Aero-engine rotor axial load pre-balancing structure

Abstract

The application belongs to the technical field of aero-engine rotor axial load control, and particularly relates to an aero-engine rotor axial load pre-balancing structure, which comprises a small ball bearing, a front-side inner elastic ring, a front-side outer elastic ring and a balance positioning ring.

Description

Technical Field

[0001] This application belongs to the field of aero-engine rotor axial load control technology, specifically relating to an aero-engine rotor axial load pre-balancing structure. Background Technology

[0002] The rotor axial load in an aero-engine consists of two parts: the main flow axial force and the air system axial force. The main flow axial force is generated by the difference in the flow velocity of the main flow and the pressure on both sides of the rotor blades. The air system axial force is generated by the pressure inside the aero-engine acting on rotor components such as the compression disk and turbine disk.

[0003] Generally, the axial force in the main flow path of an aero-engine is determined by the engine's performance design. Adjustment of the rotor axial load is primarily achieved through air system regulation to prevent excessive load on the thrust bearings on the rotor shaft, which could lead to damage. However, adjusting the rotor axial load alone is insufficient to accommodate both low and high aerodynamic load conditions. When designing the air system to adjust the rotor axial load to suit high aerodynamic load conditions, under low aerodynamic load conditions, the rotor axial load is prone to light loads or even reversal, causing thrust bearing slippage and damaging its lifespan and reliability. Conversely, when designing the air system to adjust the rotor axial load to suit low aerodynamic load conditions, under high aerodynamic load conditions, it is difficult to meet the balance requirements, posing significant technical risks and potentially causing safety issues.

[0004] This application is made in view of the aforementioned technical deficiencies.

[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 pre-balanced structure for axial load on an aero-engine rotor to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] An axial load pre-balancing structure for an aero-engine rotor includes:

[0009] A small ball bearing is fitted around the outer circumference of the rotor shaft, located in front of the thrust bearing;

[0010] An inner elastic ring is fitted on the rotor shaft and located in front of the small ball bearing, with its sidewall tilted backward.

[0011] The outer elastic ring is sleeved on the rotor shaft and located in front of the inner elastic ring, with its sidewall inclined forward.

[0012] A balance positioning ring is fitted around the inner and outer elastic rings and connected to the thrust bearing housing. The inner side has an annular balance positioning protrusion. The annular balance positioning protrusion presses against the outer edge of the outer elastic ring, causing the center of the outer elastic ring to abut against the center of the inner elastic ring. This, in turn, presses the outer edge of the inner elastic ring against the front end of the outer ring of the miniature ball bearing, thereby pressing the rear end of the inner ring of the miniature ball bearing against the front end of the inner ring of the thrust bearing, applying a rearward axial force to the thrust bearing.

[0013] According to at least one embodiment of this application, in the above-described pre-balanced axial load structure for aero-engine rotors, the front section of the inner ring of the small ball bearing is removed, and the rear end of the rear section is integrally formed on the front end of the inner ring of the thrust bearing.

[0014] According to at least one embodiment of this application, in the above-described pre-balanced structure for axial load of aero-engine rotor, there is a large gap between the inner ring of the inner elastic ring and the rotor shaft, and a small gap between the outer ring and the balance positioning ring.

[0015] According to at least one embodiment of this application, in the above-described pre-balanced structure for axial load of aero-engine rotor, the balancing positioning ring is bolted to the thrust bearing housing.

[0016] According to at least one embodiment of this application, in the above-described pre-balanced structure for axial load of aero-engine rotor, the balancing positioning ring and the thrust bearing housing are positioned by a stop.

[0017] According to at least one embodiment of this application, the above-described aero-engine rotor axial load pre-balancing structure further includes:

[0018] The adjusting shim is fitted around the outer circumference of the rotor shaft, located between the outer edge of the inner elastic ring and the front end of the outer ring of the small ball bearing. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the axial load pre-balancing structure for an aero-engine rotor provided in an embodiment of this application;

[0020] Figure 2 This is a schematic diagram of the inner elastic ring and the outer elastic ring fitting together according to an embodiment of this application;

[0021] in:

[0022] 1-Small ball bearing; 2-Rotor shaft; 3-Thrust bearing; 4-Thrust bearing housing; 5-Inner elastic ring; 6-Outer elastic ring; 7-Balance positioning ring; 8-Adjusting shim.

[0023] 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

[0024] 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.

[0025] 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.

[0026] 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.

[0027] The following is in conjunction with the appendix Figures 1-2 This application will be described in further detail.

[0028] An axial load pre-balancing structure for an aero-engine rotor includes:

[0029] A small ball bearing 1 is sleeved on the outer circumference of the rotor shaft 2 and located in front of the thrust bearing 3; the inner ring of the thrust bearing 3 is sleeved on the rotor shaft 2 and the outer ring is installed in the thrust bearing housing 4.

[0030] The inner elastic ring 5 is sleeved on the rotor shaft 2 and located in front of the small ball bearing 1, with its sidewall tilted backward.

[0031] The outer elastic ring 6 is sleeved on the rotor shaft 2 and is located in front of the inner elastic ring 5, with its sidewall inclined forward.

[0032] The balance positioning ring 7 is sleeved on the outer periphery of the inner elastic ring 5 and the outer elastic ring 6, and connected to the thrust bearing seat 4. The inner side has an annular balance positioning protrusion. The annular balance positioning protrusion presses on the outer edge of the outer elastic ring 6, so that the center part of the outer elastic ring 6 abuts against the center part of the inner elastic ring 5, thereby pressing the outer edge of the inner elastic ring 5 against the front end of the outer ring of the small ball bearing 1, thereby pressing the rear end of the inner ring of the small ball bearing 1 against the front end of the inner ring of the thrust bearing 3, and applying a rearward axial force to the thrust bearing 3.

[0033] In the axial load pre-balancing structure for aero-engine rotors disclosed in the above embodiments, the design utilizes the elastic action of the inner elastic ring 5 and the outer elastic ring 6 to transmit force between the outer and inner rings of the small ball bearing 1, applying an initial axial force backward to the thrust bearing 3. This initial force ultimately acts on the rotor shaft 2. Under low aerodynamic load conditions, when the backward axial force on the thrust bearing 3 decreases or even becomes forward, the inner elastic ring 5 and the outer elastic ring 6 can maintain the application of a backward axial force to the thrust bearing 3 through their elastic action, thereby preventing the thrust bearing 3 from slipping. Under high aerodynamic load conditions, when the rotor axial load becomes large enough, the rotor shaft 2, along with the thrust bearing 1, moves backward, and the inner elastic ring 5 and the outer elastic ring 6 disengage from the thrust bearing 3, no longer generating a backward axial force on the thrust bearing 3. This control and disengagement from the influence of the rotor axial load under aerodynamic load conditions ensures the balance requirements under aerodynamic load conditions.

[0034] In the aero-engine rotor axial load pre-balancing structure disclosed in the above embodiments, the design utilizes the inner elastic ring 5 and the outer elastic ring 6 to apply an initial force along the axial direction to the thrust bearing 3, thereby adjusting the rotor axial load. This can take into account both small and large aerodynamic load conditions, involves only improvements to the cold end components, and the modifications are small, located near the thrust bearing 3, with low technical risks and no safety issues, thus ensuring the aero-engine's aerodynamic performance.

[0035] In some optional embodiments, in the above-mentioned pre-balanced axial load structure of the aero-engine rotor, considering the effective force transmission through the small ball bearing 1 along the axial direction to the rear, the front section of the inner ring of the small ball bearing 1 is removed, leaving only the rear section. This can reduce the difficulty of machining and assembly and its weight. Furthermore, the rear end of the rear section can be designed to be integrally formed on the front end of the inner ring of the thrust bearing 3, that is, the small ball bearing 1 and the thrust bearing 3 are designed to share the same inner ring, which can further simplify the structure, facilitate machining and assembly, and reduce weight.

[0036] In some optional embodiments, in the above-mentioned pre-balanced structure for axial load of the aero-engine rotor, there is a large gap between the inner ring of the inner elastic ring 5 and the inner ring of the outer elastic ring 6 and the rotor shaft 2, and a small gap between the outer ring and the balancing positioning ring 7. This can ensure the installation and positioning of the inner elastic ring 5 and the outer elastic ring 6, and provide sufficient space for the deformation of the inner elastic ring 5 and the outer elastic ring 6.

[0037] In some alternative embodiments, in the above-described pre-balanced structure for axial load on the aero-engine rotor, the balancing positioning ring 7 is bolted to the thrust bearing housing 4.

[0038] In some optional embodiments, in the above-described pre-balanced structure for axial load of the aero-engine rotor, the balancing positioning ring 7 and the thrust bearing seat 4 are positioned by a stop.

[0039] In some optional embodiments, the above-described aero-engine rotor axial load pre-balancing structure further includes:

[0040] Adjusting shim 8 is fitted around the outer circumference of rotor shaft 2, located between the outer edge of inner elastic ring 5 and the front end of outer ring of small ball bearing 1. In specific applications, adjusting shims 8 of different thicknesses can be selected for assembly according to actual needs to adjust the magnitude of the initial axial backward force applied to thrust bearing 3.

[0041] In practice, the fit between the rotor shaft 2, the thrust bearing 3, and the thrust bearing housing 4 also involves other corresponding structures used for positioning, lubrication, and cooling of the thrust bearing 3. This part is not related to the core of the aero-engine rotor axial load pre-balancing structure provided in this application, and is only briefly described here without further detailed explanation. The specific structure can be designed in detail by relevant technical personnel according to actual needs.

[0042] 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.

[0043] 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 pre-balanced structure for axial load on an aero-engine rotor, characterized in that, include: A small ball bearing (1) is fitted around the outer circumference of the rotor shaft (2) and located in front of the thrust bearing (3); The inner elastic ring (5) is sleeved on the rotor shaft (2) and located in front of the small ball bearing (1), with its side wall tilted backward. The outer elastic ring (6) is sleeved on the rotor shaft (2) and located in front of the inner elastic ring (5), with its sidewall tilted forward. The balance positioning ring (7) is fitted around the inner elastic ring (5) and the outer elastic ring (6) and connected to the thrust bearing seat (4). The inner side has an annular balance positioning protrusion. The annular balance positioning protrusion presses on the outer edge of the outer elastic ring (6), so that the center of the outer elastic ring (6) abuts against the center of the inner elastic ring (5), thereby pressing the outer edge of the inner elastic ring (5) against the front end of the outer ring of the small ball bearing (1), thereby pressing the rear end of the inner ring of the small ball bearing (1) against the front end of the inner ring of the thrust bearing (3), and applying a rearward axial force to the thrust bearing (3).

2. The aero-engine rotor axial load pre-balancing structure according to claim 1, characterized in that, The front section of the inner ring of the small ball bearing (1) is removed, and the rear end of the rear section is integrally formed on the front end of the inner ring of the thrust bearing (3).

3. The aero-engine rotor axial load pre-balancing structure according to claim 1, characterized in that, There is a large gap between the inner ring of the inner elastic ring (5) and the rotor shaft (2), and a small gap between the outer ring and the balance positioning ring (7).

4. The aero-engine rotor axial load pre-balancing structure according to claim 1, characterized in that, The balance positioning ring (7) is bolted to the thrust bearing housing (4).

5. The aero-engine rotor axial load pre-balancing structure according to claim 1, characterized in that, The balance positioning ring (7) and the thrust bearing housing (4) are positioned by a stop.

6. The aero-engine rotor axial load pre-balancing structure according to claim 1, characterized in that, Also includes: Adjustment shim (8) is fitted on the outer circumference of rotor shaft (2), located between the outer edge of inner elastic ring (5) and the front end of outer ring of small ball bearing (1).

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