CN115435995A - Multimode test room is with simulation aeroengine bearing damage test bench - Google Patents
Multimode test room is with simulation aeroengine bearing damage test bench Download PDFInfo
- Publication number
- CN115435995A CN115435995A CN202210936646.5A CN202210936646A CN115435995A CN 115435995 A CN115435995 A CN 115435995A CN 202210936646 A CN202210936646 A CN 202210936646A CN 115435995 A CN115435995 A CN 115435995A
- Authority
- CN
- China
- Prior art keywords
- squirrel cage
- elastic support
- support
- supporting
- bearing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 35
- 238000004088 simulation Methods 0.000 title claims abstract description 27
- 238000009533 lab test Methods 0.000 claims abstract description 4
- 241000555745 Sciuridae Species 0.000 claims description 36
- 230000006399 behavior Effects 0.000 abstract description 2
- 230000004044 response Effects 0.000 abstract description 2
- 230000001052 transient effect Effects 0.000 abstract description 2
- 238000011160 research Methods 0.000 description 6
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 108010010803 Gelatin Proteins 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229920000159 gelatin Polymers 0.000 description 1
- 239000008273 gelatin Substances 0.000 description 1
- 235000019322 gelatine Nutrition 0.000 description 1
- 235000011852 gelatine desserts Nutrition 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The invention relates to a multimode laboratory test bed for simulating bearing damage of an aircraft engine, which comprises a bracket, a driving motor, a rotating shaft, a gas compressor simulation disc and an air cannon, wherein the bracket is arranged on the bracket; an opening is formed in the side edge of the compressor simulation disc, a lost mass block is detachably mounted in the opening and used for carrying out a simulation aeroengine bearing damage test under the condition that the blade is lost; the air cannon is used for carrying out a test for simulating the damage of the bearing of the aircraft engine under the impact load of bird collision; the test platform can be used for researching the dynamic behaviors of the rotor system such as transient vibration response and the like under the conditions of blade loss and bird impact load.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to a multi-mode test bed for an aero-engine bearing damage test bed for a laboratory.
Background
The rolling bearing in the aero-engine bears high temperature, high speed and high load, and the performance and the reliability of the aero-engine are directly influenced by the fact whether the rolling bearing can normally run or not. The reliability of bearings, which are extremely critical support components for aircraft engines, is of paramount importance. The choice of engine bearings is one of the important factors affecting engine reliability.
Taking a turbofan engine as an example, under the service condition, extreme severe working conditions such as bird collision and blade loss may be encountered, a sudden high-energy load is formed in the engine structure and acts on a bearing component in an axial and circumferential coupling high-density impact energy mode, so that the dynamic characteristics of the whole engine/component of the engine are deteriorated and the bearing component is damaged, the structural safety of other components of the engine is endangered, and the safety and the reliability of the engine during the service period are seriously influenced. According to the load transmission rule of a typical bearing structure of an engine, a key component bearing is an obvious load transmission path between a shaft system and a support, and when extremely severe working conditions such as bird collision, blade loss and the like occur, the key component bearing is often subjected to dynamic load which is several times of that which can be born by the design of the key component bearing.
At present, the bearing damage research of domestic and foreign scholars is mostly on the basis of radial or axial load loading, and the influence of sudden high-energy basic excitation on a key component bearing under extreme severe working conditions such as bird collision, blade loss and the like is not considered. In order to avoid structural damage to an aircraft engine key component bearing caused by sudden high-energy basic load, it is necessary to develop a test research work for simulating a damage mode and a damage margin of a key component bearing of an engine complete machine under a sudden high-energy basic excitation effect under a laboratory condition.
Therefore, a multi-mode test bed for testing the bearing damage of the aircraft engine needs to be designed to solve the problems.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a multi-mode laboratory test bed for simulating damage of an aero-engine bearing, which aims to: the damage mode of the bearing under the impact load of bird collision can be accurately realized; the damage mode of the bearing under the condition that the blade loses load can be accurately realized.
The technical scheme is as follows: a multimode test bench for simulating bearing damage of an aeroengine in a laboratory comprises a bracket, a driving motor, a rotating shaft, a compressor simulation disc coaxially arranged in front of the rotating shaft, a front supporting squirrel cage elastic support, a middle supporting squirrel cage elastic support, a rear supporting squirrel cage elastic support and an air cannon; the front supporting squirrel cage elastic support, the middle supporting squirrel cage elastic support and the rear supporting squirrel cage elastic support are detachably arranged on the rotating shaft, and the front supporting squirrel cage elastic support, the middle supporting squirrel cage elastic support and the rear supporting squirrel cage elastic support are connected with the rotating shaft through bearings; an opening is formed in the side edge of the compressor simulation disc, and a lost mass block is detachably mounted in the opening; the air cannon is positioned in front of the compressor simulation disc, and a cannon mouth of the air cannon faces the compressor simulation disc.
Has the beneficial effects that: the invention discloses a multimode laboratory-used test bed for simulating bearing damage of an aero-engine, which can realize accurate simulation of bearing damage of key members of the aero-engine under sudden high-energy loads such as bird collision, blade loss and the like in a laboratory;
the blade loss system adopted by the invention can realize working conditions such as different blade loss masses, different blade loss rotating speeds and the like, and can be used for experimental research work of damage of unbalanced load to a key component bearing of an aeroengine after blade loss in a laboratory;
the air cannon system adopted by the invention can accurately launch gelatin bird bullets with different masses and different impact speeds, and can be used for experimental research work of damage of sudden high-energy loads such as bird collision and the like to the bearings of the key components of the aeroengine in a laboratory;
the test platform has strong reliability, convenient assembly and disassembly and high design flexibility, and can select reasonable roller bearings, ball bearings or other specific types of bearings according to the specific supporting form of the model of the aero-engine; the damage mode and damage margin test research work of different types of bearings under sudden high-energy load can be realized by designing and replacing the rotating shaft and the squirrel cage elastic support.
The test platform can be used for researching the dynamic behaviors of the rotor system such as transient vibration response and the like under the conditions of blade loss and bird impact load.
Drawings
FIG. 1 is a schematic view of a multimode laboratory test rig for simulating aero-engine bearing damage;
FIG. 2 is a schematic view of a test stand for simulating aero-engine bearing damage under bird impact load;
FIG. 3 is a schematic view of a test stand for simulating aero-engine bearing damage under a blade loss load.
Detailed Description
Preferred embodiments of the apparatus and method of the present invention will now be described in further detail with reference to the accompanying drawings.
It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention discloses a multimode test bench for simulating bearing damage of an aircraft engine in a laboratory, which comprises a compressor simulation disk 1, a compressor disk baffle ring 11, a loss mass block 2, a front support ball bearing 3, a ball bearing inner and outer ring baffle ring 31, a front support squirrel cage elastic support 32, a middle support roller bearing 4, a roller bearing inner and outer ring baffle ring 41, a middle support squirrel cage elastic support 42, a rotating shaft 5, a rear support roller bearing 6, a roller bearing inner and outer ring baffle ring 61, a rear support squirrel cage elastic support 62, a flexible coupling 7, a driving motor 8, a test bench foundation 9, a front support seat 91, a middle support seat 92, a rear support seat 93 and an air cannon 10, wherein the front support bearing and the middle support seat 92 are respectively provided with a plurality of bearing inner and outer rings. The driving motor 8 and the rotating shaft 5 are coaxially arranged on the test bed foundation 9 and are coaxially connected with the rotating shaft 5 through the flexible coupling 7. The simulated aircraft engine is arranged on the test bed foundation 9 through a front supporting seat 91, a middle supporting seat 92 and a rear supporting seat 93. The front supporting squirrel cage elastic support 32, the middle supporting squirrel cage elastic support 42 and the rear supporting squirrel cage elastic support 62 are detachably arranged on the rotating shaft 5, so that the damage mode and damage margin test research work of different types of bearings under sudden high-energy load can be conveniently realized by designing and replacing the rotating shaft and the squirrel cage elastic support.
The front support base 91, the middle support base 92, and the rear support base 93 are arranged from front to rear. The front support seat 91 is located behind the compressor simulation disk 1. Wherein the drive motor 8 is mounted on the rear support 93. The rear support cage elastomeric mounts 62 are mounted to the rear of the center support base 92 at a pivot location. The middle supporting squirrel cage elastic support 42 is arranged at the rotating shaft position at the rear part of the front supporting seat 91. The front supporting squirrel cage elastic support 32 is arranged at the position of a rotating shaft at the front part of the front supporting seat 91.
The front supporting ball bearing 3 is fixed and limited by the ball bearing inner and outer ring baffle ring 31 and the front supporting squirrel cage elastic support 32. The middle supporting roller bearing 4 is fixed and limited by the inner and outer ring retaining rings 41 of the roller bearing and the middle supporting squirrel cage elastic support 42. The rear supporting roller bearing 6 is fixed and limited by an inner ring and an outer ring baffle ring 61 of the roller bearing and a rear supporting squirrel cage elastic support 62.
As can be seen from fig. 2, the air cannon 10 is installed on the front of the compressor simulation disk 1, and the muzzle of the air cannon faces the compressor simulation disk 1. The cross section of the muzzle is parallel to the disc surface of the compressor simulation disc and is arranged at a certain distance from the compressor simulation disc 1, and under the mode, a simulation aeroengine bearing damage test can be performed under the impact load of bird collision.
As can be seen from fig. 3, the missing mass 2 includes two pieces, which are respectively installed on two side edges of the simulation disk 1 of the compressor. The blade loss system can be used for realizing application of unbalanced load of blade loss under specific loss mass and specific working rotating speed, and under the mode, a simulation aeroengine bearing damage test under the load of blade loss can be developed.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A multimode laboratory is with simulating aeroengine bearing damage test bench, characterized by, including support, driving motor, spindle, install in the forward compressor simulation dish of spindle coaxially, fore support squirrel cage elastic support, rear support squirrel cage elastic support, air cannon;
the front supporting squirrel cage elastic support, the middle supporting squirrel cage elastic support and the rear supporting squirrel cage elastic support are detachably arranged on the rotating shaft, and the front supporting squirrel cage elastic support, the middle supporting squirrel cage elastic support and the rear supporting squirrel cage elastic support are connected with the rotating shaft through bearings;
an opening is formed in the side edge of the compressor simulation disc, and a lost mass block is detachably mounted in the opening; the air cannon is positioned in front of the compressor simulation disc, and a cannon mouth of the air cannon faces the compressor simulation disc.
2. The simulated aircraft engine bearing damage test bed for the multimode test room as recited in claim 1, wherein said cradle comprises a front support, a middle support, and a rear support arranged from front to rear, the front support being located behind the compressor simulation disk; wherein the driving motor is arranged on the rear supporting seat; the rear supporting squirrel cage elastic support is arranged at the position of a rotating shaft at the rear part of the middle supporting seat; the middle supporting squirrel cage elastic support is arranged at the position of a rotating shaft at the rear part of the front supporting seat; the front supporting squirrel cage elastic support is arranged at the position of a rotating shaft at the front part of the front supporting seat.
3. The simulated aircraft engine bearing damage test bed for the multimode test room as recited in claim 1, wherein the missing mass comprises two masses mounted on opposite side edges of the compressor simulation disk.
4. The multimode laboratory test stand for simulating the damage of the aero-engine bearing according to claim 2, wherein the front support ball bearing is fixed and limited by an inner ring and an outer ring baffle ring of the ball bearing and an elastic support of a front support squirrel cage; the middle supporting roller bearing is fixed and limited by an inner ring and an outer ring of the roller bearing and an elastic support of the middle supporting squirrel cage; the rear supporting roller bearing is fixed and limited through the inner ring and the outer ring baffle ring of the roller bearing and the rear supporting squirrel cage elastic support.
5. The simulated aircraft engine bearing damage test bed for the multimode test room as recited in claim 1, wherein the air cannon is used to perform a simulated aircraft engine bearing damage test under bird strike impact load; the compressor simulation disc is used for carrying out a simulation aeroengine bearing damage test under the blade loss load.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210936646.5A CN115435995A (en) | 2022-08-05 | 2022-08-05 | Multimode test room is with simulation aeroengine bearing damage test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210936646.5A CN115435995A (en) | 2022-08-05 | 2022-08-05 | Multimode test room is with simulation aeroengine bearing damage test bench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115435995A true CN115435995A (en) | 2022-12-06 |
Family
ID=84243421
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210936646.5A Pending CN115435995A (en) | 2022-08-05 | 2022-08-05 | Multimode test room is with simulation aeroengine bearing damage test bench |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115435995A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109540447A (en) * | 2018-11-12 | 2019-03-29 | 中国飞行试验研究院 | Aeroengine fan blades foreign object strike test platform |
| CN111947836A (en) * | 2020-08-17 | 2020-11-17 | 哈电发电设备国家工程研究中心有限公司 | Test device and method for simulating sudden unbalance fault of rotor system |
| CN112014109A (en) * | 2020-07-30 | 2020-12-01 | 南京航空航天大学 | Simulation test device for loss of aero-engine rotor blade |
| WO2022028419A1 (en) * | 2020-08-07 | 2022-02-10 | 上海理工大学 | Method for compiling load spectrum of reliability test for high-speed bearing of electric drive system |
-
2022
- 2022-08-05 CN CN202210936646.5A patent/CN115435995A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109540447A (en) * | 2018-11-12 | 2019-03-29 | 中国飞行试验研究院 | Aeroengine fan blades foreign object strike test platform |
| CN112014109A (en) * | 2020-07-30 | 2020-12-01 | 南京航空航天大学 | Simulation test device for loss of aero-engine rotor blade |
| WO2022028419A1 (en) * | 2020-08-07 | 2022-02-10 | 上海理工大学 | Method for compiling load spectrum of reliability test for high-speed bearing of electric drive system |
| CN111947836A (en) * | 2020-08-17 | 2020-11-17 | 哈电发电设备国家工程研究中心有限公司 | Test device and method for simulating sudden unbalance fault of rotor system |
Non-Patent Citations (2)
| Title |
|---|
| 刘璐璐;杨宗志;陈伟;吴建林;: "航空发动机叶片丢失整机响应及安全性分析" * |
| 朱倬燊: "突加高能载荷试验若干关键技术研究" * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2958060C (en) | Thrust bearing | |
| US10041534B2 (en) | Bearing outer race retention during high load events | |
| CN103528824B (en) | Based on the inner-outer birotor fault simulation experiment table of elastic foundation | |
| EP3287674A1 (en) | Floating, non-contact seal with offset building clearance for load imbalance | |
| GB969579A (en) | Gas turbine engine | |
| CN110926745B (en) | Aero-engine low-pressure turbine rotor and stator blade rub-impact test bed | |
| CN110132556B (en) | Modular turbine test piece and test method thereof | |
| US10316745B2 (en) | Turbomachine fan clutch | |
| EP3536901A1 (en) | Bearing rotor thrust control | |
| CN115435995A (en) | Multimode test room is with simulation aeroengine bearing damage test bench | |
| SE528006C2 (en) | Static gas turbine component and method of repairing such component | |
| US2862654A (en) | Variable pitch guide vanes | |
| CN111751051A (en) | Dynamic balancing method for double-disc flexible rotor of supercharged turbine | |
| US8720259B1 (en) | Device and method for testing a gas turbine engine component | |
| CN112119203A (en) | Rotor balancing method and device | |
| CN113390645B (en) | Special test method for peeling fault of main bearing of aircraft engine | |
| CN109339868B (en) | Turbine model for thermal barrier coating service working condition simulation test | |
| EP4123120A1 (en) | Method for balancing a rotating system | |
| CN114705364B (en) | Laboratory simulation sudden-adding unbalance test device and test method thereof | |
| US20230012799A1 (en) | Vibration response reduction for aircraft engines | |
| Ertas et al. | Thrust bearing | |
| CN115493850A (en) | Aero-engine rub-impact analysis method and device | |
| US20220120291A1 (en) | Damping device for damping shaft vibration | |
| EP3919731A1 (en) | Gas tubine engine with improved dynamic characteristics | |
| Volk | LF336A high pressure ratio lift fans Final report |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20221206 |