Integrated afterburner diffuser and radial stabilizer and method of designing same

Abstract

The application relates to the technical field of afterburner of an aero-engine, and particularly provides an integrated afterburner diffuser and radial stabilizer and a design method thereof, wherein an elliptic curve is adopted for the conical surface in the diffuser from the diffuser inlet to the flow blocking start position of the radial stabilizer, a straight conical surface is adopted for the position from the flow blocking start position of the radial stabilizer to the diffuser outlet, and the elliptic surface and the straight conical surface are tangent at the flow blocking start position X of the radial stabilizer s trut The design of the diffuser surface is completed. Then, the blocking ratio epsilon d , the number of radial stabilizers n and the radial height H of the radial stabilizer at the flow blocking cutoff position of the radial stabilizer are used to calculate the width W of the radial stabilizer strut , so that the integrated design of the diffuser and the radial stabilizer is completed. The integrated design method of the diffuser and the radial stabilizer provided by the application realizes the functions of deceleration expansion and low-resistance weight reduction.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine, in particular to an integrated afterburner diffuser and radial stabilizer and a design method thereof. BACKGROUND

[0002] The afterburner inlet flow velocity is large, and must be decelerated and diffused first, and then the design of on-duty ignition and combustion organization can be carried out. The diffuser structure composed of a splitter ring and an inner cone is one of the main components for the afterburner to diffuse the flow, and whether the diffusing performance is good or not is an important factor directly affecting the performance of the afterburner.

[0003] In order to achieve a low-loss diffusing effect, the conventional afterburner inner cone body usually adopts a full cone form or a truncated cone form. The large-area backflow area loss and large-area heat radiation caused by the truncated cone structure result in poor stealth performance, which cannot meet the aerodynamic performance and stealth requirements of fighter aircraft and engines. In addition, due to the requirement of weight reduction and simplification of advanced fighter aircraft, the integrated design of the afterburner has become a mainstream trend in the design of new generation military fighter aircraft engines. The integrated design of the diffuser and the radial stabilizer, as one of the important researches of the integrated design, is also becoming increasingly important. Therefore, a new integrated design method of the afterburner full-cone inner cone diffuser and the radial stabilizer is developed, which can meet the diffusing requirements, loss requirements and certain stealth requirements during the design of the diffuser. SUMMARY

[0004] In order to solve the above technical problems, the present application provides an integrated afterburner diffuser and radial stabilizer and a design method thereof, which fully considers the integrated design of the radial stabilizer on the basis of meeting the deceleration and diffusion requirements, obtains a diffuser design profile with low total pressure loss and small flow separation, and the present application also provides an afterburner with an integrated structure of the diffuser and the radial stabilizer obtained by the design method.

[0005] In the first aspect of the present application, an integrated design method of an afterburner diffuser and a radial stabilizer is provided, which comprises the following steps:

[0006] Step one, input the design indicators of the diffuser and the radial stabilizer, including the afterburner diffuser inlet splitter ring radius R shunt-in , the inlet inner cone radius R cone-in , the diffuser design length L d , the radial stabilizer length L strut , the number of radial stabilizers n and the design blockage ratio ε d ;

[0007] Step two, calculate the splitter ring profile function of the diffuser: input the splitter ring expansion angle θ, in the two-dimensional cylindrical coordinate system with the intersection point O of the diffuser inlet and the axis as the origin, the axial direction as the X axis and the radial direction as the Y axis, calculate the diffuser outlet radius R shunt-out cone-in +L d * tan θ, and calculate the profile function R shunt-out (x) = tan θ * x + R shunt shunt-in ;

[0008] Step three, calculate the equivalent expansion angle of the diffuser: calculate the equivalent expansion angle α of the diffuser by the following formula,

[0009]

[0010] Step four, calculate the inner cone profile function of the diffuser: input the starting blockage position X strut of the radial stabilizer, design an ellipse with A(0, R cone-in ) as the short semi-axis endpoint and the coordinate origin O(0, 0) as the center, and a straight line passing through the end point D(L d , 0) of the diffuser design length, tangent at the starting blockage position x = X strut of the radial stabilizer flow, to obtain the two-dimensional profile of the elliptical profile and the straight cone profile, and thus obtain the inner cone profile function of the diffuser:

[0011]

[0012] wherein b = R cone-in ,

[0013] Step five, calculate the width of the radial stabilizer: calculate the radial height H of the radial stabilizer according to the radius difference between the splitter ring and the inner cone at the section where the radial stabilizer flow blockage cutoff position x = X strut + L strut is located, take the flow passage section at the blockage cutoff position C of the radial stabilizer as the calculation section of the blockage ratio of the radial stabilizer, take the flow direction section of the airfoil design of the radial stabilizer as a rectangle, take the radial stabilizer height of the calculation section as H, the radial height as R shunt2 , and the inner cone radius as R cone2 , and calculate the width W strut of the radial stabilizer according to the following formula:

[0014]

[0015] ​​Step six, output the diffuser profile function and the radial stabilizer geometry: output the profile data of the diffuser and the geometry parameters of the radial stabilizer involved in steps one to five, and complete the integrated design of the diffuser and the radial stabilizer.

[0016] Preferably, in step three, when the equivalent expansion angle a is calculated, it is ensured that the equivalent expansion angle a is in the range of 20°-25°, and if the equivalent expansion angle a is not in the range of 20°-25°, the expansion angle θ of the splitter ring is re-input, the diffuser splitter ring profile function R shunt (x) is calculated.

[0017] Preferably, in step five, the width W strut of the radial stabilizer is calculated. strut After that, the position x=X strut at which the flow of the radial stabilizer is blocked is calculated, and the corresponding radius R strut of the circle with the width W cone2 of the radial stabilizer as the chord length is calculated, and the verification is performed according to the following formula:

[0018] nβ<2π

[0019] When the number n of the radial stabilizers and the central angle β satisfy the above formula, the width W strut of the radial stabilizer meets the design requirements.

[0020] When the number n of the radial stabilizers and the central angle β do not satisfy the above formula, the flow direction blocking start position X strut of the radial stabilizer is re-input in step one, and steps one to five are iterated until the width W strut of the radial stabilizer meets the design requirements.

[0021] Preferably, in the circle with R cone2 as the radius, the width W strut of the radial stabilizer is taken as the chord length, and the corresponding central angle β is calculated according to the following formula:

[0022]

[0023] Preferably, the integrated design method of the afterburner diffuser and the radial stabilizer further comprises:

[0024] Step seven, numerical simulation verification: design the afterburner model for numerical simulation according to the diffuser profile function and the radial stabilizer geometry output in step six, and verify the corresponding flow field and streamline distribution of the afterburner model under the boundary conditions of 0.3Ma Mach number at the inlet of the inner channel diffuser and the inlet of the outer channel; and

[0025] Step eight, parameter calculation iteration: analyze the flow field and streamline distribution corresponding to the afterburner model calculated in step seven; if the backflow area distribution behind the diffuser center cone of the afterburner model is large, or there is a large area of streamwise vortex behind the center cone, then adjust the design index of the diffuser and the radial stabilizer in step one; and / or adjust the starting blockage position X of the stabilizer in step four strut or adjust the selection of the diffuser inner cone surface;

[0026] The selection of the diffuser inner cone surface includes a circular arc surface, an elliptical surface, and an isobaric pressure gradient curve surface.

[0027] In the second aspect of the present application, an afterburner is provided, which comprises an afterburner diffuser and a radial stabilizer obtained by the integrated design method according to any one of the preceding embodiments.

[0028] The integrated design method of the diffuser and the radial stabilizer provided by the present application considers low-loss drag-reducing diffusers, enhanced infrared stealth performance, and simple and reliable design methods. BRIEF DESCRIPTION OF DRAWINGS

[0029] The accompanying drawings are included to provide a further understanding of the technical solutions of the present application, and constitute a part of the specification, and are used together with the embodiments of the present application to explain the technical solutions of the present application, and do not constitute a limitation on the technical solutions of the present application.

[0030] Figure 1 is a two-dimensional schematic view of the integrated structure of the afterburner diffuser and the radial stabilizer of the present application;

[0031] Figure 2 is a schematic view of the radial stabilizer rear edge section of the integrated structure of the diffuser and the radial stabilizer of the present application;

[0032] Figure 3 is a three-dimensional modeling schematic view of the integrated structure of the diffuser and the radial stabilizer of the present application;

[0033] Figure 4 is an eighth one structure schematic view of the present application containing the integrated structure of the diffuser and the radial stabilizer;

[0034] Figure 5 is a schematic view of the fluid domain of the afterburner of the present application containing the integrated structure of the diffuser and the radial stabilizer;

[0035] Figure 6 is the velocity field and streamline distribution at the research section of the afterburner containing the integrated structure based on the elliptical surface;

[0036] Figure 7To study the velocity field and trajectory distribution at the section of the afterburner with integrated structure containing the equal pressure gradient design profile;

[0037] Figure 8 The flow chart of the design method of the afterburner diffuser and radial stabilizer integration of the present application.

[0038] In the drawings:

[0039] 1- splitter ring;

[0040] 2- diffuser, 21- diffuser inlet, 22- diffuser outlet;

[0041] 3- inner cone, 31- elliptical profile, 32- straight conical profile;

[0042] 4- radial stabilizer;

[0043] 51- inner bypass inlet, 52- outer bypass inlet;

[0044] 6- afterburner outlet. DETAILED DESCRIPTION

[0045] The present application will be further described in conjunction with the drawings and specific embodiments. Those skilled in the art can understand that, since the afterburner has the overall cylindrical structure, it is preferred to describe the features in cylindrical coordinates, in which the radial direction is shown in the R direction in the drawings, and the axial direction is shown in the x direction in the drawings. Figure 1

[0046] In addition, considering that the structure in the afterburner has certain periodic repetition characteristics in the circumferential direction, for example, the radial stabilizer is provided with multiple equal-angle portions in the circumferential direction, when discussing the overall performance of the afterburner, only one section perpendicular to the circumferential direction needs to be taken to analyze the velocity, temperature, pressure and other parameters, and those skilled in the art should understand that the analysis of the section can be extended to the entire circumferential range based on the central symmetry.

[0047] It should be noted that: in the drawings, the same or similar reference signs represent the same or similar elements having the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, rather than all the embodiments, and the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present application, other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0048] In this document, "illustrative" means "serving as an example, instance, or illustration," and should not necessarily be construed as preferred or advantageous over other embodiments.​

[0049] As Figures 1-7 shown, the present application provides an integrated design method of diffuser and radial stabilizer, comprising the following steps:

[0050] Step one, design input preparation: obtaining design indicators for designing diffuser and radial stabilizer, the design indicators including the radius R shunt-in of the inlet split ring of the afterburner diffuser, the radius R cone-in of the inlet cone (i.e. the radial coordinate of point A in Figure 1 ), the design length L d of the diffuser (i.e. the length of the inlet cone), the length L strut of the radial stabilizer, the number n of the radial stabilizer, the design blockage ratio ε d of the radial stabilizer (i.e. the ratio of the rectangular area with W strut and H as the side length to the circular area with R cone2 as the inner diameter and R strut2 as the outer diameter shown in Figure 2 ), and the split ring expansion angle θ.

[0051] Step two, calculation of the diffuser split ring profile function R shunt (x): according to the afterburner diffuser split ring expansion angle θ, the inlet split ring radius R shunt-in , the inlet cone radius R cone-in , the design length L d of the diffuser, and the input split ring expansion angle θ, the inner surface of the split ring is designed as a conical surface, a two-dimensional Cartesian coordinate system with point O (0, 0) as the origin, x as the horizontal axis, and R as the vertical axis is established, and the diffuser outlet radius R shunt-out (wherein R shunt-out =R cone-in +tanθ) and the split ring profile function R shunt (x) (wherein R shunt (x)=tanθ·x+R shunt-in ) are calculated.

[0052] It should be noted that the diffuser outlet radius R shunt-out is designed on the premise that the diffuser inlet to the outlet is a conical surface, i.e. the straight line from R shunt-in to R shunt-out shown in Figure 1 , however, the present application does not limit this, i.e. the inner wall surface of the diffuser can also present a curved structure, at this time the diffuser outlet radius R shunt-out can be calculated by the corresponding curve equation.

[0053] Step three, the equivalent expansion angle α of the diffuser is calculated: according to the radius R of the diffuser inlet splitter ring in step one shunt-in , the radius R of the inlet inner cone cone-in , the design length L of the diffuser d and the radius R of the diffuser outlet obtained in step two shunt-out The equivalent expansion angle α of the diffuser is obtained by the general formula of equivalent expansion angle as shown in formula (1);

[0054]

[0055] The equivalent expansion angle is the conical angle representing the expansion degree of the non-circular conical diffuser converted into a circular conical diffuser, which is calculated according to the equivalent diameters of the diffuser inlet and outlet, and the larger the equivalent expansion angle is, the stronger the expansion ability of the diffuser is and the larger the expansion degree is.

[0056] Step four, the function R cone (x) of the diffuser inner cone profile is calculated: first, the starting blockage position X of the radial stabilizer is input strut (usually 0.4 of the central cone axial size is taken as the initial value, and the subsequent iterative calculation can be calculated according to the numerical simulation), and then the starting blockage position X of the radial stabilizer flow direction is input according to step one strut , the radius R of the inlet inner cone cone-in and the design length L of the diffuser d , a two-dimensional cylindrical coordinate system with point O(0,0) as the origin, x-axis as the horizontal axis and R-axis as the vertical axis is established, an ellipse with A(0,R cone-in ) as the short semi-axis endpoint and the coordinate origin O(0,0) as the center is tangent to the straight line passing through the terminal point D(L d ,0) of the diffuser design length at the radial stabilizer flow direction starting blockage position x=X strut , so as to obtain the two-dimensional profile of the elliptical profile and the straight conical profile, and the equation of the ellipse (the form of the ellipse equation is wherein b=R cone-in ) and the straight line equation (the form of the straight line equation is R=kx+c, wherein , so as to obtain the diffuser inner cone profile function

[0057] The technical effects of the application of the ellipse and the straight line tangent to construct the diffuser central cone profile include:

[0058] A simplified method for designing the central cone profile: Using an ellipse and a straight line tangent at a specified flow direction ensures that only one set of corresponding ellipse-straight line equations meets the design requirements. This effectively satisfies the design length of any central cone without mathematically unsolvable cases. For example, if a circular arc and a straight line are tangent at a specified flow direction to construct the central cone profile, no circular arc and straight line equations can simultaneously satisfy the constraint, resulting in a mathematically unsolvable situation. Furthermore, using a combination of equal pressure gradient curves and tangent straight lines to construct the central cone profile is also difficult to accurately meet the requirements of a central cone of a specified length. Additionally, this method improves aerodynamic performance: constructing the central cone profile using an ellipse and a straight line tangent at a specified flow direction effectively reduces the problem of excessive changes in the airflow turning angle gradient in the latter half of the central cone compared to equal pressure gradient designs.

[0059] Step 5, the width W of the radial stabilizer strut Calculation: Based on the radial stabilizer design blockage ratio ε input in step one. d The number of radial stabilizers n and the diffuser splitter ring profile function R obtained in steps two and four. shunt (x), Diffuser internal cone surface function R cone (x), calculate x = X at the flow direction blockage cutoff position of the radial stabilizer. strut +L strut The difference in radius between the splitter ring and the inner cone at the cross-section is the radial height H of the radial stabilizer.

[0060]

[0061] The radial stabilizer adopts an airfoil design with a rectangular flow section. The width W of the radial stabilizer is calculated according to the above equation (2). strut .

[0062] nβ<2π (3)

[0063] The cross-section of the airfoil support plate is shown in the attached figure. Figure 3 As shown, the width W of the radial stabilizer is checked. strut The width W of the radial stabilizer is calculated based on the relationship between the radial stabilizer width and the number of radial stabilizers n. strut Then, the position of the radial stabilizer blockage cutoff was calculated as x = X. strut +L strut The width W of the radial stabilizer strut The radius corresponding to the chord length is R. cone2 The central angle β (in radians) corresponding to the circle, when the number of radial stabilizers n and the central angle β satisfy the relationship shown in equation (3) above, can output the radial stabilizer width as W. strut If the requirements are not met, the radial stabilizer flow direction blockage start position X needs to be re-entered in step one. strut, re-perform other steps until the radial stabilizer width W strut meets the design requirements.

[0064]

[0065] with the radial stabilizer width W strut corresponding to the chord length of the circle with R cone2 as the radius, the calculation formula of the central angle β (radian) corresponding to the circle is shown in the above (4) formula, the central angle β, the radial stabilizer width W strut and the geometric relationship of the circle with R cone2 as the radius are shown in the attached Figure 2 .

[0066] Step six, output the diffuser profile function and the radial stabilizer geometric size: the profile data of the diffuser and the geometric parameters of the radial stabilizer involved in steps one to five, such as the radial stabilizer length L strut , the radial stabilizer flow blocking start position X strut , the radial stabilizer radial height H, and the number of radial stabilizers n, are used to realize the design of the radial stabilizer, thereby completing the integrated design of the diffuser and the radial stabilizer.

[0067] The input parameters are the afterburner diffuser inlet splitter radius R shunt-in = 400 mm, the inlet cone radius R cone-in = 200 mm, the diffuser design length L d = 500 mm, the splitter expansion angle θ = 5°, the radial stabilizer flow blocking start position X strut = 300 mm, the radial stabilizer length L strut = 100 mm, the design blocking ratio ε d = 0.25, and the number of radial stabilizers n = 8, and the integrated structure of the diffuser and the radial stabilizer obtained through the above design steps is shown in the attached Figure 3 .

[0068] Because the structure is highly central symmetric, the circumferential eighth structure is selected, as shown in the attached Figure 4 , as the research structure, the corresponding fluid domain model of the structure is extracted and the calculation of the demonstration example is carried out, on this basis, the afterburner model containing the integrated structure is designed, the length L ab of the afterburner is 1500 mm, as shown in the attached Figure 5 , the inlet Mach number of the inner bypass diffuser is 0.3Ma, and the inlet Mach number of the outer bypass is also 0.3Ma, the corresponding flow field and streamline distribution of the structure are shown in the attached Figure 6 .

[0069] To compare the differences in flow field characteristics between the integrated diffuser and radial stabilizer design method, an afterburner with an integrated diffuser and radial stabilizer structure based on an equal pressure gradient design is compared with an integrated diffuser and radial stabilizer structure using the new design method. Apart from the diffuser profile being different in the afterburner with this new structure, other factors such as equivalent expansion angle and blockage ratio are identical. The flow field distribution is shown in the attached figure. Figure 7 As shown.

[0070] Through append Figure 6 With appendix Figure 7 The flow field and streamline distribution shown indicate that the recirculation area behind the inner cone generated by this integrated structure is smaller than that behind the central cone of the diffuser under the equal pressure gradient design, and there is no large area of ​​flow vortex behind the central cone. By comparing the Mach number behind the diffuser with the inlet Mach number, it can be seen that the deceleration and diffusion performance of this integrated structure is also good.

[0071] It will be understood by those skilled in the art that if the results of the numerical simulation do not meet the requirements, the integrated design method of the afterburner diffuser and radial stabilizer further includes:

[0072] Step 7, Numerical Simulation Verification: Based on the diffuser profile function and radial stabilizer geometry output in Step 6, design an afterburner model for numerical simulation. Verify the flow field and streamline distribution of the afterburner model under boundary conditions of 0.3 Mach numbers at the inner diffuser inlet and outer bypass inlet; and

[0073] Step 8, Parameter Calculation Iteration: Analyze the flow field and streamline distribution corresponding to the afterburner model calculated in Step 7; if the recirculation zone distribution area behind the diffuser center cone of the afterburner model is large, or if there is a large area of ​​flow vortex behind the center cone, then: adjust the design parameters of the diffuser and radial stabilizer in Step 1; and / or adjust the initial clogging position X of the stabilizer in Step 4. strut Alternatively, adjust the selection of the conical surface inside the diffuser;

[0074] The selection of the conical surface inside the diffuser includes circular arc surface, elliptical surface, and equal pressure gradient curve surface.

[0075] The flowchart of a design method integrating an afterburner diffuser and a radial stabilizer is attached. Figure 8 As shown.

[0076] The above merely illustrates the specific embodiments of the present application, but the protection scope of the present application is not limited thereto, and any changes or replacements made by those skilled in the art within the technical scope disclosed by the present application shall be covered within the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A method of integrating a booster combustor diffuser with a radial stabilizer, characterized by, The method comprises the following steps: Step one, input the design parameters of the inlet and the radial stabilizer, including the radius of the inlet splitter R shunt-in , the radius of the inner cone R cone-in , the design length of the diffuser L d , the length of the radial stabilizer L strut , the number of the radial stabilizer n and the design blockage ratio ε d ; Step two, calculate the diffuser splitter ring profile function: input the splitter ring expansion angle θ, in the two-dimensional cylindrical coordinate system with the intersection O of the diffuser inlet and the axis as the origin, the axial direction as the X axis, and the radial direction as the Y axis, calculate the diffuser outlet radius R shunt-out by R cone-in + L d* tanθ shunt-out , and the profile function R shunt (x) of the outlet splitter ring is tanθ·x+R shunt-in ; Step three, calculating the equivalent expansion angle of the diffuser: the equivalent expansion angle of the diffuser is calculated by the following formula, Step four, calculate the inner cone function of the diffuser: input the starting block position X of the radial stabilizer strut , with A(0, R cone-in ) as the short semi-axis endpoint and the coordinate origin O(0, 0) as the center, and the ellipse is tangent to the straight line passing through the design length endpoint D(L d , 0) of the diffuser at the starting block position x=X strut of the radial stabilizer, to obtain the two-dimensional surface of the elliptical surface and the straight cone surface, thereby obtaining the inner cone function of the diffuser: wherein b = R cone-in , Step five, calculate the width of the radial stabilizer: according to the flow direction of the radial stabilizer at the blockage cutoff position x=X strut +L strut The difference between the radii of the two at the section where the flow is divided is calculated as the radial height H of the radial stabilizer. The flow channel section at point C, the blockage cutoff position of the radial stabilizer, is taken as the calculation section for the blockage ratio of the radial stabilizer. The flow direction section of the radial stabilizer is designed as a rectangle. The radial stabilizer height of the calculation section is H, the radial height is R shunt2 , and the inner cone radius is R cone2 . The width W of the radial stabilizer is calculated according to the following formula strut : Step six, outputting the diffuser profile function and the radial stabilizer geometric size: the profile data of the diffuser and the geometric parameters of the radial stabilizer involved in steps one to five are outputted, and the integrated design of the diffuser and the radial stabilizer is completed.

2. The method of claim 1, wherein, In the step three, the equivalent expansion angle a is calculated, and it is ensured that the equivalent expansion angle a is in the range of 20°-25°. If the equivalent expansion angle a is not in the range of 20°-25°, the expansion angle θ of the splitter ring is re-input, and the splitter ring profile function R of the diffuser is calculated shunt (x).

3. The method of claim 1, wherein, Step five calculates the width W of the radial stabilizer strut After that, the width W of the radial stabilizer at the radial stabilizer blockage cutoff position x = X strut + L strut is calculated strut The corresponding radius R of the chord length is calculated cone2 The corresponding central angle β of the circle with the radius R is calculated, and the following is verified: nβ＜2π When the number n of radial stabilizers, the central angle β satisfy the above formula, then the radial stabilizer width W strut satisfy the design requirements; When the number n of radial stabilizers and the central angle β do not satisfy the above formula, then the radial stabilizer flow direction blockage starting position X is re-input in step one strut And iterate step one to step five until the radial stabilizer width W strut satisfies the design requirements.

4. The method of claim 3, wherein, In a circle with R cone2 as the radius, with the radial stabilizer width W strut as the chord length, the corresponding central angle β is calculated using the following equation:

5. The method of claim 1, wherein, Further comprising: Step seven, numerical simulation verification: the afterburner model designed for numerical simulation is designed according to the diffuser profile function and the radial stabilizer geometric size outputted in step six, and the flow field and streamline distribution corresponding to the afterburner model are verified under the boundary condition that the Mach number of the inner and outer diffuser inlets is 0.3Ma; and wherein the selection of the diffuser inner cone profile includes a circular arc profile, an elliptical profile, and an isobaric pressure gradient curve profile; Step eight, parameter calculation iteration: analyze the flow field and streamline distribution corresponding to the afterburner model calculated in step seven; if the backflow area distribution behind the diffuser center cone of the afterburner model is large, or there is a large area of streamwise vortex behind the center cone, then adjust the design index of the diffuser and the radial stabilizer in step one; and / or adjust the starting blockage position X of the stabilizer in step four strut or adjust the selection of the diffuser inner cone surface.

6. A thrust-reverser combustion chamber, characterized in that The afterburner diffuser and the radial stabilizer obtained by the integrated design method according to any one of claims 1-5.

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