the third flow path auxiliary intake valve (3) is opened, and the outlet area adjustment sheet (7) is folded inward to reduce At this time, the injection nozzle is composed of the main flow (8) injected in the constricted main nozzle (1), the secondary flow (9) injected in the secondary flow channel (2), and the auxiliary intake valve ( 3) The fluids of the third flow path (10) jointly generate thrust; in the supersonic flight state, the auxiliary intake valve (3) of the third flow path is closed, the outlet area adjustment piece (7) is turned flat outward, and the ejection nozzle The thrust is generated by the main stream (8) and the secondary stream (9). 3.根据权利要求1或2所述的设计方法，其特征在于，所述第三流路辅助进气门(3)打开时向内翻折。3. The design method according to claim 1 or 2, characterized in that, when the third flow path auxiliary intake valve (3) is opened, it is folded inward. 4.根据权利要求1或2所述的设计方法，其特征在于，在出口面积调节片(7)外侧安装限位器(5)，使出口面积调节片(7)处于最大扩张时其外壁面(12)与引射喷管套筒(4)外壁面水平。4. The design method according to claim 1 or 2, characterized in that a limiter (5) is installed on the outside of the outlet area adjustment sheet (7), so that the outer wall surface of the outlet area adjustment sheet (7) is at the maximum expansion. (12) is level with the outer wall surface of the ejector nozzle sleeve (4). 5.根据权利要求1所述的设计方法，其特征在于，次流通道(2)内的气流流动方向为正向，即为顺流，气流从通道右侧排出；当实验或仿真中发现流动为反向时，通过增大第三流路辅助进气门(3)最大旋转角度直至次流通道(2)内的气流流动方向为正向。5. design method according to claim 1, is characterized in that, the air flow direction in the secondary flow channel (2) is forward, namely downstream, and air flow is discharged from the right side of the channel; when the flow is found in experiment or simulation When it is in the reverse direction, the maximum rotation angle of the auxiliary intake valve (3) of the third flow path is increased until the flow direction of the air flow in the secondary flow passage (2) is forward. 6.根据权利要求1所述的设计方法，其特征在于，当第三流路辅助进气门(3)关闭时与引射喷管套筒(4)完全贴合，即第三流路辅助进气门(3)与引射喷管套筒(4)之间不存在缝隙，且α始终大于等于0。6. The design method according to claim 1, characterized in that, when the third flow path auxiliary intake valve (3) is closed, it is completely fitted with the ejector nozzle sleeve (4), that is, the third flow path auxiliary There is no gap between the intake valve (3) and the injection nozzle sleeve (4), and α is always greater than or equal to 0. 7.根据权利要求1所述的设计方法，其特征在于，收缩段采用样条曲线设计，喉道处采用圆弧光滑过渡，扩张段采用多种直母线或多次曲线；扩张段母线方程为：Δy＝a2*Δx2+a3*Δx3+a4*Δx4，其中，Δx、Δy分别为横、纵坐标取值间距，Δy＝(2y-Dt)/(D-Dt),Δx＝(x-Lt)/(Le-Lt)，a2、a3、a4为方程系数，Dt为引射喷管套筒喉道直径，D为收缩主喷管进口直径，Lt为收缩主喷管进口到引射喷管套筒喉道位置的长度，Le为引射喷管总长，扩张段母线在起点和终点的切线与水平方向的夹角分别为θ1、θ2，其中θ1＝0°，θ2自行给定：若期望气流膨胀速率前后基本相当，给定a2＝-0.5tanθ2*(Le-Lt)+2.5，a3＝-1，a4＝0.5tanθ2*(Le-Lt)-0.5；7. The design method according to claim 1, wherein the constriction section adopts a spline curve design, the throat adopts a smooth arc transition, and the expansion section adopts a variety of straight generatrix or multiple curves; the generatrix equation of the expansion section is: : Δy=a 2 *Δx 2 +a 3 *Δx 3 +a 4 *Δx 4 , where Δx and Δy are the distance between the horizontal and vertical coordinates, respectively, Δy=(2y-D t )/(DD t ), Δx=(xL t )/(L e -L t ), a 2 , a 3 , and a 4 are equation coefficients, D t is the throat diameter of the ejector nozzle sleeve, D is the inlet diameter of the constricted main nozzle, L t is the length from the inlet of the shrinking main nozzle to the throat position of the ejector nozzle, Le is the total length of the ejector nozzle, and the angles between the tangents of the busbar of the expansion section at the starting point and the end point and the horizontal direction are θ 1 , θ , respectively 2 , where θ 1 =0°, θ 2 is given by itself: if the expected airflow expansion rate is basically the same before and after, given a 2 =-0.5tanθ 2 *(L e -L t )+2.5, a 3 =-1, a 4 =0.5tanθ 2 *(L e -L t )-0.5; 若期望有大的起始膨胀速率，给定a2＝0，a3＝4-tanθ2*(Le-Lt)，a4＝tanθ2*(Le-Lt)-3；若期望起始膨胀速率较小，给定a2＝6-0.5tanθ2*(Le-Lt)，a3＝-8，a4＝0.5tanθ2*(Le-Lt)+3。If a large initial expansion rate is expected, given a 2 =0, a 3 =4-tanθ 2 *(L e -L t ), a 4 =tanθ 2 *(L e -L t )-3; if The initial expansion rate is expected to be small, given a 2 =6-0.5tanθ 2 *(L e -L t ), a 3 =-8, a 4 =0.5tanθ 2 *(L e -L t )+3.
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