Aeroengine impact load deformation adaptive rotor-bearing structure

Abstract

The application discloses an aero-engine impact load deformation self-adaptive rotor-supporting structure and belongs to the technical field of bearing structure design of aero-engines. The aero-engine impact load deformation self-adaptive rotor-supporting structure comprises a rotor shaft neck, a bearing, a bearing seat, a turn-back bushing, metal rubber and a sleeve. The rotor shaft neck is used for transmitting the rotor load, the outer ring of the bearing is installed on the bearing seat, the cross section of the turn-back bushing is in the shape of a Chinese character 'fang', one end of the inner layer of the turn-back bushing is located on the shaft shoulder of the rotor shaft neck, the other end of the inner layer of the turn-back bushing is tightly fixed on the inner ring of the bearing through a nut and the sleeve, and the metal rubber is arranged in the interlayer of the turn-back bushing. The turn-back bushing can reduce the angular stiffness of the rotor-bearing system, allow greater angular misalignment and reduce the load transmitted to the bearing and the load-bearing system. The metal rubber can dissipate impact energy when the turn-back bushing is deformed. The turn-back bushing and the different inner rings have various combination modes, for example, the turn-back bushing and the inner ring one can be integrated, and when the turn-back bushing is matched with the inner ring two or three, a flexible bushing can be matched to further reduce the stiffness. The structure effectively improves the safety and reliability of the aero-engine under impact load.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of bearing structure design of aero-engines, and particularly relates to aero-engine impact load deformation self-adaptive rotor-supporting structure. BACKGROUND

[0002] With the increasing demand for high performance and high reliability of the aviation power system, the aviation gas turbine not only needs to work at higher speed and higher load, but also needs to have the structural characteristics of lightweight. This trend makes it difficult for the traditional design idea based on the rigid rotor motion assumption to meet the needs of advanced high-speed aero-engines. Compared with the past engines with relatively low speed and small rotor bending deformation, the high-speed rotor with thin-walled structure is more flexible and more prone to bending deformation.

[0003] When the aircraft encounters various complex working conditions (such as maneuvering, overloading, hard landing and blade fly-off, etc.), the rotor is subjected to a large impact load, resulting in significant bending deformation of the rotor and a more complex shape. At this time, the bearing point of the rotor often has a significant inclination angle, causing the inner and outer rings of the bearing to be misaligned, causing the bearing rollers and cages to be subjected to strong extrusion, and further causing damage or even destruction. At the same time, the inclination of the bearing point also causes the oil film damper to be deflected, weakening or even losing its original damping effect; in addition, since the load acting on the rotor is ultimately borne by the load-bearing system, excessive impact may also cause damage to the load-bearing system.

[0004] Therefore, for the design of the rotor of the new generation of high-speed aero-engines, design measures that can resist large impact loads and the angular tilting deformation of the rotor structure caused by the impact loads need to be introduced on the bearing point structure to ensure that when overloading, impact and other extreme flight states occur, the bearing point of the rotor can effectively reduce the impact load and respond to the tilting motion, thereby reducing damage to the bearing and other components and improving the overall safety and reliability of the aero-engine. SUMMARY

[0005] The purpose of the present application is to provide an aero-engine impact load deformation self-adaptive rotor-supporting structure, which solves the problem of rotor bending deformation driving bearing point tilting motion and impact load causing damage to the load-bearing structure system when the high-speed rotor of the aero-engine is subjected to impact load.

[0006] To achieve the above purpose, the present application provides an aero-engine impact load deformation self-adaptive rotor-supporting structure, comprising:

[0007] The rotor journal is part of the rotor structure of the aero-engine, used for installing the bearing and transmitting the rotor load to the load-bearing system;

[0008] A bearing, comprising a bearing inner ring and a bearing outer ring, the bearing inner ring comprising one of inner ring one, inner ring two or inner ring three, the bearing outer ring being assembled on a bearing seat through an integral flange and bolts;

[0009] A bearing seat, being a part of a load bearing system of an aero gas turbine, for supporting a bearing and carrying loads from a rotor structure;

[0010] A turn-back bushing, one end of an inner layer of which is abutted against a shoulder of the rotor journal, and the other end is compressed and fixed against the inner ring one, the inner ring two or the inner ring three through axial tightening nuts one and two and a sleeve;

[0011] A metal rubber, being a shock-resistant damping material woven by metal wires, installed in a sandwich layer between the inner layer and the outer layer of the turn-back bushing, and being extruded and dissipating impact energy when the turn-back bushing is deformed under impact load;

[0012] A sleeve, for applying axial compression force to the turn-back bushing and the metal rubber in cooperation with the axial tightening nuts one and two.

[0013] Preferably, the cross section of the turn-back bushing is a "H" shaped structure.

[0014] Preferably, a flange is processed on the inner surface of the outer layer of the turn-back bushing, for extruding the metal rubber in the radial direction when the turn-back bushing is deformed, so as to further dissipate impact energy.

[0015] Preferably, the turn-back bushing is integrated with the inner ring one of the bearing, so as to reduce assembly steps and non-continuous interfaces, and improve the stability of the mechanical properties of the bearing.

[0016] Preferably, when the turn-back bushing is matched with the inner ring two or the inner ring three of the bearing, the inner ring two or the inner ring three is matched with a flexible bushing with a boss, so that the overall angular stiffness of the turn-back bushing is reduced, thereby expanding the misalignment tolerance range.

[0017] Preferably, the metal rubber is fixed in the axial direction through the axial tightening nuts one and two and the stopper on the turn-back bushing, so that the turn-back bushing can effectively extrude the metal rubber when subjected to bending and impact deformation, thereby reducing the load and energy transmitted to the bearing and the load bearing system.

[0018] Preferably, the rotor journal is matched with the turn-back bushing to realize radial centering, and the shoulder provides axial limiting, so as to ensure the positioning reliability of the turn-back bushing under the action of high-speed rotation and impact load of the rotor.

[0019] Preferably, under the action of high-speed impact load and the bending deformation of the rotor, the structure can significantly reduce the angular torque coupling between the rotor and the bearing seat, enhance the protection of the bearing and the bearing system, and improve the overall safety and reliability of the aero-engine.

[0020] Therefore, the aero-engine impact load deformation self-adaptive rotor-supporting structure with the above structure has the following beneficial effects:

[0021] (1) The aero-engine impact load deformation self-adaptive rotor-supporting structure can reduce the angular stiffness between the rotor and the bearing through the return sleeve, thereby allowing a larger angular misalignment between the rotor and the bearing seat and reducing the load transmitted to the bearing and the bearing system.

[0022] (2) The aero-engine impact load deformation self-adaptive rotor-supporting structure can dissipate vibration energy and load transmitted to the bearing system through the metal rubber structure added at the position of the return structure.

[0023] (3) The aero-engine impact load deformation self-adaptive rotor-supporting structure can further reduce the angular stiffness and increase the allowable misalignment angle through the flexible sleeve with a boss.

[0024] The technical solutions of the present application will be further described in detail below with reference to the drawings and examples. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 is a schematic diagram of the aero-engine impact load deformation self-adaptive rotor-supporting structure in Example 1;

[0026] Figure 2 is a schematic diagram of the aero-engine impact load deformation self-adaptive rotor-supporting structure in Example 2;

[0027] Figure 3 is a schematic diagram of the aero-engine impact load deformation self-adaptive rotor-supporting structure in Example 3;

[0028] Figure 4 is a three-dimensional structure schematic diagram of the flexible sleeve with a boss in Example 3 with low angular stiffness;

[0029] REFERENCE NUMERALS

[0030] 1, rotor shaft journal, 2, bearing, 3, axial tightening nut one, 4, bearing seat, 5, integral flange, 6, bearing outer ring, 7, bolt, 8A, bearing inner ring one, 8B, bearing inner ring two, 8C, bearing inner ring three, 9, return sleeve, 10, axial tightening nut two, 11, metal rubber, 12, sleeve, 13, flange, 14, flange, 15, flexible sleeve, 16, positioning sleeve, 17, inner boss, 18, outer boss. DETAILED DESCRIPTION

[0031] The technical solutions of the present application are further described below with reference to the accompanying drawings and examples.

[0032] Unless otherwise defined, technical terms or scientific terms used in the present application shall have the ordinary meaning understood by a person with ordinary skill in the art to which the present application belongs. The terms "first", "second" and similar words used in the present application do not represent any order, number or importance, but are only used to distinguish different components. The terms "include" or "contain" and similar words mean that the elements or objects before the words cover the elements or objects listed after the words and their equivalents, without excluding other elements or objects. The terms "connect" or "connected" and similar words are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. The terms "up", "down", "left", "right" and the like are only used to represent relative positional relationships, which can change accordingly when the absolute positions of the described objects change.

[0033] Example 1

[0034] As shown in Figure 1 The present application provides an aero-engine impact load deformation adaptive rotor-support structure, which comprises a rotor shaft neck 1, a bearing 2, an axial tightening nut 3, a bearing seat 4, a return bushing 9, a metal rubber 11 and a sleeve 12.

[0035] The rotor shaft neck 1 is part of the rotor structure of an aero-gas turbine, which is used to constrain and fix the rotor structure. The bearing seat 4 is part of the load-bearing system of an aero-gas turbine, which is used to install and support the rotor structure.

[0036] The return bushing 9 is a thin-walled ring structure with a "U" shaped cross-sectional feature, which is composed of an inner layer, an outer layer and a thin-walled return shell. The return structure has the advantage of compact structure, and the thin-walled return shell can effectively reduce the angular stiffness. When the rotor is subjected to impact load, a large angular tilt eccentricity may occur between the rotor shaft neck 1 and the bearing seat 4 due to the bending deformation of the rotor. The use of the return structure to reduce the angular stiffness can effectively improve the allowable misalignment angle of the structure and reduce the load transmitted to the bearing and the load-bearing system.

[0037] The return bushing 9 is radially centered by being matched with the rotor shaft neck 1 through a cylindrical matching surface. One end of the return bushing 9 is located on the shaft shoulder of the rotor shaft neck 1, and the other end is axially pressed against the sleeve 12 under the tightening action of the axial tightening nut 3, thereby realizing axial positioning, fixation and transmission of axial load.

[0038] The outer ring 6 of bearing 2 is mounted on the bearing seat 4 via flange 5 and bolts 7. The inner ring 8A is mounted on a folded bushing 9. The bearing is axially secured by the flange of the folded bushing 9 and the tightened axial tightening nut 10. Regarding load transmission, the rotor load is transferred from the journal 1 through the folded bushing 9 to the bearing 2, then to the bearing seat 4, and further to the load-bearing system, achieving external load transmission.

[0039] Metal rubber 11 is a shock-resistant damping material woven from metal wire. It is installed in the interlayer between the inner and outer layers of the return bushing 9. Axial fixation is achieved by axially tightening nut 13 to compress sleeve 12 and flange 13 on the return bushing 9. When the return bushing 9 deforms under the action of an impact load, the return bushing 9 can squeeze the metal rubber 11 and dissipate the impact energy, reducing the load and energy transmitted to the bearing 2 and the load-bearing system. A flange 14 is machined on the inner surface of the outer layer of the return bushing 9 to compress the metal rubber 11 in the radial direction. When the return bushing 9 deforms, the metal rubber 11 is squeezed through the flange 14.

[0040] When high-speed impact loads act and the rotor bends and deforms, the structure can significantly reduce the angular torque coupling between the rotor and the bearing seat 4, enhance the protection of the bearing and the load-bearing system, and improve the overall safety and reliability of the aircraft engine.

[0041] Example 2

[0042] like Figure 2 As shown, in this embodiment, the folded bushing 9 and the bearing inner ring 2 8B can be processed into an integrated structure, reducing assembly processes and discontinuous interfaces, and improving the stability of the local mechanical properties of the bearing.

[0043] Example 3

[0044] like Figure 3 As shown in the figure, in this embodiment, the integrated structure of the return bushing and the bearing inner ring can be used with the flexible bushing 15 with a boss on the inner ring 8C to reduce the angular stiffness and the allowable misalignment angle to a greater extent. A positioning sleeve 16 is provided on one side of the flexible bushing 15 and the rib 13. The structure of the flexible bushing 15 is shown in FIG. Figure 4 The inner surface and outer surface of the flexible bushing 15 are respectively provided with a plurality of inner bosses 17 and a plurality of outer bosses 18 that are evenly arranged.

[0045] Therefore, the application adopts the above-mentioned aero-engine impact load deformation self-adaptive rotor-supporting structure to reduce the angular rigidity of the rotor-bearing structure by designing a turn-back structure between the rotor and the bearing, so that the angular tilting moment of the rotor bending deformation acting on the bearing and the load-bearing system under the impact load is reduced, and the metal rubber structure is installed in the turn-back structure, so that the structure can attenuate the impact load when subjected to rotation, impact and other loads, and reduce the load and energy transmitted to the bearing.

[0046] Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present application and not to limit them. Although the present application has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present application can still be modified or replaced by equivalents, and these modifications or replacements cannot make the modified technical solutions deviate from the spirit and scope of the technical solutions of the present application.

Claims

1. An aero-engine impact load deformation adaptive rotor-support structure, characterized in that: Comprising: A rotor journal, which is a part of the rotor structure of an aeroengine, is used for installing bearings and transmitting rotor loads to the load-bearing system; A bearing, including an inner bearing ring and an outer bearing ring. The inner bearing ring includes one of inner ring one, inner ring two or inner ring three. The outer bearing ring is assembled on the bearing housing through an integral flange and bolts; A bearing housing, which is a part of the load-bearing system of an aero-gas turbine, is used for supporting the bearing and bearing the loads from the rotor structure; A return bushing, which is composed of an inner layer, an outer layer and a thin-walled return shell, has a "C" - shaped cross-section. One end of the inner layer abuts against the shoulder of the rotor journal, and the other end of the inner layer is tightened and pressed by an axially tightened nut one and a sleeve to fix inner ring one, inner ring two or inner ring three; Metal rubber, which is installed in the interlayer between the inner layer and the outer layer of the return bushing, is an impact-resistant damping material woven with metal wires; A sleeve, which is used to cooperate with the axially tightened nut one to apply an axial pressing force to the return bushing and the metal rubber.

2. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: A flange is machined on the inner surface of the outer layer of the return bushing, which is used to radially extrude the metal rubber when the return bushing deforms.

3. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: The return bushing and the inner ring one of the bearing are made into an integral structure.

4. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: When the return bushing and the inner ring two or inner ring three of the bearing are in cooperation, the inner ring two or inner ring three is paired with a flexible bushing with a boss, so as to reduce the overall angular stiffness of the return bushing.

5. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: Under the pressing action of the axially tightened nut one in the axial direction, the metal rubber is axially fixed through the edge of the sleeve and the return bushing, which is used to enable the return bushing to effectively extrude the metal rubber when bearing bending and impact deformation, and reduce the loads and energy transmitted to the bearing and the load-bearing system.

6. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: The thin-walled return shell can effectively reduce the angular stiffness, which is used to reduce the torque transmitted to the bearing and the load-bearing system when the rotor generates bending deformation and axial inclination.

7. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: The rotor journal and the return bushing cooperate to achieve radial centering, and the shoulder provides axial limit, ensuring the positioning reliability of the return bushing under the action of high-speed rotation of the rotor and impact loads.

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