A high-mach-number turbine engine low-pressure high-pressure rotor axial force transmission structure

Abstract

The application belongs to the technical field of high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure design, and particularly relates to a high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure, which comprises a high-pressure compressor front fulcrum bearing, a fan rear fulcrum bearing, a low-pressure turbine shaft front end and a high-pressure compressor front fulcrum bearing mounting seat.

Description

Technical Field

[0001] This application belongs to the technical field of axial force transmission structure design for low-pressure and high-pressure rotors of high Mach number turbine engines, specifically relating to an axial force transmission structure for a low-pressure and high-pressure rotor of a 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 via 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 rear end of the intermediate casing via the fan front pivot bearing mounting seat 8. The high-pressure compressor front pivot bearing 4 is sleeved on the front journal 5 of the high-pressure compressor rotor and connected to the inner rear end of the intermediate casing via the high-pressure compressor front pivot bearing mounting seat 6. The fan rear pivot bearing 7 in the inner rear end of the intermediate casing is located in front of the high-pressure compressor front pivot bearing 4. Under this technical solution, when the engine is working, the forward axial force of the low-pressure rotor and the rearward axial force of the high-pressure and intermediate-pressure rotors are transmitted to the intermediate casing via the fan front pivot bearing 1 and the high-pressure compressor front pivot bearing 4 through 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.

[0003] In the low-pressure rotor support system of a low-Mach number turbine engine, the fan shaft 2 and the low-pressure 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 the turbine rotor, as well as reliable centering between them. Currently, the connecting structure between the fan shaft and the low-pressure 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 low-pressure 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 low-pressure 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 low-pressure 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 low-pressure turbine shaft 9 are connected by two cylindrical surfaces, which are located on both sides of the toothed structure, thereby ensuring reliable centering between the fan rotor and the turbine rotor.

[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 better 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 scheme used for low Mach number turbine engines is not suitable. Therefore, it is necessary to move the rear support bearing 7 of the fan rearward and design a new axial force transmission structure for the low-pressure high-pressure rotor. In light of this, this application is proposed.

[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 an axial force transmission structure for the low-pressure, high-pressure rotor of a high Mach number turbine engine, ensuring the dynamic characteristics of the fan and improving the dynamic stability margin of the fan.

[0007] The technical solution of this application is:

[0008] An axial force transmission structure for a low-pressure, high-pressure rotor of a high Mach number turbine engine includes:

[0009] The high-pressure compressor front pivot bearing is sleeved on the front journal of the high-pressure compressor rotor and installed in the high-pressure compressor front pivot bearing mounting seat, which is connected to the rear end of the intermediate casing.

[0010] The rear pivot bearing of the fan is fitted onto the front end of the low-pressure turbine shaft and installed inside the front journal of the high-pressure compressor rotor, located behind the front pivot bearing of the high-pressure compressor; the front end of the low-pressure turbine shaft is connected to the rear end of the fan shaft.

[0011] According to at least one embodiment of this application, in the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure, the outer side of the rear end of the fan shaft has an outer pressing protrusion.

[0012] The high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure also includes:

[0013] The annular transition section has its rear end fitted onto the front end of the low-pressure turbine shaft, and is centered with the front end of the low-pressure 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 low-pressure turbine shaft.

[0014] The rear pivot bearing of the fan is fitted onto the front end of the annular transition section.

[0015] According to at least one embodiment of this application, in the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission 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.

[0016] According to at least one embodiment of this application, the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure further includes:

[0017] Adjust the shim, positioned on the inner side between the protrusion and the front end of the low-pressure turbine shaft.

[0018] According to at least one embodiment of this application, the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure further includes:

[0019] The fuel injector is located inside the intermediate housing, at the front end of the front journal of the high-pressure compressor rotor.

[0020] The high-pressure compressor front support bearing lubrication oil collection ring is set at the front end of the high-pressure compressor rotor front journal. The high-pressure compressor rotor front journal has a high-pressure compressor front support bearing lubrication channel. The high-pressure compressor front support bearing lubrication oil collection ring can collect the lubricating oil sprayed from the oil injector and supply it to the high-pressure compressor front support bearing through the high-pressure compressor front support bearing lubrication channel.

[0021] The fan rear pivot bearing lubrication oil collection ring is set at the front end of the annular transition section, and the annular transition section has a fan rear pivot bearing lubrication channel; the lubricating oil sprayed from the oil injector can flow into the front journal of the high-pressure compressor rotor, and the fan rear pivot bearing lubrication oil collection ring can collect this part of the lubricating oil and supply it to the fan rear pivot bearing through the fan rear pivot bearing lubrication channel.

[0022] According to at least one embodiment of this application, in the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure, the high-pressure compressor rotor front journal and annular transition section are sealed from front to back using graphite and honeycomb mesh.

[0023] Between the front journal of the high-pressure compressor rotor and the front support bearing mounting seat of the high-pressure compressor, a graphite and comb-tooth honeycomb seal is used from front to back.

[0024] According to at least one embodiment of this application, in the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure, the front journal of the high-pressure compressor rotor has multiple balance flow holes.

[0025] The space between the graphite and honeycomb seal between the front journal of the high-pressure compressor rotor and the annular transition section is connected to the space between the graphite and honeycomb seal between the front journal of the high-pressure compressor rotor and the front support bearing mounting seat of the high-pressure compressor through various balance flow holes. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the low-pressure rotor support system of an existing low-Mach number turbine engine;

[0027] Figure 2 This is a schematic diagram of the connection structure between the fan shaft and the low-pressure turbine shaft of an existing low-Mach number turbine engine.

[0028] Figure 3 This application provides a schematic diagram of the axial force transmission structure of the low-pressure, high-pressure rotor of a high Mach number turbine engine;

[0029] Figure 4 This is a schematic diagram of a low-pressure rotor support system for a high-Mach number turbine engine, based on the axial force transmission structure of the low-pressure high-pressure rotor of the Mach number turbine engine provided in the embodiments of this application.

[0030] in:

[0031] 1-Fan front pivot bearing; 2-Fan shaft; 3-Fan front pivot bearing mounting seat; 4-High pressure compressor front pivot bearing; 5-High pressure compressor rotor front journal; 6-High pressure compressor front pivot bearing mounting seat; 7-Fan rear pivot bearing; 8-Fan rear pivot bearing mounting seat; 9-Low pressure turbine shaft; 10-Pressure nut; 11-Adapter cylinder; 12-Anti-rotation cylinder; 13-Spring retaining ring; 14-Annular adapter section; 15-Adjusting shim; 16-Oil injector; 17-High pressure compressor front pivot bearing lubrication oil recovery ring; 18-Fan rear pivot bearing lubrication oil recovery ring.

[0032] 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

[0033] 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.

[0034] 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.

[0035] 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.

[0036] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.

[0037] An axial force transmission structure for the low-pressure, high-pressure rotor of a high Mach number turbine engine, such as... Figure 3 As shown, it includes:

[0038] The high-pressure compressor front pivot bearing 4 is sleeved on the high-pressure compressor rotor front journal 5 and installed in the high-pressure compressor front pivot bearing mounting seat 6. The high-pressure compressor front pivot bearing mounting seat 6 is connected to the rear end of the intermediate casing.

[0039] The rear pivot bearing 7 of the fan is sleeved on the front end of the low-pressure turbine shaft 9 and installed inside the front journal 5 of the high-pressure compressor rotor, located behind the front pivot bearing 4 of the high-pressure compressor; the front end of the low-pressure turbine shaft 9 is connected to the rear end of the fan shaft 2.

[0040] The overall structure of the high Mach number turbine engine low-pressure rotor support system based on the axial force transmission structure of the low-pressure and high-pressure rotors disclosed in the above embodiments is as follows: Figure 4 As shown, the rear support bearing 7 of the fan is moved rearward and located behind the front support bearing 4 of the high-pressure compressor. This effectively ensures the dynamic characteristics of the fan and improves the dynamic stability margin of the fan. In addition, under this structure, the forward axial force of the low-pressure rotor can be transmitted to the front support bearing 4 of the high-pressure compressor via the rear support bearing 7 of the fan and the front journal 5 of the high-pressure compressor rotor. The backward axial force of the high-pressure rotor can be transmitted to the front support bearing 4 of the high-pressure compressor rotor via the front journal 5 of the high-pressure compressor rotor. The forward axial force of the low-pressure rotor and the backward axial force of the high-pressure rotor partially cancel each other out on the front support bearing 4 of the high-pressure compressor. The remaining part is transmitted to the intermediate casing via the mounting seat 6 of the front support bearing of the high-pressure compressor. 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, which can reduce the overall weight of the engine. It can also transfer radial loads to the intermediate casing and provide reliable support for the low-pressure and high-pressure rotor systems.

[0041] In some optional embodiments, in the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure, the outer side of the rear end of the fan shaft 2 has an outer clamping protrusion.

[0042] The high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure also includes:

[0043] The annular transition section 14 has its rear end sleeved on the front end of the low-pressure turbine shaft 9 and centered with the front end of the low-pressure turbine shaft 9 through a cylindrical 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 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 low-pressure turbine shaft 9.

[0044] The rear pivot bearing 7 of the fan is sleeved on the front end of the annular transition section 14.

[0045] Regarding the high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure 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, the low-pressure turbine shaft 9, and the fan rear support bearing 7, which facilitates assembly.

[0046] In some optional embodiments, in the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission 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.

[0047] In some optional embodiments, the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure further includes:

[0048] Adjustment shim 15, located between the inner positioning protrusion and the front end of the low-pressure turbine shaft 9, can be installed according to the required thickness.

[0049] In some optional embodiments, the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure further includes:

[0050] The fuel injector 16 is installed in the intermediate casing and is located at the front end of the front journal 5 of the high-pressure compressor rotor.

[0051] The high-pressure compressor front support bearing lubrication oil collection ring 17 is set at the front end of the high-pressure compressor rotor front journal 5. The high-pressure compressor rotor front journal 5 has a high-pressure compressor front support bearing lubrication channel. The high-pressure compressor front support bearing lubrication oil collection ring 17 can collect the lubricating oil sprayed by the oil injector 16 and supply it to the high-pressure compressor front support bearing 4 through the high-pressure compressor front support bearing lubrication channel for lubrication and cooling.

[0052] The fan rear pivot bearing lubrication oil collection ring 18 is set at the front end of the annular transition section 14, and the annular transition section 14 has a fan rear pivot bearing lubrication channel; the lubricating oil sprayed from the oil nozzle 16 can flow into the front journal 5 of the high-pressure compressor rotor, and the fan rear pivot bearing lubrication oil collection ring 18 can collect this part of the lubricating oil and supply it to the fan rear pivot bearing 7 through the fan rear pivot bearing lubrication channel for lubrication and cooling.

[0053] In some optional embodiments, in the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure, the high-pressure compressor rotor front journal 5 and the annular transition section 14 are sealed from front to back with graphite and honeycomb mesh to prevent lubricating oil from leaking into the high-pressure compressor part.

[0054] Between the front journal 5 of the high-pressure compressor rotor and the front support bearing mounting seat 6 of the high-pressure compressor, a graphite and honeycomb seal is used from front to back to prevent lubricating oil from leaking into the high-pressure compressor parts.

[0055] In some optional embodiments, in the above-described high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure, the high-pressure compressor rotor front journal 5 has multiple balance flow holes.

[0056] The space between the graphite and honeycomb seal between the front journal 5 of the high-pressure compressor rotor and the annular transition section 14 is connected to the space between the graphite and honeycomb seal between the front journal 5 of the high-pressure compressor rotor and the front support bearing mounting seat 6 of the high-pressure compressor through various balance flow holes to enable balanced ventilation.

[0057] In practice, the high Mach number turbine engine low-pressure rotor support system, which utilizes the high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure disclosed in the above embodiments, is difficult to adopt a connection structure between the low Mach number turbine engine fan shaft and the low-pressure turbine shaft due to structural space limitations. Therefore, this application designs a new high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure to ensure reliable transmission of torque and axial force between the high Mach number turbine engine fan rotor and turbine rotor, as well as reliable centering between the fan rotor and turbine rotor. The design includes a low-pressure turbine shaft 9 with an annular positioning protrusion inside its front end; and a fan shaft 2 with its rear end extending into the front end of the low-pressure turbine shaft 9, connected to the front end of the low-pressure turbine shaft 9 via a sleeve gear engagement, thereby ensuring torque transmission between the fan rotor and turbine rotor, and centering through two cylindrical surfaces located on both sides of the sleeve gear, thus ensuring reliable centering between the fan rotor and turbine rotor. The rear end of the fan shaft 2 also has an annular limiting protrusion and an annular limiting groove. Furthermore, the new high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure includes:

[0058] The adapter cylinder 11 is installed inside the fan shaft 2, with its rear end extending into the front end of the low-pressure 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.

[0059] 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 low-pressure turbine shaft 9 from loosening, and ensures the reliability of axial force transmission between the fan rotor and the turbine rotor.

[0060] 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.

[0061] Regarding the high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure 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 fully utilize the internal space of the fan shaft 2 and the low-pressure turbine shaft 9 under space-constrained conditions, to achieve a reliable connection between the rear end of the fan shaft 2 and the front end of the low-pressure 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.

[0062] 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.

[0063] 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. An axial force transmission structure for a low-pressure, high-pressure rotor of a high Mach number turbine engine, characterized in that, include: The front pivot bearing (4) of the high pressure compressor is sleeved on the front journal (5) of the high pressure compressor rotor and installed in the front pivot bearing mounting seat (6) of the high pressure compressor. The front pivot bearing mounting seat (6) of the high pressure compressor is connected to the rear end of the intermediate casing. The rear pivot bearing (7) of the fan is sleeved on the front end of the low-pressure turbine shaft (9) and installed inside the front journal (5) of the high-pressure compressor rotor, located behind the front pivot bearing (4) of the high-pressure compressor; the front end of the low-pressure turbine shaft (9) is connected to the rear end of the fan shaft (2); The fan shaft (2) has an outer pressing protrusion on the outer side of its rear end; The high Mach number turbine engine low-pressure high-pressure rotor axial force transmission structure also includes: The annular transition section (14) is fitted at the rear end of the low-pressure turbine shaft (9) and centered with the front end of the low-pressure turbine shaft (9) through a cylindrical fit. The front end is fitted 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 low-pressure turbine shaft (9). The rear pivot bearing (7) of the fan is fitted onto the front end of the annular transition section (14).

2. The axial force transmission structure for the low-pressure, high-pressure rotor 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.

3. The axial force transmission structure for the low-pressure, high-pressure rotor of a high Mach number turbine engine according to claim 1, characterized in that, Also includes: Adjusting pad (15) is positioned on the inner side between the protrusion and the front end of the low-pressure turbine shaft (9).

4. The axial force transmission structure for the low-pressure, high-pressure rotor of a high Mach number turbine engine according to claim 1, characterized in that, Also includes: The fuel injector (16) is installed in the intermediate casing and is located at the front end of the front journal (5) of the high-pressure compressor rotor; A lubrication ring (17) for the front bearing of the high-pressure compressor is provided at the front end of the front journal (5) of the high-pressure compressor rotor. A lubrication channel for the front bearing of the high-pressure compressor is constructed on the front journal (5) of the high-pressure compressor rotor. The lubrication ring (17) can collect the lubricating oil sprayed from the nozzle (16) and supply it to the front bearing (4) of the high-pressure compressor through the lubrication channel. The fan rear pivot bearing lubrication oil collection ring (18) is set at the front end of the annular transition section (14), and the annular transition section (14) has a fan rear pivot bearing lubrication channel; the lubricating oil sprayed by the oil nozzle (16) can flow into the front journal (5) of the high pressure compressor rotor, and the fan rear pivot bearing lubrication oil collection ring (18) can collect this part of the lubricating oil and supply it to the fan rear pivot bearing (7) through the fan rear pivot bearing lubrication channel.

5. The axial force transmission structure for the low-pressure, high-pressure rotor of a high Mach number turbine engine according to claim 4, characterized in that, Between the front journal (5) and the annular transition section (14) of the high-pressure compressor rotor, a graphite and comb-tooth honeycomb seal is used from front to back. Between the front journal (5) of the high-pressure compressor rotor and the front support bearing mounting seat (6) of the high-pressure compressor, a graphite and comb-tooth honeycomb seal is used from front to back.

6. The axial force transmission structure for the low-pressure, high-pressure rotor of a high Mach number turbine engine according to claim 5, characterized in that, The front journal (5) of the high-pressure compressor rotor has multiple balance flow holes; The space between the graphite and honeycomb seal between the front journal (5) and the annular transition section (14) of the high-pressure compressor rotor is connected to the space between the graphite and honeycomb seal between the front journal (5) and the front support bearing mounting seat (6) of the high-pressure compressor rotor through various balance flow holes.

Images