Small axial turbine guide vane and casing integrated structure and its molding method

Abstract

The application relates to a small-sized axial flow turbine guide vane and casing integrated structure and a shaping method thereof, and belongs to the field of aeroengines. The application solves the problems of high requirements for welding equipment and environment, easy cracking of the welding position under high-temperature stress, and easy damage caused by stress concentration due to the bending treatment of the inner hole end of the guide vane, which exist in the separate machining and then welding connection of the turbine guide vane, the flame tube exhaust guide pipe and the turbine shaft sleeve in the existing small-sized turbine engine. The integrated shaping method of the turbine guide vane and the casing comprises the following steps: collecting design parameters required by the integrated casing; determining the size parameters of the flame tube exhaust guide pipe; determining the size parameters of the guide vane; determining the size parameters of the inner support of the guide vane; and determining the size parameters of the turbine rotor casing section. The application can integrate the shaping of the small-sized axial flow turbine guide vane and the casing, and adapt to the integrated design requirements of the small-sized axial flow turbine guide vane and the casing.

Description

TECHNICAL FIELD

[0001] The application relates to a small axial turbine guide vane and casing integrated structure and a molding method thereof, and belongs to the field of aero-engines. BACKGROUND

[0002] The turbine guide vane of an aero-engine is composed of an outer ring, an inner ring and guide vanes, and the guide vanes are between the inner and outer rings. In an existing small turbine engine, the turbine guide vane, the flame tube exhaust guide pipe and the turbine shaft sleeve are connected together through machining and welding respectively. Since the combustion gas in the combustion chamber needs to pass through the guide vane and then pass through the turbine to do work outside, the connection needs to have good sealing performance to prevent the combustion gas from leaking out, so sealing welding technology needs to be used in the assembly process. The welding technology has high requirements for welding equipment and environment, and the thermal stress generated during heating treatment needs to be eliminated to control the deformation degree of the parts. Even so, under the harsh working environment of high temperature stress, cracks and other faults are prone to occur in the welding parts first. In the small turbine engine, in order to connect the turbine guide vane and the turbine shaft sleeve together, the inner hole end of the guide vane is bent to fit with the sleeve for welding operation. The design causes a large bending angle at the bending part, which causes stress concentration and is prone to damage in advance. Therefore, a molding method for integrating a small axial turbine guide vane and a casing is provided. SUMMARY

[0003] The application provides a small axial turbine guide vane and casing integrated structure and a molding method thereof, to solve the problems that in the existing small turbine engine, the turbine guide vane, the flame tube exhaust guide pipe and the turbine shaft sleeve are connected through machining and welding respectively, the welding equipment and environment have high requirements, and cracks and other faults are prone to occur in the welding parts under the high temperature stress environment; and the inner hole end of the guide vane is bent to connect the sleeve, which causes a large bending angle at the bending part, resulting in stress concentration and prone to damage in advance.

[0004] The small axial turbine guide vane and casing integrated structure comprises a front mounting edge, a flame tube exhaust guide pipe, a guide vane outer ring, a turbine rotor casing, a guide vane blade, a guide vane inner ring, a guide vane inner support, a shaft sleeve mounting edge and a shaft sleeve mounting edge bolt hole, the front mounting edge is connected with the flame tube exhaust guide pipe in a stepped manner, the flame tube exhaust guide pipe and the guide vane outer ring are connected in a stepped manner, the guide vane outer ring is connected with the turbine rotor casing, the guide vane outer ring is connected with the guide vane blade, the guide vane blade is connected with the outer circumferential surface of the guide vane inner ring, the guide vane inner support is connected with the inner circumferential surface of the guide vane inner ring, the shaft sleeve mounting edge is arranged on the guide vane inner support, the shaft sleeve mounting edge bolt holes are arranged on the end surface of the shaft sleeve mounting edge in a circumferential direction, the shaft sleeve mounting edge bolt holes are provided in plurality and are all axial holes, and the shaft sleeve mounting edge is fixedly connected with the turbine shaft sleeve through bolts in the shaft sleeve mounting edge bolt holes.

[0005] The front mounting edge, the flame tube exhaust guide pipe, the guide vane outer ring and the turbine rotor casing are integrally formed.

[0006] Further, a plurality of front mounting edge bolt holes are arranged on the front mounting edge in a circumferential direction, and the front mounting edge bolt holes are all radial holes.

[0007] Further, a plurality of casing reinforcing ribs are arranged on the guide vane outer ring and the turbine rotor casing.

[0008] Further, an evaporation pipe inlet is further arranged on the flame tube exhaust guide pipe.

[0009] Further, the guide vane blade is perpendicular to the tangent line at the connection point of the guide vane outer ring and the guide vane inner ring.

[0010] Further, the guide vane inner ring is gradually tapered downward into a cylindrical shaft hole.

[0011] The small axial turbine guide vane and casing integrated modeling method is based on the small axial turbine guide vane and casing integrated structure, and comprises the following steps:

[0012] S1, collecting design parameters required for the integrated casing;

[0013] S2, determining the size parameters of the flame tube exhaust guide pipe based on the parameters in S1;

[0014] S3, determining the size parameters of the guide vane based on the parameters in S1;

[0015] S4, determining the size parameters of the guide vane inner support based on the parameters in S1;

[0016] S5, determining size parameters of the turbine rotor casing section based on the parameters in S1.

[0017] Further, in S1, the following steps are included,

[0018] S11, collecting size parameters of the combustion chamber flame tube afterburning area;

[0019] S12, collecting size and position parameters of the evaporation pipe;

[0020] S13, collecting size parameters of the turbine shaft shaft sleeve;

[0021] S14, collecting size parameters of the turbine shaft shaft sleeve guider mounting end;

[0022] S15, collecting size parameters of the turbine shaft;

[0023] S16, collecting flame tube outlet gas parameters, and calculating the optimal size of the turbine passage according to aerodynamic calculation;

[0024] In S2, the following steps are included,

[0025] S21, determining the outer diameter of the front mounting edge of the flame tube exhaust guide pipe;

[0026] S22, determining the inner and outer diameters of the large circle end of the conical surface of the flame tube exhaust guide pipe;

[0027] S23, determining the contraction shape of the flame tube exhaust guide pipe;

[0028] S24, determining the size and position parameters of the evaporation pipe inlet on the flame tube exhaust guide pipe;

[0029] In S3, the following steps are included,

[0030] S31, determining the inner and outer diameters of the guider outer ring;

[0031] S32, determining the size parameters of the casing reinforcing ribs on the guider outer ring;

[0032] S33, determining the aerodynamic parameters of the guider vane and the surface shape and axial length of the guider inner ring;

[0033] S34, determining the wall thickness of the guider inner ring;

[0034] In S4, the following steps are included,

[0035] S41, determining the inner support ring angle, wall thickness, and axial length of the guider inner support;

[0036] S42, determining the diameter of the cylindrical shaft hole on the guider inner support;

[0037] S43, determine the maximum diameter of the support sleeve installation edge of the guide and the diameter of the internal through hole;

[0038] In S5, the following steps are included,

[0039] S51, determine the inner and outer diameters of the turbine rotor casing segment;

[0040] S52, determine the axial length of the turbine rotor casing segment;

[0041] S53, determine the size parameters of the casing reinforcing ribs on the turbine rotor casing segment.

[0042] A storage medium, the storage medium stores a computer program, the computer program is executed by the processor to realize the above-mentioned small axial flow turbine guide and casing integrated modeling method.

[0043] A computer device, comprising: memory, processor and storage on the memory and can be run on the processor of the computer program, the processor executes the program, to realize the above-mentioned small axial flow turbine guide and casing integrated modeling method.

[0044] The beneficial effects of the application: the small axial flow turbine guide and casing integrated structure and its modeling method of the application, aiming at the problems of high requirement for equipment and environment and the welding place prone to crack in the welding connection of turbine guide and flame tube exhaust guide pipe and turbine shaft sleeve in the prior art, the integrated modeling method of the application avoids these welding problems, improves the reliability and stability of the connection. At the same time, aiming at the problem that the bending treatment of the inner hole end of the guide causes stress concentration and easy damage, the application redesigns the connection mode, the integrated structure and the modeling method solve the stress concentration phenomenon caused by the reserved welding surface, improve the service life and reliability of the component. In addition, the application can integrate the small axial flow turbine guide and casing, meet the integrated design requirements, and is beneficial to the optimization and performance improvement of the overall structure of the aero-engine. BRIEF DESCRIPTION OF DRAWINGS

[0045] Figure 1 It is a three-dimensional schematic view of the small axial flow turbine guide and casing integrated structure of the application;

[0046] Figure 2 It is a flowchart of the small axial flow turbine guide and casing integrated modeling method of the application;

[0047] Figure 3 It is a flowchart of S1 in the small axial flow turbine guide and casing integrated modeling method of the application;

[0048] Figure 4It is three-dimensional schematic view of flame tube exhaust guide pipe in small axial flow turbine guide vane and casing integrated structure of the application;

[0049] Figure 5 It is flow chart of S2 in small axial flow turbine guide vane and casing integrated modeling method of the application;

[0050] Figure 6 It is three-dimensional schematic view of turbine guide vane and guide vane inner support in small axial flow turbine guide vane and casing integrated structure of the application;

[0051] Figure 7 It is flow chart of S3 in small axial flow turbine guide vane and casing integrated modeling method of the application;

[0052] Figure 8 It is flow chart of S4 in small axial flow turbine guide vane and casing integrated modeling method of the application;

[0053] Figure 9 It is three-dimensional schematic view of turbine rotor casing section in small axial flow turbine guide vane and casing integrated structure of the application;

[0054] Figure 10 It is flow chart of S5 in small axial flow turbine guide vane and casing integrated modeling method of the application.

[0055] Wherein, 1 is front mounting edge, 2 is flame tube exhaust guide pipe, 3 is guide vane outer ring, 4 is turbine rotor casing, 5 is casing reinforcing rib, 6 is guide vane blade, 7 is guide vane inner ring, 8 is guide vane inner support, 9 is shaft sleeve mounting edge, 10 is cylindrical shaft hole, 11 is evaporation pipe inlet, 12 is front mounting edge bolt hole, 13 is shaft sleeve mounting edge bolt hole. DETAILED DESCRIPTION

[0056] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the application.

[0057] Reference Figure 1 - Figure 10As shown, a small axial turbine guide vane and casing integrated structure, the small axial turbine guide vane and casing integrated structure comprises: a front mounting edge 1, a flame tube exhaust guide pipe 2, a guide vane outer ring 3, a turbine rotor casing 4, a guide vane blade 6, a guide vane inner ring 7, a guide vane inner support 8, a shaft sleeve mounting edge 9 and a shaft sleeve mounting edge bolt hole 13, the front mounting edge 1 is connected with the flame tube exhaust guide pipe 2 in a stepped manner, the flame tube exhaust guide pipe 2 and the guide vane outer ring 3 are connected in a stepped manner, the guide vane outer ring 3 is connected with the turbine rotor casing 4, the guide vane outer ring 3 is connected with the guide vane blade 6, the guide vane blade 6 is connected with the outer circumferential surface of the guide vane inner ring 7, the guide vane inner support 8 is connected with the inner circumferential surface of the guide vane inner ring 7, the shaft sleeve mounting edge 9 is arranged on the guide vane inner support 8, a plurality of shaft sleeve mounting edge bolt holes 13 are arranged on the end surface of the shaft sleeve mounting edge 9 in a circumferential direction, the shaft sleeve mounting edge bolt holes 13 are axially opened, and the shaft sleeve mounting edge 9 is fixedly connected with the turbine shaft sleeve through bolts in the shaft sleeve mounting edge bolt holes 13.

[0058] The front mounting edge 1, the flame tube exhaust guide pipe 2, the guide vane outer ring 3 and the turbine rotor casing 4 are integrally formed.

[0059] Specifically, in view of the problems of high requirements for welding equipment and environment, cracks at the welding position and stress concentration caused by the bending treatment of the inner hole end of the guide vane in the existing small turbine engine, the present application provides a small axial turbine guide vane and casing integrated structure. In the structure, the front mounting edge 1, the flame tube exhaust guide pipe 2, the guide vane outer ring 3 and the turbine rotor casing 4 are integrally formed, and other components are connected by a reasonable connection method, which avoids the problems caused by welding and improves the connection reliability and stability. At the same time, the stress concentration phenomenon caused by the reserved welding surface is solved, the service life and reliability of the components are improved, the integrated design requirements of the small axial turbine guide vane and casing are met, which is beneficial to the optimization and performance improvement of the overall structure of the aero-engine.

[0060] Further, a plurality of front mounting edge bolt holes 12 are arranged on the front mounting edge 1 in a circumferential direction, and the front mounting edge bolt holes 12 are radially opened.

[0061] Specifically, the present application aims at the problems of high requirements for welding equipment and environment, cracks at the welding position, and stress concentration caused by bending processing of the inner hole end of the guide vane, which leads to early damage, in the welding connection of the turbine guide vane and the turbine shaft sleeve in the existing small turbine engine, and proposes a small axial turbine guide vane and casing integrated structure. In the structure, the front mounting edge 1, the flame tube exhaust guide pipe 2, the guide vane outer ring 3 and the turbine rotor casing 4 are integrally formed, the front mounting edge 1 is provided with a front mounting edge bolt hole 12 with a radial opening in the circumferential direction, and through a reasonable connection mode, the problems caused by welding are avoided, and the connection reliability and stability are improved. At the same time, the stress concentration phenomenon caused by the reserved welding surface is solved, the service life and reliability of the component are improved, and the integrated design requirements of the small axial turbine guide vane and the casing are met.

[0062] Further, the casing stiffener 5 is arranged on the guide vane outer ring 3 and the turbine rotor casing 4, and the casing stiffener 5 is provided with a plurality of.

[0063] Specifically, in the structure of the present application, a plurality of casing stiffeners 5 are arranged on the guide vane outer ring 3 and the turbine rotor casing 4, which can enhance the structural strength of the connection part of the guide vane outer ring 3 and the turbine rotor casing 4, improve the stability and reliability of the overall structure, effectively reduce the risk of deformation or damage that may occur due to stress in the working process, thereby prolonging the service life of the component, ensuring the normal operation of the aero-engine, and improving its performance.

[0064] Further, the flame tube exhaust guide pipe 2 is also provided with an evaporation pipe inlet 11.

[0065] Specifically, the evaporation pipe inlet 11 is arranged on the flame tube exhaust guide pipe 2, so that the fuel enters the combustion chamber through the evaporation pipe and is fully mixed and burned with high-pressure air to do work on the subsequent power components.

[0066] Further, the guide vane 6 is perpendicular to the tangent line at the connection point of the guide vane outer ring 3 and the guide vane inner ring 7.

[0067] Specifically, the guide vane 6 is perpendicular to the tangent line at the connection point of the guide vane outer ring 3 and the guide vane inner ring 7, which can ensure that the gas flows more smoothly when flowing through the guide vane, reduce air resistance, improve the guiding effect and efficiency of the guide vane, and thus optimize the performance of the entire turbine system.

[0068] Further, the guide vane inner ring 7 is gradually tapered downward into a cylindrical shaft hole 10.

[0069] Specifically, the inner ring 7 of the guide gradually converges downward into a cylindrical shaft hole 10, which helps to guide the airflow more smoothly, reduces airflow turbulence, and improves the flow efficiency of the gas; at the same time, it can better cooperate with related components, and enhance the compactness and stability of the overall structure.

[0070] Referring to Figure 2 As shown in the drawings, a small axial turbine guide and casing integrated modeling method is based on the above-mentioned small axial turbine guide and casing integrated structure, and the small axial turbine guide and casing integrated modeling method comprises the following steps,

[0071] S1, collecting design parameters required for the integrated casing;

[0072] S2, determining the size parameters of the flame tube exhaust guide 2 based on the parameters of S1;

[0073] S3, determining the size parameters of the guide based on the parameters of S1;

[0074] S4, determining the size parameters of the inner support 8 of the guide based on the parameters of S1;

[0075] S5, determining the size parameters of the turbine rotor casing section 4 based on the parameters of S1.

[0076] Specifically, the small axial turbine guide and casing integrated modeling method can realize accurate design and manufacturing by collecting design parameters and sequentially determining the size parameters of each component, ensuring good matching and cooperative work between each component. This method improves the scientificity and rationality of the design, which is beneficial to optimize the overall structure, reduce the performance degradation caused by size mismatching and other problems, and improve the reliability and performance of the aero-engine. At the same time, it also provides a standardized process for production and manufacturing, and improves the production efficiency.

[0077] Further, in S1, in the present embodiment, as shown in Figure 3 , the design parameters required for the integrated casing are collected, including the following steps,

[0078] S11, collecting the size parameters of the combustion chamber flame tube afterburning area.

[0079] In some embodiments, the size parameters of the combustion chamber flame tube afterburning area are collected, considering the assembly connection of the flame tube afterburning area and the exhaust guide front mounting edge. The collected parameters are the inner and outer diameters of the flame tube afterburning area and the inner diameter of the outlet end mounting edge.

[0080] S12, collecting the size and position parameters of the evaporation pipe.

[0081] In some embodiments, the size and position parameters of the evaporation tube are collected, and the size parameters collected are the size and position parameters of the evaporation tube, including: the outer diameter of the evaporation tube, the number, and the diameter of the circumferential circle where the axis is located.

[0082] S13, collecting the size parameters of the turbine shaft sleeve.

[0083] In some embodiments, the size parameters of the turbine shaft sleeve are collected, and the parameters collected are the outer diameters of different shaft sections of the turbine shaft sleeve, considering that the inner ring of the guider is rigidly connected to the sleeve to closely fit the combustion chamber.

[0084] S14, collecting the size parameters of the turbine shaft sleeve guider mounting end.

[0085] In some embodiments, the size parameters of the turbine shaft sleeve guider mounting end are collected, specifically including: the inner and outer diameters of the sleeve mounting end.

[0086] S15, collecting the size parameters of the turbine shaft.

[0087] In some embodiments, the size parameters of the turbine shaft are collected, specifically including: the outer diameter of the turbine shaft.

[0088] S16, collecting the flame tube outlet gas parameters, and calculating the optimal size of the turbine passage according to aerodynamic calculation.

[0089] Specifically, by collecting the relevant size parameters of the combustion chamber flame tube afterburning area, the combustion gas parameters, the turbine shaft sleeve and mounting end size parameters, and the turbine shaft and flame tube outlet gas parameters, a comprehensive and accurate data basis is provided for the accurate determination of the size of each component. Considering various assembly connection relationships and working characteristic environmental factors, it is helpful to achieve perfect adaptation between each component, improve the rationality and reliability of the overall structure.

[0090] Further, S2, determining the size parameters of the flame tube exhaust guide pipe 2 based on the parameters of S1.

[0091] In some embodiments, as shown in Figure 4 , 5 the size parameters of the flame tube exhaust guide pipe 2 are determined, including:

[0092] S21, determining the outer diameter of the front mounting edge 1 of the flame tube exhaust guide pipe 2.

[0093] In some embodiments, the inner diameter of the mounting edge of the flame tube afterburning area outlet end is read, considering that the two are interference fit, and the outer diameter r1 of the front mounting edge 1 of the flame tube exhaust guide pipe 2 is determined accordingly.

[0094] S22, determine the inner and outer diameters of the large circle end of the conical surface of the flame tube exhaust guide 2.

[0095] In some embodiments, the inner and outer diameters of the flame tube afterburning zone are read, and the smooth continuity of the inner and outer walls of the flame tube is considered, based on which the inner diameter r2 and the outer diameter r3 of the large circle end of the conical surface of the flame tube exhaust guide 2 are determined.

[0096] S23, determine the contraction shape of the flame tube exhaust guide 2.

[0097] In some embodiments, the flow velocity of the gas after complete combustion in the flame tube afterburning zone is read, and the reasonable range of the outlet velocity of the combustion gas is combined to determine the contraction shape of the flame tube exhaust guide 2, which can be determined by determining the inner diameter r4 and the outer diameter r5 of the small circle end of the conical surface of the exhaust guide 2 and the height l1 of the conical body.

[0098] S24, determine the size and position parameters of the evaporation tube inlet 11 on the flame tube exhaust guide 2.

[0099] In some embodiments, the outer diameter, number, and diameter of the circumferential circle of the evaporation tube axis are read to determine the size and position parameters of the evaporation tube inlet 11 on the flame tube exhaust guide 2.

[0100] S3, determine the size parameters of the director based on the parameters of S1.

[0101] In some embodiments, as shown in Figure 6 , 7 , the size parameters of the director are determined, including:

[0102] S31, determine the inner and outer diameters of the outer ring 3 of the director.

[0103] In some embodiments, the inner diameter r4 and the outer diameter r5 of the small circle end of the flame tube exhaust guide 2 are read, and the smooth continuity of the inner and outer walls of the integrated casing is considered to determine the inner diameter r6 and the outer diameter r7 of the outer ring 3 of the director.

[0104] S32, determine the size parameters of the casing reinforcing ribs 5 on the outer ring 3 of the director.

[0105] In some embodiments, the ribs on the outer ring of the director are associated with the size of the casing wall thickness to ensure structural stability, and the axial length of the ribs is determined to be 2.7 times the wall thickness (r7-r6), and the radial thickness is 2.1 times the wall thickness (r7-r6).

[0106] S33, determine the aerodynamic parameters of the director blades 6 and the curved surface shape and axial length of the inner ring 7 of the director.

[0107] In some embodiments, the optimal size and channel map of the turbine channel are read, and the aerodynamic parameters of the turbine guide vane 6 and the surface shape and axial length l2 of the inner ring 7 of the guide are determined.

[0108] S34, the wall thickness of the inner ring 7 of the guide is determined.

[0109] In some embodiments, the wall thickness t1 of the inner ring 7 of the guide is determined in combination with the strength calculation result.

[0110] S4, the size parameters of the inner support of the guide are determined based on the parameters of S1;

[0111] In some embodiments, as shown in Figure 6 , 8 , the size parameters of the inner support of the guide are determined, including:

[0112] S41, the inner support ring angle, wall thickness, and axial length of the inner support 8 of the guide are determined.

[0113] In some embodiments, the size parameters of the inner ring 7 of the guide are read, and the inner support ring angle a, wall thickness t2, and axial length l3 of the inner support 8 of the guide are determined in combination with the strength calculation result.

[0114] S42, the diameter of the cylindrical shaft hole 10 on the inner support 8 of the guide is determined.

[0115] The outer diameter of the corresponding shaft section of the turbine shaft sleeve is read, and the diameter r8 of the cylindrical shaft hole 10 on the inner support 8 of the guide is determined.

[0116] S43, the maximum diameter of the shaft sleeve mounting edge 9 on the inner support 8 of the guide and the diameter of the internal through hole are determined.

[0117] In some embodiments, the inner and outer diameters of the guide mounting end of the turbine shaft sleeve and the outer diameter of the turbine shaft are read, and the maximum diameter r9 of the shaft sleeve mounting edge 10 on the inner support 8 of the guide and the diameter r 10 .

[0118] S5, the size parameters of the turbine rotor casing section are determined based on the parameters of S1.

[0119] In some embodiments, as shown in Figure 9 , 10 , the size parameters of the turbine rotor casing section are determined, including:

[0120] S51, the inner and outer diameters of the turbine rotor casing section 4 are determined.

[0121] In some embodiments, the size parameters of the turbine guide outer ring 3 are read, and the coherence and smoothness of the inner and outer walls of the integrated casing are considered to determine the inner diameter r 11、 and the outer diameter r12 .

[0122] S52, determine the axial length of the turbine rotor casing section 4.

[0123] In some embodiments, the axial length of the turbine rotor is read, and the axial length l4 of the turbine rotor casing section 4 is determined considering that the casing needs to completely wrap the turbine rotor part.

[0124] S53, determine the size parameters of the reinforcing ribs 5 on the turbine rotor casing section 4.

[0125] In some embodiments, the ribs on the turbine casing need to match the engine shell, and the size parameters of the reinforcing ribs 5 on the turbine rotor casing section 4 are determined considering that they cannot interfere with the engine shell.

[0126] Specifically, the present application determines the size parameters of each component based on the parameters of S1, and by reasonably determining the size parameters of the flame tube exhaust guide pipe, such as determining the outer diameter of the front mounting edge considering the cooperation with the flame tube afterburning area, and determining the size of the circular end inner and outer diameter of the conical surface and the contraction shape according to the afterburning area, the good adaptation of the exhaust guide pipe with other components and the optimization of gas flow can be realized. When determining the size parameters of the guide vane, the inner and outer diameters of the outer ring are determined considering the continuity with the exhaust guide pipe, the size of the reinforcing ribs is determined combined with strength calculation, and the aerodynamic parameters of the blade and the related parameters of the inner ring are determined according to the turbine passage, which ensures the performance of the guide vane. When determining the size parameters of the guide vane inner support and the turbine rotor casing section, various factors are also considered comprehensively to ensure the close cooperation and reasonable structure of each component. This size determination method based on parameters improves the rationality and reliability of the overall structure, optimizes the cooperative work between each component of the aero-engine, and improves the performance of the engine.

[0127] A storage medium having a computer program stored thereon, wherein the computer program is executed by a processor to implement the small axial flow turbine guide vane and casing integrated modeling method.

[0128] Specifically, the computer program stored on the storage medium has important beneficial effects. When the computer program is executed by the processor, it can implement the small axial flow turbine guide vane and casing integrated modeling method, which provides an efficient and accurate implementation approach for the design and manufacture of aero-engines. In this way, the accurate implementation of the integrated modeling method can be ensured, the design efficiency can be improved, the human error can be reduced, the cooperation between components can be optimized, and the overall performance and reliability of the aero-engine can be improved.

[0129] The computer device comprises a memory, a processor and a computer program stored on the memory and executable on the processor, and the processor executes the program to implement the small axial turbine guide vane and casing integrated modeling method.

[0130] Specifically, the computer device has significant benefits. The memory, processor and related computer program contained therein can implement the small axial turbine guide vane and casing integrated modeling method through the execution of the program by the processor. This not only improves the implementation efficiency and accuracy of the modeling method, reduces the errors that may be caused by manual operation, but also optimizes the design and cooperation of components, improves the overall performance and reliability of the aero-engine, and provides strong technical support for the manufacture of the aero-engine.

[0131] The small axial turbine guide vane and casing integrated structure and the modeling method thereof of the present application avoid these welding problems by using the integrated modeling method, improve the reliability and stability of the connection. At the same time, in view of the problem that the bending treatment of the inner hole end of the guide vane causes stress concentration and is prone to damage in advance, the present application redesigns the connection method, and the integrated structure and the modeling method solve the stress concentration phenomenon caused by the reserved welding surface, and improve the service life and reliability of the components. In addition, the present application can integrate the small axial turbine guide vane and casing, meet the integrated design requirements, and is beneficial to the optimization and performance improvement of the overall structure of the aero-engine.

[0132] It should be noted that, in this article, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between the entities or operations. Moreover, the terms "include", "contain" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or equipment. In addition, "front", "back", "left", "right", "up", "down" in this article are referred to the placement state shown in the drawings.

[0133] It should be pointed out finally that the above embodiments are only used for illustrating the technical solutions of the present application, but not for limiting the same; and although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features thereof can be replaced equivalently; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A small axial turbine guide integrated with a casing structure, characterized in that, It comprises: The front mounting edge (1), the flame tube exhaust guide pipe (2), the guider outer ring (3), the turbine rotor casing section (4), the guider blade (6), the guider inner ring (7), the guider inner support (8), the shaft sleeve mounting edge (9) and the shaft sleeve mounting edge bolt hole (13), the front mounting edge (1) is connected with the flame tube exhaust guide pipe (2) in a stepped manner, the flame tube exhaust guide pipe (2) and the guider outer ring (3) are connected in a stepped manner, the guider outer ring (3) is connected with the turbine rotor casing section (4), the guider outer ring (3) is connected with the guider blade (6), the guider blade (6) is connected with the outer circumferential surface of the guider inner ring (7), the guider inner support (8) is connected with the inner circumferential surface of the guider inner ring (7), the shaft sleeve mounting edge (9) is arranged on the guider inner support (8), the shaft sleeve mounting edge bolt hole (13) is arranged on the end surface of the shaft sleeve mounting edge (9) in a circumferential direction, the shaft sleeve mounting edge bolt hole (13) is provided with a plurality of axial holes, and the shaft sleeve mounting edge (9) is fixedly connected with the turbine shaft sleeve through the bolts in the shaft sleeve mounting edge bolt hole (13), The front mounting edge (1), the flame tube exhaust guide pipe (2), the guider outer ring (3) and the turbine rotor casing section (4) are integrally formed; The guider outer ring (3) and the turbine rotor casing section (4) are arranged with the casing reinforcing ribs (5), and the casing reinforcing ribs (5) are provided with a plurality of casing reinforcing ribs (5); The flame tube exhaust guide pipe (2) is further provided with the evaporation pipe inlet (11); The guider blade (6) is perpendicular to the tangent line of the connection point of the guider outer ring (3) and the guider inner ring (7).

2. A small-sized axial turbine guide vane and casing integrated structure according to claim 1, characterized in that, The front mounting edge (1) is arranged with the front mounting edge bolt hole (12) in a circumferential direction, and the front mounting edge bolt hole (12) is provided with a plurality of radial holes.

3. A small-sized axial turbine guide vane and casing integrated structure according to claim 1, characterized in that, The guider inner ring (7) is gradually tapered downward into a cylindrical shaft hole (10).

4. A method for forming an integrated casing and guide vane for a small axial turbine, the method comprising: providing a guide vane according to any one of claims 1-3; and forming an integrated casing and guide vane by joining the guide vane to the casing. The small axial flow turbine guider and casing integrated modeling method It comprises the following steps, S1, collecting the design parameters required by the integrated casing; S2, determining the size parameters of the flame tube exhaust guide pipe (2) based on the parameters in S1; S3, determining the size parameters of the guider based on the parameters in S1; S4, determining the size parameters of the guider inner support (8) based on the parameters in S1; S5, determining the size parameters of the turbine rotor casing section (4) based on the parameters in S1; In S1, It comprises the following steps, S11, collecting the size parameters of the combustion chamber flame tube afterburning area; S12, collecting the size and position parameters of the evaporation pipe; S13, collecting the size parameters of the turbine shaft sleeve; S14, collecting the size parameters of the turbine shaft sleeve guider mounting end; S15, collecting the size parameters of the turbine shaft; S16, collecting the flame tube outlet gas parameters, and calculating the optimal size of the turbine passage according to the aerodynamic calculation; In S2, it comprises the following steps, S21, determining the outer diameter of the front mounting edge (1) on the flame tube exhaust guide pipe (2); S22, determining the inner and outer diameters of the large circle end of the conical surface of the flame tube exhaust guide pipe (2); S23, determining the contraction shape of the flame tube exhaust guide pipe (2); S24, determining the size and position parameters of the evaporation tube inlet (11) on the flame tube exhaust guide (2); In S3, the following steps are included, S31, determining the inner and outer diameters of the outer ring (3) of the guide vane; S32, determining the size parameters of the casing stiffening ribs (5) on the outer ring (3) of the guide vane; S33, determining the aerodynamic parameters of the guide vane blade (6) and the curved surface shape and axial length of the inner ring (7) of the guide vane; S34, determining the wall thickness of the inner ring (7) of the guide vane; In S4, The following steps are included, S41, determining the inner support ring angle, wall thickness, and axial length of the inner support (8) of the guide vane; S42, determining the diameter of the cylindrical shaft hole (10) on the inner support (8) of the guide vane; S43, determining the maximum diameter of the shaft sleeve mounting edge (9) and the diameter of the internal through hole on the inner support (8) of the guide vane; In S5, the following steps are included, S51, determining the inner and outer diameters of the turbine rotor casing section (4); S52, determining the axial length of the turbine rotor casing section (4); S53, determining the size parameters of the casing stiffening ribs (5) on the turbine rotor casing section (4).

5. A storage medium having stored thereon a computer program, characterized in that The computer program is executed by a processor to realize the small axial flow turbine guide vane and casing integrated modeling method of claim 4.

6. A computer device, comprising: It includes: a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor executes the program to realize the small axial flow turbine guide vane and casing integrated modeling method of claim 4.

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