Rear support plate serial design method and system with rectification and shielding functions
By generating the support profile using Bezier curves and employing a tandem layout method, a rear support tandem layout with both rectification and shielding functions was designed. This solved the thrust and aerodynamic loss problem of axisymmetric nozzles when shielding infrared signals from high-temperature components, achieving efficient infrared stealth and improved aerodynamic performance.
Patent Information
- Application Number
- CN202511070807.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-31
- Publication Date
- 2025-11-18
AI Technical Summary
Existing axisymmetric nozzles are unable to effectively suppress infrared signals from high-temperature components behind the turbine, resulting in reduced engine thrust and increased aerodynamic losses.
A rear support plate tandem arrangement method that combines rectification and shielding functions is designed. The support plate profile is generated using Bezier curves. The tandem arrangement achieves full shielding of high-temperature components and reduces flow resistance loss by interrupting the flow transition section.
It achieves complete rearward shielding of high-temperature components, reduces the infrared radiation intensity of the engine, and at the same time reduces separation losses in the flow transition region and flow resistance losses caused by boundary layer thickening, thereby improving aerodynamic performance.
Smart Images
Figure CN120974629A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application belongs to the field of gas turbine engine design, and particularly relates to a rear strut string design method and system with flow regulation and shielding functions. BACKGROUND
[0002] With the continuous development of military technology, the air defense force is gradually enhanced, and how to improve the survivability of military aircraft is crucial. Improving the stealth performance of the aircraft can reduce the probability of being detected and discovered, thereby improving the survivability in the battlefield. Radar stealth and infrared stealth are two extremely important aspects of the stealth effectiveness of military aircraft.
[0003] For the problem of radar stealth, researchers achieve radar stealth through aircraft shape design, spraying stealth materials, and using advanced electronic countermeasures systems.
[0004] For the problem of infrared stealth, the exhaust system of an aero-engine is one of the main infrared radiation signals of a military aircraft. In order to reduce the infrared signal of the engine exhaust device, researchers have developed stealth configurations such as binary nozzles and S-bend nozzles, such as the F-22 fighter, B-2 bomber, and French "neuron" unmanned aerial vehicle. Among them, the binary nozzle reduces the temperature of the high-temperature gas by strengthening the mixing of the high-temperature gas and the atmosphere, and reduces the infrared signal in combination with wall cooling technology. The S-bend nozzle bends the wall based on the binary nozzle, thereby shielding the high-temperature components of the engine and improving the infrared stealth performance. However, the use of these two nozzles will increase the aerodynamic loss of the engine, resulting in a decrease in the thrust of the engine.
[0005] As the most widely used axisymmetric nozzle at present, compared with the special-shaped nozzle, it has the advantage of small thrust loss, but it is difficult to effectively suppress the infrared signal of high-temperature components such as low-pressure turbines. The turbine rear casing is located between the turbine components and the tail nozzle of the engine, and the core component, the flow regulation strut, on the one hand, is a part of the load-bearing framework of the engine, and on the other hand, regulates the high-temperature gas from the turbine to reduce exhaust loss. Some researchers have proposed a design method and system for the internal and external flow coupling structure of the fully shielded turbine rear strut, which shields the high-temperature components of the engine and cools the strut.
[0006] Under the above background, how to design a new turbine rear strut configuration with backward geometric shielding function and low flow resistance loss has become a challenging problem. SUMMARY
[0007] The present application aims at the deficiencies of the prior art, and provides a rear strut plate string design method with rectification and shielding functions.
[0008] In order to achieve the above-mentioned purpose, the present application adopts the following technical scheme: In a first aspect, the present application provides a rear strut plate string design method with rectification and shielding functions, comprising the following steps: S1, designing two or more turbine rear strut plate string profiles along the radial section; S2, in any section, the front row strut plate profile and the rear row strut plate profile are designed respectively, the shape of the front row strut plate is determined by the middle camber line thereof, the middle camber line of the front row strut plate is generated by a third-order Bezier curve; the leading edge profile and the trailing edge profile of the front row strut plate are both generated by a second-order Bezier curve, so that the leading edge profile and the trailing edge profile are tangent to the middle part profile of the strut plate; in the same section, the rear row strut plate profile is designed by the same method as the front row strut plate profile, and the outlet geometric angle of the rear row strut plate is consistent with the axial direction; S3, after the strut plate profile design of all sections is completed, the stacking mode of the string strut plate is determined, the string rear strut plate profiles of different sections are sequentially arranged along the radial direction to generate a continuous and smooth three-dimensional profile of the string rear strut plate; in the profile of both sides of the strut plate, the profile that can be observed from the rear is defined as the visible profile of the string strut plate, and the profile that cannot be observed is defined as the invisible profile of the string strut plate; S4, the radial parameters of the upper end wall and the lower end wall of the rear strut plate and the tail cone are determined, the upper and lower end wall profiles and the tail cone profile of the rear strut plate are obtained by rotation, and the three-dimensional modeling of the string strut plate is obtained by trimming the three-dimensional profile of the string strut plate with the upper and lower end wall profiles of the rear strut plate.
[0009] Further, in S2, the third-order Bezier curve has four control points, the first and last control points are located at the starting point and the ending point of the curve and remain unchanged, and the shape of the curve is changed by changing the positions of the middle two control points; Further, in S2, according to the relative positions of the starting point and the ending point of the middle camber line, the shape of the middle camber line is "C" or "S", and the shape of the strut plate corresponds to "C" or "S".
[0010] Further, in S2, in any section, the strut plate profile is formed by the middle camber line plus the thickness distribution, and at different arc length positions of the middle camber line, the strut plate thickness follows the change rule of the quadratic function; The thickness of the support plate follows a quadratic function variation rule, and the thickness of the front edge, midpoint and tail edge of the camber line is given in the design process, and the thickness of the support plate at each position of the camber line is generated by interpolation; at each position of the camber line, a circle with the local thickness of the support plate as the diameter is made, and the envelope of all the circles is the support plate profile; Further, in S2, when designing the rear support plate profile, the determination of the front edge coordinate of the rear support plate is obtained by the tail edge coordinate of the front support plate, the axial overlap rate and the circumferential pitch ratio of the tandem support plate, and the tail edge coordinate of the rear support plate is obtained according to the front edge coordinate of the front support plate and the calculation of the axial chord length, pitch, shielding width and tail edge thickness of the rear support plate; the inlet geometric angle of the front support plate is consistent with the outlet flow angle of the last stage low-pressure turbine.
[0011] Further, in S2, when designing the rear support plate profile, full shielding refers to that the projection of the circumferentially adjacent two columns of tandem support plates at any axial section has an overlapping or tangent part, and due to the existence of the overlapping or tangent part, the components upstream of the support plate cannot be observed at the outlet of the rear support plate.
[0012] Further, in S1, at any section, the rear support plate tandem profile is composed of the front support plate profile and the rear support plate profile.
[0013] In a second aspect, the application provides a rear support plate tandem design system with rectification and shielding functions, which comprises a type design module, a support plate profile design module, a tandem rear support plate three-dimensional surface design module and a tandem support plate three-dimensional modeling design module. The type design module is used to design two or more turbine rear support plate tandem profiles along the radial section; The support plate profile design module is used to design the front support plate profile and the rear support plate profile at any section respectively, the shape of the front support plate is determined by its camber line, and the camber line of the front support plate is generated by a third-order Bezier curve; the leading edge profile and the tail edge profile of the front support plate are generated by a second-order Bezier curve, so that the leading edge profile and the tail edge profile are tangent to the middle part profile of the support plate; in the same section, the rear support plate profile is designed by the same method as the front support plate profile, and the outlet geometric angle of the rear support plate is consistent with the axial direction; The tandem rear support plate three-dimensional surface design module is used to determine the stacking mode of the tandem support plate after the design of the support plate profile at all sections, and generate a continuous and smooth tandem rear support plate three-dimensional surface by arranging the tandem rear support plate profiles of different sections along the radial direction in turn; The tandem support plate three-dimensional modeling design module is used to determine the radial parameters of the upper end wall and the lower end wall of the rear support plate and the tail cone, obtain the type surface of the upper end wall and the lower end wall of the rear support plate by rotation, and trim the tandem support plate three-dimensional surface by using the type surface of the upper end wall and the lower end wall of the rear support plate to obtain the three-dimensional modeling of the tandem support plate.
[0014] In a third aspect, the present application can provide a rear strut plate cascade blade with rectification and shielding functions, which is obtained by using the rear strut plate cascade design method with rectification and shielding functions.
[0015] Finally, the present application can also provide an aero-engine, the rectification strut plate of the turbine rear casing being obtained by using the rear strut plate cascade blade with rectification and shielding functions obtained by using the rear strut plate cascade design method with rectification and shielding functions.
[0016] Compared with the prior art, the present application has at least the following beneficial effects: the present application relates to a rear strut plate cascade design method with rectification and shielding functions, which parameterizes the description of the shielding width, realizes flexible adjustment of the backward geometric shielding rate, and the designed rear strut plate can realize positive backward complete shielding of high-temperature components such as an upstream low-pressure turbine, and can effectively inhibit the backward infrared signal of the exhaust system; in order to reduce the flow resistance loss as much as possible while ensuring the geometric shielding, a new layout method of intermittently arranging the strut plate in the flow turning area to form a cascade arrangement is proposed, through the cascade blade layout, the boundary layer loss caused by the thickening of the boundary layer and the separation loss of the flow turning area can be effectively reduced, and the full-shielding turbine rear strut plate designed by using the above method can realize backward full shielding of high-temperature components such as low-pressure turbine blades while ensuring the aerodynamic performance, so as to reduce the infrared radiation intensity of the engine. BRIEF DESCRIPTION OF DRAWINGS
[0017] Figure 1 is a schematic diagram of different cross-sectional profiles of the cascade strut plate; Figure 2 is a schematic diagram of the profile and parameters of the cascade strut plate; Figure 3 is a schematic diagram of the arc line and control points in the cascade strut plate; Figure 4a is a schematic diagram of the three-dimensional modeling of the rear strut plate cascade blade, Figure 4b is a schematic diagram of the backward full shielding of the rear strut plate cascade blade; BRIEF DESCRIPTION OF DRAWINGS: 1-root section, 2-middle section, 3-top section, 4-visible surface of the cascade strut plate, 5-non-visible surface of the cascade strut plate, 6-arc line of the front row of strut plates, 7-first end control point of the front row of strut plates, 8-first intermediate control point of the front row of strut plates, 9-second intermediate control point of the front row of strut plates, 10-second end control point of the front row of strut plates, 11-arc line of the rear row of strut plates, 12-first end control point of the rear row of strut plates, 13-first intermediate control point of the rear row of strut plates, 14-second intermediate control point of the rear row of strut plates, 15-second end control point of the rear row of strut plates, 16-front row of strut plates, 17-rear row of strut plates, 18-upper end wall of the cascade strut plate, 19-lower end wall and tail cone of the cascade strut plate. DETAILED DESCRIPTION
[0018] In order to better illustrate the parameterized modeling method and advantages of the present application, the present application is further described in detail below by a specific example in conjunction with the drawings, and it should be noted that this is only a part of the implementation of the present modeling method, but not a limitation of the present modeling method.
[0019] The applicant found through long-term theoretical and practical research that the turbine rear casing fairing strut is designed into a full-shielding configuration capable of geometrically shielding the low-pressure turbine part, which is expected to significantly reduce the infrared radiation signal of the axisymmetric nozzle exhaust system, and is a new idea for improving the infrared stealth performance of the engine; the shielding width is described in a parameterized manner, and the flexible adjustment of the backward geometric shielding rate is realized, the designed rear strut can realize positive backward complete shielding of the upstream low-pressure turbine and other high-temperature parts, and can effectively suppress the backward infrared signal of the exhaust system; at the same time, considering that the flow passage of the geometric shielding strut is long and there is a flow turning, in order to further ensure the aerodynamic performance and reduce the thrust loss, the strut is designed into a new configuration of a tandem blade with a front row of struts and a rear row of struts. Due to the use of the tandem layout, the discontinuity between the front and rear rows of struts on the one hand avoids the continuous thickening of the boundary layer, thereby reducing the boundary layer flow resistance loss, and on the other hand forces the airflow to locally accelerate to increase the turbulence, thereby weakening the separation loss in the flow turning area.
[0020] The present application is a rear strut tandem design method with flow regulation and shielding functions, and the specific design steps are as follows: S1, according to the incoming flow conditions and actual design requirements, a certain number of radial sections are selected to design the tandem strut profile, in this example, three radial sections of root section tandem strut profile 1, middle section 2 and top section 3 are selected for tandem strut profile design, as shown in Figure 1 .
[0021] S2, as shown in Figure 2 , at any section, first determine the axial chord length , pitch , shielding width of the rear strut tandem blade; set the tandem axial chord length ratio and the tandem width ratio , wherein is the axial chord length of the front row of struts, is the width of the front row of struts, and , , the axial chord length and the width of the front row of struts can be determined by calculation. Secondly, the inlet geometric angle , the outlet geometric angle and the front edge coordinate of the front row of struts are determined, and the trailing edge coordinate of the front row of struts is obtained by calculation.,in , In this example, take , .
[0022] S3, as Figure 3 As shown, in any cross-section, the shapes of the front and rear support plate profiles of the tandem blades of the rear support plate depend on the shape of their respective mid-curves. When designing the mid-curve 6 of the front support plate, a third-order Bezier curve is used to generate the mid-curve 6 of the front support plate. The coordinates of the leading edge and trailing edge of the front support plate are set as the first end control point 7 and the second end control point 10 in the Bezier curve and remain unchanged. The tangents at the start and end of the Bezier curve can intersect at a certain point. The first intermediate control point 8 and the second intermediate control point 9 of the Bezier curve are located on the line segment formed by the intersection of the tangents at the start and end of the Bezier curve and the start and end points, or on their extensions. In this example, the first intermediate control point 8 and the second intermediate control point 9 are located at the midpoints of the line segment formed by the line connecting the intersection of the tangents and the start point, and the line segment formed by the line connecting the intersection of the tangents and the end point, respectively. The middle arc of the front support plate is "C" shaped. In the profiles on both sides of the support plate, the profile that can be observed from directly behind is defined as the visible profile 4 of the tandem support plate, and the profile that cannot be observed is defined as the invisible profile 5 of the tandem support plate.
[0023] S4, at any cross-section, the profile of the front support plate is formed by the mid-arc line plus the local support plate thickness distribution. During the design process, the thickness at the starting point, midpoint, and ending point of the mid-arc line of the front support plate is first determined. The thickness at different locations is determined by the axial chord length of the tandem support plates. The multiples represent the thickness distribution at other locations along the arc of the support plate, formed by quadratic interpolation based on the three-point thickness. Secondly, using the local thickness as the diameter, circles centered on the arc are drawn at different locations along the arc; the envelopes of these circles form the profile of the front support plate. In this example, the thicknesses at the starting point, midpoint, and ending point of the arc of the front support plate are respectively... , and .
[0024] In section S5, the leading and trailing edge profiles of the front support plate are generated using a second-order Bezier curve at any cross-section. Of the three control points on the second-order Bezier curve, control point one is the starting point of the mid-arc line; control point three is the expected intersection point where the soon-to-be-generated leading and trailing edge profiles intersect with the front support plate profile generated in section S4; and control point two is the intersection point of the tangent to the mid-arc line at the intersection point and the normal line at the starting point of the mid-arc line. These three control points ensure a smooth transition between the leading and trailing edge profiles and the front support plate profile at control point three. This completes the design and generation of the front support plate profile.
[0025] S6, in any cross section, when determining the trailing support plate leading edge coordinate and the trailing support plate trailing edge coordinate, the axial overlap degree is introduced and the circumferential pitch ratio wherein is the difference between the axial coordinate of the trailing support plate leading edge and the axial coordinate of the front support plate trailing edge, represents that the front and rear support plates have axial overlap, and vice versa represents that the front and rear support plates have no axial overlap, is the difference between the circumferential coordinate of the front support plate trailing edge and the circumferential coordinate of the trailing support plate leading edge, and the positive and negative values thereof represent whether the front and rear support plates have circumferential overlap. Thus, the trailing support plate leading edge coordinate wherein , , the trailing support plate trailing edge coordinate wherein , , can be obtained from the front support plate leading edge coordinate and the axial chord length , , In this example, the trailing support plate inlet geometric angle and the outlet geometric angle are set.
[0026] S7, in any cross section, the middle arc line 11 of the trailing support plate is also generated by a third-order Bezier curve, and the leading edge and trailing edge coordinates of the trailing support plate are set as the first end control point 12 and the second end control point 15 of the Bezier curve and remain unchanged. The tangent at the starting point of the Bezier curve and the tangent at the ending point can intersect at a point, and the first intermediate control point 13 and the second intermediate control point 14 of the Bezier curve are located on the line segment formed by the intersection point of the tangent at the starting point and the tangent at the ending point and the starting point and the ending point or the extension line thereof, and in this example, the first intermediate control point 13 and the second intermediate control point 14 are located at the midpoint of the line segment, and the middle arc line of the trailing support plate is of the "C" type.
[0027] S8, in any cross section, the trailing support plate profile is generated by the same method as S4. First, the thicknesses at the starting point of the middle arc line, the midpoint of the middle arc line, and the ending point of the middle arc line of the trailing support plate are determined, and the thickness distribution at other positions of the support plate middle arc line is formed by quadratic function interpolation according to the three-point thicknesses; second, a circle with the local thickness as the diameter is made at different positions of the middle arc line with the center on the middle arc line, and the envelope of these circles can form the trailing support plate profile. In this example, the thicknesses at the starting point of the middle arc line, the midpoint of the middle arc line, and the ending point of the middle arc line of the trailing support plate are , , and , respectively.
[0028] S9, in any cross section, the front edge profile and the trailing edge profile of the rear row of struts are also generated by a second-order Bezier curve. Among the three control points of the second-order Bezier curve, the control point one is the starting point of the camber line, the control point three is the intersection point of the front trailing edge profile to be generated and the front row of strut profile generated in S8, and the control point two is the intersection point of the tangent line of the camber line at the intersection point and the normal line at the starting point of the camber line, which ensures the smooth transition of the front edge profile, the trailing edge profile and the front row of strut profile at the control point three. Thus, the design and generation of the rear row of strut profile are completed S10, after the design of the front row of strut profile and the rear row of strut profile in three cross sections is completed, the stacking mode of the tandem struts is determined, for example, the front edge stacking, the trailing edge stacking or the barycenter stacking, and a continuous and smooth three-dimensional profile of the tandem struts is generated; different circumferential stacking can form a three-dimensional profile of the tandem struts with bending and twisting characteristics.
[0029] S11, the axial and radial coordinates of the upper end wall 18 of the tandem struts, the lower end wall of the tandem struts and the tail cone 19 are determined, the upper end wall profile of the tandem struts, the lower end wall of the tandem struts and the tail cone profile are generated by rotation, and the final three-dimensional modeling of the tandem struts is obtained by trimming the strut profile, as shown in Figure 4a . Figure 4b For the tandem struts observed from the downstream direction, the upstream components of the struts are shielded.
[0030] Example 2, based on the above design method, the present application can also provide a rear strut tandem blade with rectification and shielding functions, and the tandem struts in the downstream direction completely shield the upstream components of the struts.
[0031] Example 3, an aero-engine is also provided, and the rectification struts of the turbine rear casing adopt the rear strut tandem blade with rectification and shielding functions obtained based on the design method of the present application.
[0032] The rear strut tandem design method designed by the present application can parameterize the shielding width, realize the load bearing function of the rear struts, achieve the rear geometric shielding of high-temperature components such as low-pressure turbines, reduce the rear infrared radiation of the engine, and at the same time, the rear strut tandem design can reduce the aerodynamic loss while rectifying, reduce the fuel consumption rate of the engine and improve the economy.
[0033] The above examples are only one design method of the present application, and according to the actual design requirements, the parameters can be adjusted locally without departing from the design principles of the present application, which are all within the protection scope of the present application.
Claims
1. A method for designing a tandem rear support plate that combines rectification and shielding functions, characterized in that, Includes the following steps: S1, design two or more radial sections with turbine rear support plate tandem profiles; S2, at any cross section, design the front row support plate profile and the rear row support plate profile respectively. The shape of the front row support plate is determined by its own central arc line, which is generated by a third-order Bezier curve. The leading edge profile and trailing edge profile of the front row support plate are both generated by a second-order Bezier curve, so that the leading edge profile and trailing edge profile are tangent to the profile of the middle part of the support plate. At the same cross section, design the rear row support plate profile using the same method as the front row support plate profile. The exit geometry angle of the rear row support plate is consistent with the axial direction. S3. After the design of the support plate profiles of all sections is completed, the stacking method of the tandem support plates is determined. The tandem support plate profiles of different sections are arranged in the radial direction to generate a continuous and smooth three-dimensional surface of the tandem support plate. S4. Determine the radial parameters of the upper and lower end walls and the tail cone of the rear support plate. Obtain the profiles of the upper and lower end walls and the tail cone of the rear support plate by rotation. Use the profiles of the upper and lower end walls of the rear support plate to trim the three-dimensional profiles of the tandem support plates to obtain the three-dimensional shape of the tandem support plates.
2. The turbine rear support plate tandem blade design method with both rectification and geometric shielding functions as described in claim 1, characterized in that, In S2, the third-order Bezier curve has four control points. The first and last two control points are located at the start and end points of the curve and remain unchanged. The shape of the curve is changed by changing the positions of the two middle control points.
3. The rear support plate tandem design method with both rectification and shielding functions as described in claim 1, characterized in that, In S2, depending on the relative positions of the starting and ending points of the middle arc, the shape of the middle arc is either "C" or "S", and the shape of the support plate is also either "C" or "S".
4. The rear support plate tandem design method with both rectification and shielding functions as described in claim 1, characterized in that, In S2, at any cross section, the support plate profile is formed by the distribution of thickness along the middle arc. At different arc lengths of the middle arc, the thickness of the support plate follows a quadratic function variation law. The thickness of the support plate follows the variation law of a quadratic function. During the design process, the thickness at the leading edge, midpoint and trailing edge of the middle arc is given, and the support plate thickness at each position of the middle arc is generated by interpolation. At each position of the middle arc, a circle is drawn with the local support plate thickness as the diameter, and the envelope of all circles is the support plate profile.
5. The rear support plate tandem design method with both rectification and shielding functions as described in claim 1, characterized in that, In S2, when designing the profile of the rear support plate, the coordinates of the leading edge of the rear support plate are determined by the coordinates of the trailing edge of the front support plate, the axial overlap rate of the tandem support plates, and the circumferential pitch ratio. The coordinates of the trailing edge of the rear support plate are obtained by calculating the coordinates of the leading edge of the front support plate, the axial chord length, pitch, shielding width of the tandem support plates, and the thickness of the trailing edge of the rear support plate. The inlet geometry of the front support plate is consistent with the outlet airflow angle of the final stage low-pressure turbine.
6. The rear support plate tandem design method with both rectification and shielding functions as described in claim 1, characterized in that, In S2, when designing the rear support plate profile, full obstruction means that the projections of two adjacent circumferential rows of tandem support plates on any axial section have overlapping or tangential portions. Due to the existence of these overlapping or tangential portions, the components upstream of the support plate cannot be observed at the rear support plate outlet.
7. The rear support plate tandem design method with both rectification and shielding functions as described in claim 1, characterized in that, In S1, at any cross section, there is a rear support plate tandem profile composed of the front support plate profile and the rear support plate profile.
8. A tandem design system for a rear support plate that combines rectification and shielding functions, characterized in that, It includes a type design module, a support plate profile design module, a 3D surface design module for tandem support plates, and a 3D modeling design module for tandem support plates. The profile design module is used to design two or more turbine rear support plate tandem profiles along radial sections; The support plate profile design module is used to design the front and rear support plate profiles at any cross section. The shape of the front support plate is determined by its own central arc, which is generated by a third-order Bezier curve. The leading and trailing edge profiles of the front support plate are generated by second-order Bezier curves, ensuring that the leading and trailing edge profiles are tangent to the profile of the middle part of the support plate. At the same cross section, the rear support plate profile is designed using the same method as the front support plate profile, and the exit geometry of the rear support plate is consistent with the axial direction. The 3D profile design module for tandem support plates is used to determine the stacking method of tandem support plates after the support plate profiles of all sections are designed. It generates a continuous and smooth 3D profile of tandem support plates by arranging the tandem support plate profiles of different sections radially. The tandem support plate 3D modeling design module is used to determine the radial parameters of the upper and lower end walls and the tail cone of the rear support plate, obtain the upper and lower end walls and tail cone profiles of the rear support plate by rotation, and use the upper and lower end wall profiles of the rear support plate to trim the tandem support plate 3D model to obtain the tandem support plate 3D model.
9. A tandem blade with rear support plate that combines rectification and shielding functions, characterized in that, The rear support plate tandem design method with both rectification and shielding functions as described in any one of claims 1-7 is adopted.
10. An aircraft engine, characterized in that, The turbine rear casing uses turbine rear support plate tandem blades obtained by the rear support plate tandem design method that combines rectification and shielding functions as described in any one of claims 1-7.