Small axial flow turbine guider and casing integrated structure and modeling method thereof

Abstract

The invention relates to a small axial flow turbine guider and cartridge receiver integrated structure and a modeling method thereof, and belongs to the field of aero-engines. The problems that in an existing small turbine engine, due to the fact that a turbine guider, a flame tube exhaust guide pipe and a turbine shaft sleeve are respectively machined and then connected in a welded mode, the requirements for welding equipment and the environment are high, the welding position is prone to cracking under high-temperature stress, and the inner hole end of the guider is prone to damage due to stress concentration caused by bending treatment are solved. The integrated modeling method for the turbine guider and the casing comprises the following steps that design parameters needed by the integrated casing are collected; determining size parameters of a flame tube exhaust duct; determining size parameters of the guider; determining size parameters of the guider inner support; and determining the size parameters of the turbine rotor casing section. According to the method, the small axial flow turbine guider and the casing can be integrally molded, and the requirement for the integrated design of the small axial flow turbine guider and the casing is met.

Description

Technical Field

[0001] The invention relates to a small axial-flow turbine guide and casing integrated structure and a molding method thereof, and belongs to the field of aviation engines. Background Art

[0002] The turbine guide of an aircraft engine is composed of an outer ring, an inner ring and guide blades, and the guide blades are between the inner and outer rings. In a certain existing small turbine engine, the turbine guide, the exhaust duct of the flame tube and the turbine shaft sleeve are connected together by processing and welding. Since it is necessary to ensure that all the post-combustion gases in the combustion chamber pass through the guide and then work outside through the turbine, the connection needs to have good sealing to prevent the post-combustion gases from leaking out. Therefore, sealing welding technology needs to be used during the assembly process. This welding technology has high requirements for welding equipment and environment. During the welding process, it is also necessary to eliminate the thermal stress generated during the heating treatment and control the deformation degree of the parts. Even so, in the harsh working environment of high temperature and stress, some welds are still prone to cracks and other faults first; in this model of small turbine engine, in order to connect the turbine guide and the turbine shaft sleeve together, the inner hole end of the guide is also bent so that it can fit with the sleeve, so as to perform welding operations. Such a design makes the bending part have a large angle, resulting in the undesirable phenomenon of stress concentration, and it is also easy to be damaged in advance. Therefore, a modeling method for the integration of a small axial turbine guide and a casing is proposed. Summary of the invention

[0003] The present invention proposes an integrated structure of a small axial-flow turbine guide and a casing and a molding method thereof, so as to solve the problem that in the existing small turbine engine, the turbine guide is connected to the flame tube exhaust duct and the turbine shaft sleeve by separate processing and then welding, which has high requirements on welding equipment and environment, and some welds are prone to cracks and other faults under high temperature and stress environment; at the same time, in order to connect the sleeve, the inner hole end of the guide is bent to produce a large angle, which leads to stress concentration and easy premature damage.

[0004] A small axial turbine guide and casing integrated structure, the small axial turbine guide and casing integrated structure comprises: a front mounting edge, a flame tube exhaust duct, a guide outer ring, a turbine rotor casing, a guide blade, a guide inner ring, a guide inner support, a sleeve mounting edge and a sleeve mounting edge bolt hole, the front mounting edge is connected to the flame tube exhaust duct in a stepped manner, the flame tube exhaust duct and the guide outer ring are connected in a stepped manner, the guide outer ring is connected to the turbine rotor casing, the guide outer ring is connected to the guide blade, the guide blade is connected to the outer circumferential surface of the guide inner ring, the guide inner support is connected to the inner circumferential surface of the guide inner ring, a sleeve mounting edge is provided on the guide inner support, and sleeve mounting edge bolt holes are circumferentially arranged on the end surface of the sleeve mounting edge, a plurality of sleeve mounting edge bolt holes are provided, all of which are axial openings, and the sleeve mounting edge is fixedly connected to the turbine shaft sleeve by bolts in the sleeve mounting edge bolt holes.

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

[0006] Furthermore, front mounting side bolt holes are circumferentially arranged on the front mounting side, and there are a plurality of front mounting side bolt holes, all of which are radial openings.

[0007] Furthermore, casing reinforcement ribs are arranged on the guide outer ring and the turbine rotor casing, and a plurality of casing reinforcement ribs are provided.

[0008] Furthermore, an evaporation tube inlet is also provided on the flame tube exhaust duct.

[0009] Furthermore, the guide vane is perpendicular to a tangent line at a connection point between the guide outer ring and the guide inner ring.

[0010] Furthermore, the inner ring of the guide gradually converges downward to form a cylindrical shaft hole.

[0011] A method for integrating a small axial-flow turbine guide and a casing is provided. Based on the above-mentioned integrated structure of a small axial-flow turbine guide and a casing, the method for integrating a small axial-flow turbine guide and a casing comprises the following steps:

[0012] S1. Collect the design parameters required for the integrated casing;

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

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

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

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

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

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

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

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

[0021] S14, collecting the dimension parameters of the installation end of the turbine shaft sleeve guide;

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

[0023] S16, collecting the gas parameters at the flame tube outlet, and calculating the optimal size of the turbine channel according to aerodynamics;

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

[0025] S21. Determine the outer diameter of the front mounting edge of the flame tube exhaust duct;

[0026] S22, determine the inner and outer diameters of the large circular end of the conical surface of the flame tube exhaust duct;

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

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

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

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

[0031] S32, determining the size parameters of the casing reinforcement rib on the outer ring of the guide;

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

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

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

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

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

[0037] S43, determining the maximum diameter of the upper sleeve mounting edge of the guide inner support and the diameter of the inner through hole;

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

[0039] S51, determining the inner and outer diameters of the turbine rotor casing section;

[0040] S52, determining the axial length of the turbine rotor casing section;

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

[0042] A storage medium stores a computer program, which, when executed by a processor, implements the above-mentioned method for integrating a small axial-flow turbine guide and a casing.

[0043] A computer device comprises: a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the above-mentioned method for integrating a small axial-flow turbine guide and a casing.

[0044] Beneficial effects of the present invention: The present invention provides an integrated structure of a small axial-flow turbine guide and casing and a molding method thereof. Aiming at the problems of high requirements on equipment and environment and easy cracking at the welding joints of the turbine guide and the flame tube exhaust duct and the turbine shaft sleeve in the prior art, the present invention adopts an integrated molding method to avoid these welding problems and 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 in the prior art leads to stress concentration and easy premature damage, the present invention redesigns the connection method. The integrated structure and molding 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 invention can integrate the small axial-flow turbine guide and casing, meet the requirements of integrated design, and is conducive to the optimization of the overall structure and performance improvement of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 A three-dimensional schematic diagram of an integrated structure of a small axial-flow turbine guide and a casing according to the present invention;

[0046] Figure 2 It is a schematic flow chart of a method for integrating a small axial-flow turbine guide and casing according to the present invention;

[0047] Figure 3 It is a schematic flow chart of S1 in a method for integrating a small axial-flow turbine guide and casing of the present invention;

[0048] Figure 4It is a three-dimensional schematic diagram of a flame tube exhaust duct in a small axial flow turbine guide and casing integrated structure of the present invention;

[0049] Figure 5 It is a schematic diagram of the process of S2 in a method for integrating a small axial-flow turbine guide and casing of the present invention;

[0050] Figure 6 It is a three-dimensional schematic diagram of a turbine guide and a guide inner support in a small axial-flow turbine guide and casing integrated structure of the present invention;

[0051] Figure 7 It is a schematic flow chart of S3 in a method for integrating a small axial-flow turbine guide and casing of the present invention;

[0052] Figure 8 It is a schematic diagram of the process of S4 in a method for integrating a small axial-flow turbine guide and casing of the present invention;

[0053] Fig. 9 It is a three-dimensional schematic diagram of a turbine rotor casing section in a small axial-flow turbine guide and casing integrated structure of the present invention;

[0054] Fig.10 It is a schematic diagram of the process of S5 in a method for integrating a small axial-flow turbine guide and casing of the present invention.

[0055] Among them, 1 is the front mounting edge, 2 is the flame tube exhaust duct, 3 is the guide outer ring, 4 is the turbine rotor casing, 5 is the casing reinforcement rib, 6 is the guide blade, 7 is the guide inner ring, 8 is the guide inner support, 9 is the sleeve mounting edge, 10 is the cylindrical shaft hole, 11 is the evaporator tube inlet, 12 is the front mounting edge bolt hole, and 13 is the sleeve mounting edge bolt hole. DETAILED DESCRIPTION

[0056] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0057] Reference Figure 1 - Fig.10As shown, a small axial turbine guide and casing integrated structure, the small axial turbine guide and casing integrated structure comprises: a front mounting edge 1, a flame tube exhaust duct 2, a guide outer ring 3, a turbine rotor casing 4, a guide vane 6, a guide inner ring 7, a guide inner support 8, a sleeve mounting edge 9 and a sleeve mounting edge bolt hole 13, the front mounting edge 1 is connected to the flame tube exhaust duct 2 in a stepped manner, the flame tube exhaust duct 2 and the guide outer ring 3 are connected in a stepped manner, and the guide outer ring 3 is connected to the turbine rotor casing 4, the guide outer ring 3 is connected to the guide blades 6, the guide blades 6 are connected to the outer circumference of the guide inner ring 7, the guide inner support 8 is connected to the inner circumference of the guide inner ring 7, a sleeve mounting edge 9 is provided on the guide inner support 8, and sleeve mounting edge bolt holes 13 are circumferentially arranged on the end surface of the sleeve mounting edge 9, and the sleeve mounting edge bolt holes 13 are provided in plurality, all of which are axial openings, and the sleeve mounting edge 9 is fixedly connected to the turbine shaft sleeve through bolts in the sleeve mounting edge bolt holes 13.

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

[0059] Specifically, the present invention proposes an integrated structure of a small axial-flow turbine guide and casing to solve the problems of high requirements for welding equipment and environment, easy cracking at the welding joints, and stress concentration and premature damage caused by bending of the inner hole end of the guide in the existing small turbine engines. In the structure, the front mounting edge 1, the flame tube exhaust duct 2, the guide outer ring 3 and the turbine rotor casing 4 are integrally formed, and other components are connected in a reasonable manner to avoid problems caused by welding and improve 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, and the integrated design requirements of the small axial-flow turbine guide and casing are met, which is beneficial to the optimization of the overall structure and performance improvement of the aircraft engine.

[0060] Furthermore, front mounting side bolt holes 12 are circumferentially arranged on the front mounting side 1, and there are a plurality of front mounting side bolt holes 12, all of which are radial openings.

[0061] Specifically, the present invention proposes an integrated structure of a small axial flow turbine guide and casing to solve the problems of high requirements for welding equipment and environment, easy cracking at the welding joint, and stress concentration and premature damage caused by bending treatment of the inner hole end of the guide in the existing small turbine engine. In this structure, the front mounting edge 1, the flame tube exhaust duct 2, the guide outer ring 3 and the turbine rotor casing 4 are integrally formed, and the front mounting edge 1 is circumferentially arranged with radially opened front mounting edge bolt holes 12. Through a reasonable connection method, 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 components are improved, and the integrated design requirements of the small axial flow turbine guide and casing are met.

[0062] Furthermore, casing reinforcement ribs 5 are arranged on the guide outer ring 3 and the turbine rotor casing 4, and a plurality of casing reinforcement ribs 5 are provided.

[0063] Specifically, in the structure of the present invention, a plurality of casing reinforcement ribs 5 are arranged on the guide outer ring 3 and the turbine rotor casing 4, which can enhance the structural strength of the connection portion between the guide outer ring 3 and the turbine rotor casing 4, improve the stability and reliability of the overall structure, and effectively reduce the risk of deformation or damage due to force during operation, thereby extending the service life of the components, ensuring the normal operation of the aircraft engine, and improving its performance.

[0064] Furthermore, an evaporation tube inlet 11 is also provided on the flame tube exhaust duct 2 .

[0065] Specifically, an evaporator inlet 11 is provided on the flame tube exhaust duct 2, so that the fuel enters the combustion chamber through the evaporator, is fully mixed with the high-pressure air and combusted, and performs work on subsequent power components.

[0066] Furthermore, the guide vanes 6 are perpendicular to the tangent line at the connection points with the guide outer ring 3 and the guide inner ring 7 .

[0067] Specifically, the guide vanes 6 are perpendicular to the tangent of the connection points between the guide outer ring 3 and the guide inner ring 7, which can ensure that the gas flows more smoothly when passing through the guide, reduce airflow resistance, improve the guiding effect and efficiency of the guide on the airflow, and thus optimize the performance of the entire turbine system.

[0068] Furthermore, the guide inner ring 7 gradually converges downward to form 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 to pass more smoothly, reduce airflow turbulence, and improve the flow efficiency of the gas; at the same time, it can better cooperate with related components to enhance the compactness and stability of the overall structure.

[0070] Reference Figure 2 As shown, a method for integrating a small axial-flow turbine guide and a casing is provided. Based on the above-mentioned integrated structure of a small axial-flow turbine guide and a casing, the method for integrating a small axial-flow turbine guide and a casing comprises the following steps:

[0071] S1. Collect the design parameters required for the integrated casing;

[0072] S2, determining the size parameters of the flame tube exhaust duct 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 guide inner support 8 based on the parameters of S1;

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

[0076] Specifically, the integrated modeling method of the small axial turbine guide and casing can achieve accurate design and manufacturing by collecting design parameters and determining the size parameters of each component in sequence, ensuring good matching and coordination between the components. This method improves the scientificity and rationality of the design, is conducive to optimizing the overall structure, reducing performance degradation caused by size mismatch and other problems, and improving the reliability and performance of the aircraft engine. At the same time, it also provides a standardized process for production and manufacturing, and improves production efficiency.

[0077] Further, in S1, in this embodiment, if Figure 3 As shown, the design parameters required for the integrated casing are collected, including the following steps:

[0078] S11. Collect the dimensional parameters of the combustion chamber flame tube supplementary combustion zone.

[0079] In some embodiments, the dimensional parameters of the flame tube reburning zone of the combustion chamber are collected. Considering the assembly connection between the flame tube reburning zone and the front mounting edge of the exhaust duct, the collected parameters are the inner and outer diameters of the flame tube reburning zone and the inner diameter of the mounting edge at the outlet end.

[0080] S12. Collect the size and position parameters of the evaporation tube.

[0081] In some embodiments, the size and position parameters of the evaporator tube are collected, and considering that an assembly hole for the evaporator tube needs to be reserved on the wall of the flame tube exhaust duct 2, the collected size parameters are the size and position parameters of the evaporator tube, including: the outer diameter of the evaporator tube, the number, and the diameter of the circumferential circle where the axis is located.

[0082] S13. Collect the dimension parameters of the turbine shaft sleeve.

[0083] In some embodiments, the dimension parameters of the turbine shaft sleeve are collected, and considering that the inner ring of the guide and the sleeve are rigidly connected and tightly fit to form a combustion chamber, the collected parameters are the outer diameters of different shaft sections of the turbine shaft sleeve.

[0084] S14, collecting the dimension parameters of the turbine shaft sleeve guide mounting end.

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

[0086] S15. Collect the dimension 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. Collect the gas parameters at the flame tube outlet and calculate the optimal size of the turbine channel based on aerodynamics.

[0089] Specifically, by collecting detailed dimensional parameters of the combustion chamber flame tube reburning area, combustion gas parameters, turbine shaft sleeve and mounting end dimensional parameters, and turbine shaft and flame tube outlet gas parameters, a comprehensive and accurate data basis is provided for the accurate determination of the subsequent dimensions of each component. Taking into account a variety of assembly connection relationships and working characteristic environmental factors, it helps to achieve perfect adaptation between the various components and improve the rationality and reliability of the overall structure.

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

[0091] In some embodiments, Figure 4 , 5 As shown, the size parameters of the flame tube exhaust duct 2 are determined, including:

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

[0093] In some embodiments, the inner diameter of the mounting edge at the outlet of the flame tube afterburning zone is read, and the outer diameter r of the front mounting edge 1 on the flame tube exhaust duct 2 is determined based on the interference fit between the two. 1 .

[0094] S22. Determine the inner and outer diameters of the large circular end of the conical surface of the flame tube exhaust duct 2.

[0095] In some embodiments, the inner and outer diameters of the flame tube afterburning zone are read, and the inner and outer walls of the flame tube are smooth and continuous, and the inner diameter r of the large circular end of the conical surface on the flame tube exhaust duct 2 is determined accordingly. 2 、Outer diameter r 3 .

[0096] S23, determining the contraction shape of the flame tube exhaust duct 2.

[0097] In some embodiments, the flow velocity of the gas after complete combustion in the flame tube afterburning zone is read, and the contraction shape of the flame tube exhaust duct 2 is determined in combination with the reasonable range of the combustion gas outlet velocity. The contraction shape can be determined by determining the inner diameter r of the conical surface of the exhaust duct 2. 4 、Outer diameter r 5 , cone height l 1 Sure.

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

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

[0100] S3. Determine the size parameters of the guide based on the parameters of S1.

[0101] In some embodiments, Figure 6 , 7 As shown, determine the size parameters of the guide, including:

[0102] S31, determining the inner and outer diameters of the guide outer ring 3.

[0103] In some embodiments, the inner diameter r of the small round end of the flame tube exhaust duct 2 is read 4 、Outer diameter r 5 Considering the smoothness of the inner and outer walls of the integrated casing, the inner diameter r of the guide outer ring 3 is determined 6 、Outer diameter r 7 .

[0104] S32, determining the size parameters of the casing reinforcement rib 5 on the guide outer ring 3.

[0105] In some embodiments, the ribs on the outer ring of the guide are related to the thickness of the casing wall to ensure structural stability, and the axial length of the ribs is determined to be the wall thickness (r 7 -r 6 ) is 2.7 times the wall thickness (r7 -r 6 ) is 2.1 times.

[0106] S33. Determine the aerodynamic parameters of the guide vane 6 and the curved surface shape and axial length of the guide inner ring 7.

[0107] In some embodiments, the optimal size and channel diagram of the turbine channel are read to determine the aerodynamic parameters of the turbine guide vane 6 and the curved surface shape and axial length l of the guide inner ring 7. 2 .

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

[0109] In some embodiments, the wall thickness t of the inner ring 7 of the guide is determined by combining the strength calculation results. 1 .

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

[0111] In some embodiments, Figure 6 , 8 As shown, determine the size parameters of the guide internal support, including:

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

[0113] In some embodiments, the dimension parameters of the guide inner ring 7 are read and the inner support ring angle α and the wall thickness t of the guide inner support 8 are determined in combination with the strength calculation results. 2 , axial length l 3 .

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

[0115] Read the outer diameter of the corresponding shaft section of the turbine shaft sleeve to determine the diameter r of the cylindrical shaft hole 10 on the inner support 8 of the guide 8 .

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

[0117] In some embodiments, the inner and outer diameters of the turbine shaft sleeve guide mounting end and the turbine shaft outer diameter are read to determine the maximum diameter r of the sleeve mounting edge 10 on the guide inner support 8. 9 and the diameter r of the internal through hole 10 .

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

[0119] In some embodiments, Fig. 9 , 10 As shown, the dimension parameters of the turbine rotor casing section are determined, including:

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

[0121] In some embodiments, the dimension parameters of the turbine guide outer ring 3 are read, and the inner diameter r of the turbine rotor casing section 4 is determined by considering the continuity and smoothness of the inner and outer walls of the integrated casing. 11、 Outer diameter 12 .

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

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

[0124] S53, determining the size parameters of the reinforcing rib 5 on the turbine rotor casing segment 4.

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

[0126] Specifically, the present invention determines the size parameters of each component based on the parameters of S1. By reasonably determining the size parameters of the flame tube exhaust duct, such as determining the outer diameter of the front mounting edge in consideration of the coordination with the flame tube supplementary combustion zone, and determining the inner and outer diameters of the large and small circular ends of the conical surface and the contraction shape according to the supplementary combustion zone, a good fit between the exhaust duct and other components and optimization of gas flow can be achieved. When determining the size parameters of the guide, the inner and outer diameters of the outer ring are determined in consideration of the continuity with the exhaust duct, the size of the reinforcing ribs is determined in combination with the strength calculation, and the aerodynamic parameters of the blades and the related parameters of the inner ring are determined according to the turbine channel conditions, thereby ensuring the performance of the guide. When determining the size parameters of the guide internal support and the size parameters of the turbine rotor casing section, a variety of factors are also comprehensively considered to ensure that the components are closely matched and the structure is reasonable. This method of determining dimensions based on parameters improves the rationality and reliability of the overall structure, optimizes the collaborative work between the various components of the aircraft engine, and improves the performance of the engine.

[0127] A storage medium stores a computer program, which, when executed by a processor, implements the above-mentioned method for integrating a small axial-flow turbine guide and a casing.

[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 realize the integrated modeling method of the small axial turbine guide and the casing, which provides an efficient and accurate implementation path for the design and manufacture of aircraft engines. In this way, it is possible to ensure the accurate implementation of the integrated modeling method, improve design efficiency, reduce human errors, optimize the coordination between components, and improve the overall performance and reliability of aircraft engines.

[0129] A computer device comprises: a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the above-mentioned method for integrating a small axial-flow turbine guide and a casing.

[0130] Specifically, the computer device has significant beneficial effects. The memory, processor and related computer programs included therein can realize the integrated modeling method of the small axial turbine guide and casing by executing the programs by the processor. This not only improves the efficiency and accuracy of the modeling method, reduces the errors that may be caused by manual operation, but also optimizes the design and matching of components, improves the overall performance and reliability of aircraft engines, and provides strong technical support for the manufacture of aircraft engines.

[0131] The present invention provides an integrated structure of a small axial-flow turbine guide and casing and a molding method thereof. In view of the problems in the prior art of the welding connection between the turbine guide and the exhaust duct of the flame tube and the turbine shaft sleeve, such as high requirements for equipment and environment and cracks easily appearing at the welding points, the present invention adopts an integrated molding method to avoid these welding problems and improve the reliability and stability of the connection. At the same time, in view of the problem in the prior art that the bending treatment of the inner hole end of the guide leads to stress concentration and easy premature damage, the present invention redesigns the connection method. The integrated structure and molding 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 invention can integrate the small axial-flow turbine guide and casing, meet the requirements of the integrated design, and is conducive to the optimization of the overall structure and performance improvement of the aircraft engine.

[0132] It should be noted that, in this article, relational terms such as "first" and "second" are used only 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 these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In addition, "front", "back", "left", "right", "upper" and "lower" in this article are all referenced to the placement state shown in the accompanying drawings.

[0133] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A small axial flow turbine guide and casing integrated structure, characterized in that: include: A front mounting edge (1), a flame tube exhaust duct (2), a guide device outer ring (3), a turbine rotor casing (4), a guide device blade (6), a guide device inner ring (7), a guide device inner support (8), a sleeve mounting edge (9) and a sleeve mounting edge bolt hole (13), wherein the front mounting edge (1) is connected to the flame tube exhaust duct (2) in a stepped manner, the flame tube exhaust duct (2) and the guide device outer ring (3) are connected in a stepped manner, the guide device outer ring (3) is connected to the turbine rotor casing (4), and the guide device outer ring (3) is connected to the guide device blade The guide vane (6) is connected to the outer circumference of the guide inner ring (7), the guide inner support (8) is connected to the inner circumference of the guide inner ring (7), the guide inner support (8) is provided with a sleeve mounting edge (9), the sleeve mounting edge bolt holes (13) are arranged circumferentially on the end surface of the sleeve mounting edge (9), the sleeve mounting edge bolt holes (13) are provided with a plurality of them, all of which are axial openings, the sleeve mounting edge (9) is fixedly connected to the turbine shaft sleeve through bolts in the sleeve mounting edge bolt holes (13), The front mounting edge (1), the flame tube exhaust duct (2), the guide outer ring (3) and the turbine rotor casing (4) are integrally formed.

2. The small axial flow turbine guide and casing integrated structure according to claim 1 is characterized in that: Front mounting side bolt holes (12) are circumferentially arranged on the front mounting side (1), and a plurality of front mounting side bolt holes (12) are provided, all of which are radial openings.

3. The small axial flow turbine guide and casing integrated structure according to claim 1 is characterized in that: Casing reinforcement ribs (5) are arranged on the guide outer ring (3) and the turbine rotor casing (4), and a plurality of casing reinforcement ribs (5) are provided.

4. The small axial flow turbine guide and casing integrated structure according to claim 3 is characterized in that: The flame tube exhaust conduit (2) is also provided with an evaporation tube inlet (11).

5. The small axial flow turbine guide and casing integrated structure according to claim 1, characterized in that: The guide vanes (6) are perpendicular to the tangent line at the connection points with the guide outer ring (3) and the guide inner ring (7).

6. The small axial flow turbine guide and casing integrated structure according to claim 1, characterized in that: The guide inner ring (7) gradually converges downwards into a cylindrical shaft hole (10).

7. A method for integrating a small axial flow turbine guide and a casing, based on a small axial flow turbine guide and a casing integrated structure as claimed in any one of claims 1 to 6, characterized in that: The integrated modeling method of the small axial flow turbine guide and casing The following steps are included: S1. Collect the design parameters required for the integrated casing; S2, determining the size parameters of the flame tube exhaust duct (2) based on the parameters of S1; S3, determining the size parameters of the guide based on the parameters of S1; S4, determining the size parameters of the guide inner support (8) based on the parameters of S1; S5. Determine the size parameters of the turbine rotor casing section (4) based on the parameters of S1.

8. The method for integrating a small axial flow turbine guide and casing according to claim 7, characterized in that: In S1, the following steps are included: S11, collecting the size parameters of the combustion chamber flame tube supplementary combustion area; S12, collecting the size and position parameters of the evaporation tube; S13, collecting dimension parameters of turbine shaft sleeve; S14, collecting the dimension parameters of the installation end of the turbine shaft sleeve guide; S15, collecting dimension parameters of the turbine shaft; S16, collecting the gas parameters at the flame tube outlet, and calculating the optimal size of the turbine channel according to aerodynamics; In S2, the following steps are included: S21, determining the outer diameter of the front mounting edge (1) on the flame tube exhaust duct (2); S22, determining the inner and outer diameters of the large circular end of the conical surface of the flame tube exhaust duct (2); S23, determining the contraction shape of the flame tube exhaust duct (2); S24, determining the size and position parameters of the evaporation tube inlet (11) on the flame tube exhaust duct (2); In S3, the following steps are included: S31, determining the inner and outer diameters of the guide outer ring (3); S32, determining the size parameters of the casing reinforcement rib (5) on the guide outer ring (3); S33, determining the aerodynamic parameters of the guide vane (6) and the curved surface shape and axial length of the guide inner ring (7); S34, determining the wall thickness of the guide inner ring (7); 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; S42, determining the diameter of the cylindrical shaft hole (10) on the inner support (8) of the guide; S43, determining the maximum diameter of the sleeve mounting edge (9) on the guide inner support (8) and the diameter of the internal through hole; 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 reinforcement rib (5) on the turbine rotor casing segment (4).

9. A storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, a method for integrating a small axial-flow turbine guide and a casing as described in any one of claims 7 to 8 is implemented.

10. A computer device, characterized in that: include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement a method for integrating a small axial-flow turbine guide and a casing as described in any one of claims 7 to 8.

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