Impact load deformation self-adaptive rotor-supporting structure of aero-engine

Abstract

The invention discloses an aero-engine impact load deformation self-adaptive rotor-supporting structure, and belongs to the technical field of aero-engine bearing structure design. Comprising a rotor journal, a bearing, a bearing seat, a turn-back bushing, metal rubber and a sleeve. The rotor journal is used for transmitting rotor load, the bearing outer ring is installed on the bearing seat, the section of the turn-back lining is in a U shape, one end of the inner layer of the turn-back lining abuts against a shaft shoulder of the rotor journal, the other end of the turn-back lining presses and fixes the bearing inner ring through the nut and the sleeve, and the metal rubber is arranged in an interlayer of the turn-back lining. The turn-back bushing can reduce the rotor-bearing angular rigidity, allows larger angular misalignment, and reduces the load transmitted to the bearing and a force bearing system; the metal rubber can dissipate impact energy when the turn-back lining deforms. The turn-back lining and different inner rings can be combined in various modes, for example, the turn-back lining and the first inner ring can be manufactured into a whole, and when the turn-back lining is matched with the second inner ring or the third inner ring, a flexible lining can be matched to further reduce rigidity. By means of the structure, the safety and reliability of the aero-engine under the impact load are effectively improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine bearing structure design, and in particular to an aircraft engine impact load deformation adaptive rotor-support structure. Background Art

[0002] With the increasing demand for high performance and high reliability of aviation power systems, aviation gas turbines must not only operate at higher speeds and higher loads, but also have lightweight structural features. This trend makes it difficult for traditional design ideas based on the assumption of rigid rotor motion to meet the needs of advanced high-speed aircraft engines. Compared with the relatively low-speed engines with small rotor bending deformation in the past, today's high-speed rotors with thin-walled structures are more flexible and more prone to bending deformation.

[0003] When the aircraft encounters various complex working conditions (such as maneuvers, overloads, hard landings, and blade loss), the rotor is subjected to a large impact load, causing the rotor to bend and deform significantly and present a more complex shape. At this time, the rotor fulcrum often has a significant tilt angle, causing the inner and outer rings of the bearing to be misaligned, causing the bearing rollers and retainers to be strongly squeezed, which in turn causes damage or even destruction. At the same time, the tilt of the fulcrum will also cause the oil film damper to deflect, weakening or even losing its original vibration reduction 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 rotor design of the new generation of high-speed aircraft engines, it is necessary to introduce design measures on the fulcrum structure that can resist large impact loads and the angular tilt deformation of the rotor structure caused by them, to ensure that when extreme flight conditions such as overload and impact occur, the rotor fulcrum can effectively reduce the impact load and cope with the tilting movement, thereby reducing damage to bearings and other components and improving the overall safety and reliability of the aircraft engine. Summary of the invention

[0005] The purpose of the present invention is to provide an aircraft engine impact load deformation adaptive rotor-support structure, which solves the problem that when the high-speed rotor of the aircraft engine is subjected to an impact load, the bending deformation of the rotor drives the tilting movement of the fulcrum and the impact load causes damage to the load-bearing structure system.

[0006] To achieve the above object, the present invention provides an aero-engine impact load deformation adaptive rotor-support structure, comprising: The rotor journal is a part of the rotor structure of an aircraft engine, used to install bearings and transfer rotor loads to the load-bearing system; A bearing, comprising a bearing inner ring and a bearing outer ring, wherein the bearing inner ring comprises one of inner ring one, inner ring two or inner ring three, and the bearing outer ring is assembled on a bearing seat through an integrated flange and bolts; The bearing housing, which is a part of the load-bearing system of an aero-gas turbine, is used to support the bearing and bear the load from the rotor structure; The return bushing, one end of the inner layer of which abuts against the shoulder of the rotor journal, and the other end is tightened and pressed by the axial tightening nut one, the axial tightening nut two and the sleeve, to fix the inner ring one, the inner ring two or the inner ring three; The metal rubber is installed in the sandwich layer between the inner layer and the outer layer of the return bushing and is an impact-resistant damping material woven with metal wires; when the return bushing deforms under the action of an impact load, it squeezes the metal rubber and dissipates the impact energy; The sleeve is used to cooperate with the axial tightening nut one and the axial tightening nut two to apply an axial pressing force to the return bushing and the metal rubber.

[0007] Preferably, the cross-section of the return bushing is a "C" - shaped structure.

[0008] Preferably, a flange is machined on the inner surface of the outer layer of the return bushing, which is used to radially squeeze the metal rubber when the return bushing deforms, so as to further dissipate the impact energy.

[0009] Preferably, the return bushing and the inner ring one of the bearing are made into an integral structure to reduce the assembly links and discontinuous interfaces and improve the stability of the mechanical properties of the local part of the bearing.

[0010] Preferably, when the return bushing is in cooperation 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 return bushing is reduced, thereby expanding the allowable range of misalignment.

[0011] Preferably, the metal rubber is fixed axially by the axial tightening nut one, the axial tightening nut two and the edge on the return bushing, so that the return bushing can effectively squeeze the metal rubber when bearing bending and impact deformation, and reduce the load and energy transmitted to the bearing and the load-bearing system.

[0012] Preferably, the rotor journal and the return bushing cooperate to achieve radial centering, and the axial limit is provided by the shoulder to ensure the positioning reliability of the return bushing under the action of high-speed rotation of the rotor and impact load.

[0013] Preferably, under the action of high-speed impact load and when the rotor undergoes bending deformation, the structure can significantly reduce the angular moment coupling between the rotor and the bearing housing, enhance the protection effect on the bearing and the load-bearing system, and improve the overall safety and reliability of the aero-engine.

[0014] Therefore, an aero-engine impact load deformation adaptive rotor - support structure adopting the above structure has the following beneficial effects: (1) The present invention can reduce the angular stiffness between the rotor and the bearing by means of the folded bushing, thereby allowing a larger angular misalignment between the rotor and the bearing seat, and can reduce the load transmitted to the bearing and the load-bearing system.

[0015] (2) The present invention adds a metal rubber structure at the position of the return structure to dissipate vibration energy and the load transmitted to the load-bearing system by utilizing the impact damping effect.

[0016] (3) The present invention can further reduce the angular stiffness and increase the allowable misalignment angle by adding a flexible bushing with a boss.

[0017] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of the aero-engine impact load deformation adaptive rotor-support structure in Example 1; Figure 2 is a schematic diagram of an aero-engine impact load deformation adaptive rotor-support structure in Example 2; Figure 3 is a schematic diagram of an aero-engine impact load deformation adaptive rotor-support structure in Example 3; Figure 4 is a schematic diagram of the three-dimensional structure of a flexible bushing with a boss and low angular stiffness in Example 3; Reference numerals 1. Rotor journal, 2. Bearing, 3. Axial tightening nut 1, 4. Bearing seat, 5. Integrated flange, 6. Bearing outer ring 7. Bolts, 8A. Bearing inner ring 1, 8B. Bearing inner ring 2, 8C. Bearing inner ring 3, 9. Return bushing, 10. Axial tightening nut 2, 11. Metal rubber, 12. Sleeve, 13. Flange, 14. Flange, 15. Flexible bushing, 16. Positioning sleeve, 17. Inner boss, 18. Outer boss. DETAILED DESCRIPTION

[0019] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0020] Unless otherwise defined, the technical terms or scientific terms used in the present invention shall have the ordinary meanings understood by those of ordinary skill in the field to which the present invention pertains. The "first", "second" and similar terms used in the present invention do not denote any order, quantity or importance, but are only used to distinguish different components. Words such as "comprising" or "including" mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects. Words such as "connected" or "coupled" are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Upper", "lower", "left", "right", etc. are only used to represent relative positional relationships. When the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0021] Embodiment 1 As Figure 1 shown, an impact load deformation adaptive rotor-bearing structure for an aero-engine provided by the present invention includes a rotor journal 1, a bearing 2, an axial tightening nut 3, a bearing housing 4, a return bushing 9, metal rubber 11, and a sleeve 12.

[0022] The rotor journal 1 is part of the rotor structure of an aero-gas turbine and is used to realize the restraint and fixation of the rotor structure. The bearing housing 4 is part of the load-bearing system of the aero-gas turbine and is used to install and support the rotor structure.

[0023] The return bushing 9 is a thin-walled ring-shaped structure with a "C"-shaped cross-section feature, which is composed of an inner layer, an outer layer, and a thin-walled return shell. The return structure has the advantage of being structurally compact. At the same time, the thin-walled return shell can effectively reduce the angular stiffness. When the rotor is subjected to an impact load, there may be a large angular tilt and misalignment between the rotor journal 1 and the bearing housing 4 due to the bending deformation of the rotor. Adopting the return structure to reduce the angular stiffness can effectively increase the allowable misalignment angle of the structure and reduce the load transmitted to the bearing and the load-bearing system.

[0024] The return bushing 9 is radially centered with the rotor journal 1 through a cylindrical mating surface. One end of it abuts against the shoulder of the rotor journal 1, and the other end is axially pressed against the sleeve 12 under the tightening action of the axial tightening nut 3, realizing axial positioning, fixation, and transmission of the axial load.

[0025] The outer ring 6 of the bearing 2 is installed on the bearing housing 4 through a flange 5 and bolts 7; the inner ring 8A is installed on the return bushing 9, and the axial fixation constraint of the bearing is realized through the flanging of the return bushing 9 and the tightened axial tightening nut 10. In terms of load transmission, the load on the rotor can be transmitted from the journal 1 to the bearing 2 through the return bushing 9, then to the bearing housing 4, and further to the load-bearing system to realize the external transmission of the load.

[0026] The metal rubber 11 is a kind of impact-resistant damping material woven with metal wires, installed in the interlayer between the inner layer and the outer layer of the return bushing 9, and axially fixed by the axial tightening nut 3 under the compression of the sleeve 12 and the flange 13 on the return bushing 9. When the return bushing 9 is deformed under the 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 processed 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 is deformed, the metal rubber 11 is squeezed through the flange 14.

[0027] 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.

[0028] Example 2 like Figure 2 As shown, in this embodiment, the return bushing 9 and the bearing inner ring 8B can be processed into an integral structure, reducing assembly steps and discontinuous interfaces, and improving the stability of the local mechanical properties of the bearing.

[0029] Example 3 like Figure 3 As shown, in this embodiment, the integrated structure of the return bushing and the inner ring of the bearing can be used with the inner ring 8C in combination with the flexible bushing 15 with a boss, which can 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 as shown in FIG. Figure 4 The inner surface and outer surface of the flexible bushing 15 are respectively provided with a plurality of evenly arranged inner bosses 17 and a plurality of outer bosses 18.

[0030] Therefore, the present invention adopts the above-mentioned aircraft engine impact load deformation adaptive rotor-support structure by designing a return structure between the rotor and the bearing to reduce the angular stiffness of the rotor-bearing structure, so that under the action of the impact load, the angular tilting moment of the rotor bending deformation acting on the bearing and the load-bearing system is reduced, and by installing a metal rubber structure in the return structure, the structural design can attenuate the impact load when subjected to rotation, impact and other loads, thereby reducing the load and energy transmitted to the bearing.

[0031] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. An aero-engine impact load deformation adaptive rotor-support structure, characterized in that: Comprising: A rotor journal, which is part of the rotor structure of an aeroengine, used for installing bearings and transferring 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 1, Inner Ring 2 or Inner Ring 3. The outer bearing ring is assembled on the bearing housing through an integral flange and bolts; A bearing housing, which is part of the load-bearing system of an aero gas turbine, used for supporting the bearing and bearing the loads from the rotor structure; A return bushing, one end of the inner layer of which abuts against the shoulder of the rotor journal, and the other end is tightened and pressed by an axial tightening nut 1, an axial tightening nut 2 and a sleeve to fix Inner Ring 1, Inner Ring 2 or Inner Ring 3; Metal rubber, installed in the sandwich layer between the inner layer and the outer layer of the return bushing, which is an impact-resistant damping material woven with metal wires; A sleeve, used to cooperate with the axial tightening nut 1 and the axial tightening nut 2 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: The cross-section of the return bushing is a "C" - shaped structure.

3. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: Flanges are machined on the inner surface of the outer layer of the return bushing, used to squeeze the metal rubber in the radial direction when the return bushing deforms.

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

5. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: When the return bushing cooperates with Inner Ring 2 or Inner Ring 3 of the bearing, Inner Ring 2 or Inner Ring 3 is paired with a flexible bushing with a boss to reduce the overall angular stiffness of the return bushing.

6. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: The metal rubber is fixed in the axial direction by the axial tightening nut 1, the axial tightening nut 2 and the edge on the return bushing, used to enable the return bushing to effectively squeeze the metal rubber when bearing bending and impact deformation, and reduce the loads and energy transmitted to the bearing and the load-bearing system.

7. The aero-engine impact load deformation adaptive rotor-support structure according to claim 1, characterized in that: The return bushing has a low angular stiffness, used to reduce the torque transmitted to the bearing and the load-bearing system when the rotor generates bending deformation and axial tilt.

8. 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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