Aero-engine rotor axial load pre-control structure

Abstract

The application belongs to the technical field of aero-engine rotor axial load control, and particularly relates to a kind of aero-engine rotor axial load pre-control structure, comprising: small ball bearing, sleeve is set in the outer periphery of rotor shaft, is located in the rear side of roller bearing, and inner ring front end is folded in, and is connected in the rear end of roller bearing inner ring;Support ring, sleeve is set in the outer periphery of small ball bearing, is located in the inner side of roller bearing seat, and rear end has outward annular flange, and inner side has annular adapter convex;A plurality of springs are arranged between support ring and roller bearing seat in the circumferential direction, and are abutted on outward annular flange and roller bearing seat in the circumferential direction, and annular adapter convex is compressed in the front end of small ball bearing outer ring by relying on the elastic force thereof, so as to apply the rear axial force to roller bearing inner ring by small ball bearing inner 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-control 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-control 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-control structure for an aero-engine rotor includes:

[0009] A small ball bearing is fitted around the outer circumference of the rotor shaft, located behind the roller bearing, with the front end of the inner ring folded inward and connected to the rear end of the inner ring of the roller bearing.

[0010] The support ring is fitted around the outer circumference of the small ball bearing and located inside the roller bearing housing. It has an outward annular fold at the rear end and an annular transition protrusion on the inner side.

[0011] Multiple springs are arranged circumferentially between the support ring and the roller bearing housing, and abut against the outward annular flange and the roller bearing housing. Relying on their elastic force, the annular transition protrusion is pressed against the front end of the outer ring of the small ball bearing, thereby applying a rearward axial force to the inner ring of the roller bearing through the inner ring of the small ball bearing.

[0012] According to at least one embodiment of this application, in the above-described aero-engine rotor axial load pre-control structure, the front section of the annular groove on the inner ring of the small ball bearing is removed, leaving a straight section.

[0013] According to at least one embodiment of this application, in the above-described aero-engine rotor axial load pre-control structure, there is a small gap between the outward annular flange and the inner side of the roller bearing housing.

[0014] According to at least one embodiment of this application, in the above-described aero-engine rotor axial load pre-control structure, the rear end of the roller bearing has an outward annular protrusion.

[0015] The front end of the roller bearing housing has an inward annular protrusion, which is located in front of the outward annular protrusion.

[0016] The aero-engine rotor axial load pre-control structure also includes:

[0017] Multiple bolt fasteners, with outward and inward annular protrusions for fastening connections;

[0018] Multiple adjusting shims are placed between each bolt, fastener nut, and outward annular protrusion. Attached Figure Description

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

[0020] in:

[0021] 1-Small ball bearing; 2-Rotor shaft; 3-Roller bearing; 4-Support ring; 5-Roller bearing housing; 6-Spring; 7-Bolt fastener; 8-Adjusting shim.

[0022] 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

[0023] 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.

[0024] 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.

[0025] 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.

[0026] The following is in conjunction with the appendix Figure 1 This application will be described in further detail.

[0027] An axial load pre-control structure for an aero-engine rotor includes:

[0028] A small ball bearing 1 is sleeved on the outer circumference of the rotor shaft 2 and located behind the roller bearing 3. The front end of the inner ring is folded inward and connected to the rear end of the inner ring of the roller bearing 3. Specifically, it can be welded, bolted, or connected by an adapter, or it can be integrally formed. The inner ring of the roller bearing 3 is sleeved on the rotor shaft 2, and the outer ring is installed in the anti-rolling rod bearing housing 5.

[0029] Support ring 4 is sleeved on the outer periphery of small ball bearing 1 and located inside the roller bearing housing 5. It has an outward annular fold at the rear end and an annular transition protrusion on the inner side.

[0030] Multiple springs 6 are arranged circumferentially between the support ring 4 and the roller bearing seat 5, and abut against the outward annular flange and the roller bearing seat 5. Relying on their elastic force, the annular transition protrusion is pressed against the front end of the outer ring of the small ball bearing 1, thereby applying a rearward axial force to the inner ring of the roller bearing 3 through the inner ring of the small ball bearing 1.

[0031] In the aero-engine rotor axial load pre-control structure disclosed in the above embodiments, the elastic action of each inner spring 6 is utilized to transmit force through the support ring 4 between the outer and inner rings of the small ball bearing 1, applying an initial axial backward force to the roller 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 decreases or even becomes forward, each spring 6 can maintain the application of a backward axial force to the roller bearing 3 through its elastic action, thereby preventing the thrust bearing from slipping. Under high aerodynamic load conditions, when the rotor axial load becomes large enough, the rotor shaft 2, along with the roller bearing 3, moves backward, and each spring 6 disengages from the roller bearing 3, no longer generating a backward axial force on the roller 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.

[0032] In the aero-engine rotor axial load pre-balancing structure disclosed in the above embodiments, the design utilizes each spring 6 to apply an initial force along the axial direction to the roller bearing 3 to adjust 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 minor. Located near the roller bearing 3 and at the rear end of the rotor shaft 2, it has a large operating space, is easy to process and assemble, has low technical risks, will not cause safety issues, and can ensure the aerodynamic performance of the aero-engine.

[0033] In some optional embodiments, in the above-mentioned aero-engine rotor axial load pre-control structure, considering the effective force transmission through the small ball bearing 1, the design extends axially backward, and the front section of the annular groove on the inner ring of the small ball bearing 1 is removed, making it a straight section, which can reduce the difficulty of machining and assembly and its weight.

[0034] In some optional embodiments, in the above-described aero-engine rotor axial load pre-control structure, there is a small gap between the outward annular flange and the inner side of the roller bearing housing 5, which can ensure the positioning of the support ring 4 and leave space for the sliding of the support ring 4.

[0035] In some optional embodiments, in the above-described aero-engine rotor axial load pre-control structure, the rear end of the roller bearing 3 has an outward annular protrusion;

[0036] The front end of the roller bearing housing 5 has an inward annular protrusion, which is located in front of the outward annular protrusion.

[0037] The aero-engine rotor axial load pre-control structure also includes:

[0038] Multiple bolt fasteners 7, fastening connections with outward and inward annular protrusions;

[0039] Multiple adjusting shims 8 are placed between the nuts and outward annular protrusions of each bolt fastener 7. In specific applications, adjusting shims 8 of different thicknesses can be selected and assembled according to actual needs to adjust the initial compression of each spring 6 and adjust the magnitude of the initial axial backward force applied to the roller bearing 3.

[0040] In practice, the fit between the rotor shaft 2, the roller bearing 3, and the roller bearing housing 5 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.

[0041] 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.

[0042] 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-control structure for axial load on an aero-engine rotor, characterized in that, include: A small ball bearing (1) is fitted on the outer circumference of the rotor shaft (2) and located on the rear side of the roller bearing (3). The front end of the inner ring is folded inward and connected to the rear end of the inner ring of the roller bearing (3). The support ring (4) is sleeved on the outer periphery of the small ball bearing (1) and located inside the roller bearing housing (5). The rear end has an outward annular folded edge and the inner side has an annular transition protrusion. Multiple springs (6) are arranged circumferentially between the support ring (4) and the roller bearing seat (5), and abut against the outward annular flange and the roller bearing seat (5) in the circumferential direction. Relying on their elastic force, the annular transition protrusion presses against the front end of the outer ring of the small ball bearing (1), thereby applying a backward axial force to the inner ring of the roller bearing (3) through the inner ring of the small ball bearing (1).

2. The aero-engine rotor axial load pre-control structure according to claim 1, characterized in that, The front section of the annular groove on the inner ring of the small ball bearing (1) is removed, leaving a straight section.

3. The aero-engine rotor axial load pre-control structure according to claim 1, characterized in that, There is a small gap between the outward annular fold and the inner side of the roller bearing housing (5).

4. The aero-engine rotor axial load pre-control structure according to claim 1, characterized in that, The rear end of the roller bearing (3) has an outward annular protrusion; The front end of the roller bearing housing (5) has an inward annular protrusion, which is located in front of the outward annular protrusion. The aero-engine rotor axial load pre-control structure also includes: Multiple bolt fasteners (7) are fastened with outward and inward annular protrusions; Multiple adjusting shims (8) are placed between the nuts and outward annular protrusions of each bolt fastener (7).

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