A high-mach number turbine engine fan shaft and turbine shaft connection
By employing a ring-shaped positioning protrusion at the front end of the turbine shaft and a toothed connection at the rear end of the fan shaft in a high Mach number turbine engine, combined with the design of an adapter sleeve, anti-rotation sleeve, and spring retainer ring, the problem of reliable transmission and centering of the connection structure between the fan shaft and the turbine shaft under space constraints is solved, achieving efficient torque and axial force transmission and reducing engine weight.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AECC SHENYANG ENGINE RES INST
- Filing Date
- 2023-09-18
- Publication Date
- 2026-06-16
Smart Images
Figure CN117189375B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of connection structure design between fan shaft and turbine shaft of high Mach number turbine engine, and specifically relates to a connection structure between fan shaft and turbine shaft of high Mach number turbine engine. Background Technology
[0002] Low Mach number turbine engines, such as two-stage Mach number aero engines, low-pressure rotor support systems such as Figure 1 As shown, the fan front pivot bearing 1 is sleeved on the front end of the fan shaft 2 and connected to the front end of the inner intermediate casing through the fan front pivot bearing mounting seat 3. The fan rear pivot bearing 7 is sleeved on the rear end of the fan shaft 2 and connected to the inner upper part of the rear end of the intermediate casing through the fan front pivot bearing mounting seat 8. The compressor front pivot bearing 4 is sleeved on the compressor rotor front journal 5 and connected to the inner upper part of the rear end of the intermediate casing through the compressor front pivot bearing mounting seat 6. The fan rear pivot bearing 7 in the rear end of the intermediate casing is located in front of the compressor front pivot bearing 4.
[0003] In the low-pressure rotor support system of a low-Mach number turbine engine, the fan shaft 2 and turbine shaft 9 are connected by a connecting structure. This connecting structure needs to ensure reliable transmission of torque and axial force between the fan rotor and turbine rotor, as well as reliable centering between them. Currently, the connecting structure between the fan shaft and turbine shaft of a low-Mach number turbine engine is as follows: Figure 2 As shown, the rear end of the fan shaft 2 is sleeved on the front end of the turbine shaft 9, and they are connected by a toothed fit to ensure torque transmission between the fan rotor and the turbine rotor. The fan shaft 2 has an annular stop protrusion, and a clamping nut 10 is screwed onto the front end of the turbine shaft 9. The clamping nut 10 presses against the annular stop protrusion, so that the annular stop protrusion abuts against the protruding part at the front end of the turbine shaft 9, thereby ensuring reliable transmission of axial force between the fan rotor and the turbine rotor. In addition, the rear end of the fan shaft 2 and the front end of the turbine shaft 9 are connected by two cylindrical surfaces located on both sides of the toothed structure to ensure reliable centering between the fan rotor and the turbine rotor. Under this technical solution, when the engine is working, the forward axial force of the low-pressure rotor and the backward axial force of the high-pressure rotor are transmitted to the intermediate casing through the fan front support bearing 1 and the compressor front support bearing 4, respectively, via the corresponding bearing mounting seats. The overall force transmission path is relatively long, and the structural components along the force transmission path bear a large load and have a large weight, which increases the overall mass of the engine.
[0004] High Mach number turbine engines have significantly higher maximum flight altitudes and speeds than low Mach number turbine engines. During operation, the fan inlet temperature of a high Mach number turbine engine is also much higher than that of a low Mach number turbine engine, requiring the use of materials with superior high-temperature resistance. This results in a substantial change in the weight and center of gravity of the fan rotor compared to a low Mach number turbine engine, altering the inherent dynamic characteristics of the low-pressure rotor support system. To ensure the fan's dynamic characteristics and improve its dynamic stability margin, the low-pressure rotor support system design of low Mach number turbine engines is not suitable. Currently, the design of low-pressure rotor support systems for high Mach number turbine engines is as follows: Figure 3 As shown, the compressor front pivot bearing 4 is sleeved on the compressor rotor front journal 5 and connected to the rear end of the intermediate casing via the compressor front pivot bearing mounting seat 6. The fan rear pivot bearing 7 is sleeved on the front end of the turbine shaft 9 and installed inside the compressor rotor front journal 5. The fan rear pivot bearing 7 is moved to the rear side of the compressor front pivot bearing 4. The rear end of the fan shaft 2 extends into the front end of the turbine shaft 9 for connection. In this case, the forward axial force of the low-pressure rotor can be transmitted to the compressor front pivot bearing 4 via the fan rear pivot bearing 7 and the compressor rotor front journal 5. The backward axial force of the high-pressure rotor can be transmitted to the compressor front pivot bearing 4 via the compressor rotor front journal 5. The forward axial force of the low-pressure rotor and the backward axial force of the high-pressure rotor are transmitted to the compressor front pivot bearing 4 at the compressor front. Part of the force is canceled out on the pivot bearing 4, and the remaining force is transmitted to the intermediate casing via the compressor front pivot bearing mounting seat 6. This shortens the force transmission path to a certain extent and reduces the load and weight of each structural component on the force transmission path. In particular, it can reduce the weight of the intermediate casing and reduce the overall weight of the engine. However, due to structural space limitations, it is difficult to adopt the connection structure between the fan shaft and turbine shaft of a low Mach number turbine engine. Therefore, a new connection structure between the fan shaft and turbine shaft needs to be designed to ensure the reliable transmission of torque and axial force between the fan rotor and turbine rotor of a high Mach number turbine engine, as well as to ensure reliable centering between the fan rotor and turbine rotor. In view of this, this application is made.
[0005] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention
[0006] The purpose of this application is to provide a connection structure between the fan shaft and the turbine shaft of a high Mach number turbine engine, so as to ensure the reliable transmission of torque and axial force between the fan rotor and the turbine rotor of the high Mach number turbine engine, as well as to ensure reliable centering between the fan rotor and the turbine rotor.
[0007] The technical solution of this application is:
[0008] A connection structure between the fan shaft and the turbine shaft of a high Mach number turbine engine includes:
[0009] The turbine shaft has an annular positioning protrusion inside the front end.
[0010] The rear end of the fan shaft extends into the front end of the turbine shaft and is connected to the front end of the turbine shaft by a sleeve gear engagement and is centered by two cylindrical surfaces. These two cylindrical surfaces are located on both sides of the sleeve gear and have annular limiting protrusions and annular limiting grooves inside.
[0011] The adapter cylinder is installed inside the fan shaft, with its rear end extending into the front end of the turbine shaft and threadedly connected to the annular positioning protrusion. The outer side of the front end has an annular pressing protrusion; the annular pressing protrusion presses against the annular limiting protrusion, so that the front end of the fan shaft abuts against the annular positioning protrusion.
[0012] The anti-rotation cylinder is installed inside the fan shaft, with its rear end sleeved on the front end of the adapter cylinder. It is connected to the front end of the adapter cylinder by a sleeve tooth engagement, and its front end is connected to the inner side of the rear end of the fan shaft by a sleeve tooth engagement.
[0013] The spring retainer is set in the annular limiting groove and abuts against the front end of the anti-rotation cylinder.
[0014] According to at least one embodiment of this application, in the above-described high Mach number turbine engine fan shaft and turbine shaft connection structure, a fan rear pivot bearing is sleeved on the outside of the turbine shaft, the fan rear pivot bearing is installed on the inside of the compressor rotor front journal, a compressor front pivot bearing is sleeved on the outside of the compressor rotor front journal, and the compressor front pivot bearing is connected to the rear end of the intermediate casing through a compressor front pivot bearing mounting seat.
[0015] According to at least one embodiment of this application, in the above-described high Mach number turbine engine fan shaft and turbine shaft connection structure, the outer side of the rear end of the fan shaft has an outer pressing protrusion.
[0016] The connection structure between the fan shaft and the turbine shaft of the high Mach number turbine engine also includes:
[0017] The annular transition section has its rear end fitted onto the front end of the turbine shaft, and is centered with the front end of the turbine shaft through a cylindrical fit. Its front end is fitted onto the rear end of the fan shaft, and is centered with the outer pressing protrusion through a cylindrical fit. The inner side has an inner positioning protrusion. The inner positioning protrusion is connected to the rear end of the fan shaft through a sleeve tooth fit. The outer pressing protrusion presses against the inner positioning protrusion, so that the inner positioning protrusion presses against the front end of the turbine shaft.
[0018] The rear pivot bearing of the fan is fitted onto the front end of the annular transition section.
[0019] According to at least one embodiment of this application, in the above-described high Mach number turbine engine fan shaft and turbine shaft connection structure, an annular sealing groove is provided between the outer pressing protrusion and the inner side of the annular transition section, and a sealing ring is provided in the annular sealing groove. Attached Figure Description
[0020] Figure 1 This is a schematic diagram of the low-pressure rotor support system of an existing low-Mach number turbine engine;
[0021] Figure 2 This is a schematic diagram of the connection structure between the fan shaft and the turbine shaft of an existing low Mach number turbine engine.
[0022] Figure 3 A schematic diagram of an existing low-pressure rotor support system for a high Mach number turbine engine;
[0023] Figure 4 This is a schematic diagram of the connection structure between the fan shaft and the turbine shaft of a high Mach number turbine engine provided in an embodiment of this application;
[0024] in:
[0025] 1-Fan front pivot bearing; 2-Fan shaft; 3-Fan front pivot bearing mounting seat; 4-Compressor front pivot bearing; 5-Compressor rotor front journal; 6-Compressor front pivot bearing mounting seat; 7-Fan rear pivot bearing; 8-Fan rear pivot bearing mounting seat; 9-Turbine shaft; 10-Pressure nut; 11-Adapter cylinder; 12-Anti-rotation cylinder; 13-Spring retaining ring; 14-Annular adapter section.
[0026] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation
[0027] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.
[0028] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.
[0029] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.
[0030] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.
[0031] A connection structure between the fan shaft and the turbine shaft of a high Mach number turbine engine includes:
[0032] Turbine shaft 9 has an annular positioning protrusion inside the front end;
[0033] The rear end of the fan shaft 2 extends into the front end of the turbine shaft 9 and is connected to the front end of the turbine shaft 9 by a sleeve gear engagement, thereby ensuring torque transmission between the fan rotor and the turbine rotor, and centering is achieved by two cylindrical surfaces located on both sides of the sleeve gear, thereby ensuring reliable centering between the fan rotor and the turbine rotor. The rear end of the fan shaft 2 has an annular limiting protrusion and an annular limiting groove.
[0034] The adapter cylinder 11 is installed inside the fan shaft 2, with its rear end extending into the front end of the turbine shaft 9 and threadedly connected to the annular positioning protrusion. The outer side of the front end has an annular pressing protrusion. The annular pressing protrusion presses against the annular limiting protrusion, so that the front end of the fan shaft 2 abuts against the annular positioning protrusion, thereby ensuring the reliable transmission of axial force between the fan rotor and the turbine rotor.
[0035] Anti-rotation cylinder 12 is installed inside the fan shaft 2, with its rear end sleeved on the front end of the adapter cylinder 11. It is connected to the front end of the adapter cylinder 11 by a sleeve tooth engagement, and its front end is connected to the inner side of the rear end of the fan shaft 2 by a sleeve tooth engagement. This prevents the threads between the adapter cylinder 11 and the turbine shaft 9 from loosening, and ensures the reliability of axial force transmission between the fan rotor and the turbine rotor.
[0036] The spring retainer 13 is set in the annular limiting groove and abuts against the front end of the anti-rotation cylinder 12 to reliably position the anti-rotation cylinder 12 inside the rear end of the fan shaft 2 and prevent the anti-rotation cylinder 12 from loosening outward.
[0037] Regarding the connection structure between the fan shaft and turbine shaft of the high Mach number turbine engine disclosed in the above embodiments, those skilled in the art will understand that its design utilizes the adapter cylinder 11, anti-rotation cylinder 12, and spring retainer 13 to make full use of the internal space of the fan shaft 2 and turbine shaft 9 under space-constrained conditions, thereby achieving a reliable connection between the rear end of the fan shaft 2 and the front end of the turbine shaft 9, and can effectively ensure the reliable transmission of torque and axial force between the fan rotor and the turbine rotor, as well as ensure the reliable centering between the fan rotor and the turbine rotor.
[0038] In some optional embodiments, in the above-described high Mach number turbine engine fan shaft and turbine shaft connection structure, the rear end of the fan shaft 2 has an outer pressing protrusion.
[0039] The connection structure between the fan shaft and the turbine shaft of the high Mach number turbine engine also includes:
[0040] The annular transition section 14 has its rear end sleeved on the front end of the turbine shaft 9 and centered with the front end of the turbine shaft 9 through a cylindrical surface fit. Its front end is sleeved on the rear end of the fan shaft 2 and centered with the outer pressing protrusion through a cylindrical surface fit. It has an inner positioning protrusion on the inner side. The inner positioning protrusion is connected to the rear end of the fan shaft 2 through a sleeve tooth fit. The outer pressing protrusion presses against the inner positioning protrusion, so that the inner positioning protrusion presses against the front end of the turbine shaft 9.
[0041] The front end of the annular transition section 14 is fitted with a fan rear pivot bearing 7, which is installed inside the compressor rotor front journal 5. The compressor rotor front journal 5 is fitted with a compressor front pivot bearing 4, which is connected to the rear end of the intermediate casing through a compressor front pivot bearing mounting seat 6.
[0042] Regarding the connection structure between the fan shaft and turbine shaft of the high Mach number turbine engine disclosed in the above embodiments, those skilled in the art will understand that its design uses an annular transition section 14 to transition between the fan shaft 2, turbine shaft 9, and fan rear pivot bearing 7, which can prevent interference between the protruding parts during assembly and facilitate assembly.
[0043] In some optional embodiments, in the above-described high Mach number turbine engine fan shaft and turbine shaft connection structure, there is an annular sealing groove between the outer pressing protrusion and the inner side of the annular transition section 14, and a sealing ring is provided in the annular sealing groove.
[0044] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.
[0045] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.
Claims
1. A connection structure between the fan shaft and the turbine shaft of a high Mach number turbine engine, characterized in that, include: The turbine shaft (9) has an annular positioning protrusion inside the front end; The fan shaft (2) extends into the front end of the turbine shaft (9) and is connected to the front end of the turbine shaft (9) by a sleeve tooth engagement and is centered by two cylindrical surfaces. These two cylindrical surfaces are located on both sides of the sleeve tooth and have annular limiting protrusions and annular limiting grooves inside. The adapter tube (11) is installed inside the fan shaft (2), with its rear end extending into the front end of the turbine shaft (9) and threadedly connected to the annular positioning protrusion. The outer side of the front end has an annular pressing protrusion. The annular pressing protrusion presses against the annular limiting protrusion, so that the front end of the fan shaft (2) abuts against the annular positioning protrusion. Anti-rotation cylinder (12) is installed inside the fan shaft (2), with its rear end sleeved on the front end of the adapter cylinder (11), and connected to the front end of the adapter cylinder (11) by a sleeve tooth engagement, and connected to the inner side of the rear end of the fan shaft (2) by a sleeve tooth engagement. A spring retainer (13) is set in an annular limiting groove and abuts against the front end of the anti-rotation cylinder (12); The fan shaft (2) has an outer pressing protrusion on the outer side of its rear end; The connection structure between the fan shaft and the turbine shaft of the high Mach number turbine engine also includes: The annular transition section (14) is sleeved at the front end of the turbine shaft (9) and centered with the front end of the turbine shaft (9) through a cylindrical fit. The front end is sleeved at the rear end of the fan shaft (2) and centered with the outer pressing protrusion through a cylindrical fit. The inner side has an inner positioning protrusion. The inner positioning protrusion is connected to the rear end of the fan shaft (2) through a sleeve tooth fit. The outer pressing protrusion presses against the inner positioning protrusion, so that the inner positioning protrusion presses against the front end of the turbine shaft (9).
2. The connection structure between the fan shaft and the turbine shaft of a high Mach number turbine engine according to claim 1, characterized in that, There is an annular sealing groove between the outer pressing protrusion and the inner side of the annular transition section (14), and a sealing ring is provided in the annular sealing groove.