CN107346000B - Test tool for aviation alternating-current generator and application method thereof - Google Patents
Test tool for aviation alternating-current generator and application method thereof Download PDFInfo
- Publication number
- CN107346000B CN107346000B CN201710688116.2A CN201710688116A CN107346000B CN 107346000 B CN107346000 B CN 107346000B CN 201710688116 A CN201710688116 A CN 201710688116A CN 107346000 B CN107346000 B CN 107346000B
- Authority
- CN
- China
- Prior art keywords
- mounting disc
- aviation
- bearing
- current generator
- mounting plate
- 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.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 12
- 125000006850 spacer group Chemical group 0.000 claims abstract description 25
- 230000008878 coupling Effects 0.000 claims abstract description 17
- 238000010168 coupling process Methods 0.000 claims abstract description 17
- 238000005859 coupling reaction Methods 0.000 claims abstract description 17
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052802 copper Inorganic materials 0.000 claims abstract description 6
- 239000010949 copper Substances 0.000 claims abstract description 6
- 230000000694 effects Effects 0.000 claims abstract description 5
- 239000003921 oil Substances 0.000 claims description 28
- 238000011056 performance test Methods 0.000 claims description 25
- 239000010687 lubricating oil Substances 0.000 claims description 3
- 238000005192 partition Methods 0.000 claims description 3
- 238000010248 power generation Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 230000006978 adaptation Effects 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 2
- 230000005540 biological transmission Effects 0.000 description 10
- 230000006872 improvement Effects 0.000 description 8
- 238000009434 installation Methods 0.000 description 5
- 238000002407 reforming Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/34—Testing dynamo-electric machines
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to a test fixture for an aviation alternating-current generator and a use method thereof, and the test fixture comprises a mounting plate and a modified mounting plate connected with the mounting plate, wherein the modified mounting plate is of a hollow structure, a bearing chamber is arranged on the mounting plate, one end of the bearing chamber is connected with a bearing cover, the other end of the bearing chamber is connected with a copper bar, an axially matched spacer bush is sleeved in the middle of the bearing cover, a modified coupling is arranged on the spacer bush, and an oil inlet and outlet joint is arranged on the mounting plate. The invention has stronger operability, can provide corresponding rotating speed and flow, can test the performance of the aviation alternating-current generator by simple operation steps, has easier fault positioning and better effect on the aviation alternating-current generator, and has reasonable design, simple structure, practical combination production and strong operability.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a test tool for an aviation alternating-current generator and a use method thereof.
Background
The aviation generator consists of an aviation alternating-current generator and a constant-speed transmission device, the aviation alternating-current generator is assembled on the constant-speed transmission device for testing in the early repair period of a certain type of aviation generator, and the constant-speed transmission device is assembled with a special flange plate for testing and then performs performance testing with a performance test console. When the performance parameters are unqualified or other faults occur in the product test process, the whole of a certain type of aero-generator is required to be detached, the possibly faulty components are roughly analyzed, the aero-alternator is further separated from the constant speed transmission device, the possibly faulty components are replaced, then the aero-alternator and the constant speed transmission device are assembled, and then the performance test is carried out. If the failure does not recur, it indicates that the replaced component is faulty, and if the failure recurs, it indicates that the failure is present in the component that is not replaced. However, this method of testing the aero-alternator and constant speed drive as a whole is complex in operation and not prone to fault location.
Disclosure of Invention
In order to avoid and solve the technical problems, the invention provides a test tool for an aviation alternator and a use method thereof.
The technical problems to be solved by the invention are realized by adopting the following technical scheme:
the utility model provides a be used for experimental frock of aviation alternator, includes the mounting disc, changes the mounting disc of being connected with the mounting disc, it is hollow structure to change the mounting disc, be equipped with the bearing room on the mounting disc, the one end of bearing room is connected with the bearing cap and the other end is connected with the bar copper, bearing cap middle part cover is equipped with axial complex spacer bush, install the change shaft coupling on the spacer bush, be equipped with into the oil joint on the mounting disc.
As a further improvement of the invention, a reforming clamp with a fixing function is arranged at the joint of the mounting plate and the reforming mounting plate, and the reforming clamp is of a two-connected semicircular structure.
As a further improvement of the invention, the modified mounting plate is provided with a conical screw connected with the performance test platform.
As a further improvement of the invention, the spacer bush is provided with a deep groove ball bearing matched with the bearing chamber.
As a further improvement of the invention, the number of the deep groove ball bearings is two, and a cylindrical bearing spacer with a partition effect is arranged between the deep groove ball bearings.
As a further improvement of the invention, a boss structure is arranged at the joint of the bearing cover and the bearing chamber. The connection part of the mounting plate and the modified mounting plate adopts a boss structure.
As a further improvement of the invention, the spacer bush is provided with a pin for fastening the reformed coupling and a circlip for positioning the spacer bush. The spacer bush is in a cylindrical form.
As a further improvement of the invention, the modified coupling comprises a small spline shaft, a transition shaft and a large spline shaft with a central hole which are connected in sequence. And an O-shaped ring is arranged on the small spline shaft.
As a further development of the invention, the mounting plate is provided with two circular holes.
As a further improvement of the invention, the mounting plate is provided with a hollow pin communicated with the oil inlet and outlet joint. The hollow pin adopts a groove type structure.
A method of use for an aircraft alternator test fixture, the method of use comprising the steps of:
the first step: and connecting the test fixture with a mounting hole on a performance test console through a large spline shaft of the modified coupling, and fixing the test fixture by using a conical screw.
And a second step of: and correspondingly installing an oil inlet and an oil outlet of the aviation alternating-current generator and a hollow pin on the installation disc, and fixing the oil inlet and the oil outlet by using screws.
And a third step of: and the oil inlet and outlet pipelines of the performance test control table are respectively connected with the oil inlet and outlet connectors.
The oil supply mode in the invention is to provide lubricating oil for the aviation alternating-current generator through a motor pump which is arranged on a hydraulic supply source of a performance test console and is controlled by the console, so as to provide required rated flow for aviation alternating-current power generation.
According to the invention, the functional load box is controlled by the performance test console to realize the detection and maintenance of the aviation alternating-current generator.
The beneficial effects of the invention are as follows:
the invention has simple structure and reasonable design, is combined with practical production, has stronger operability, can better meet the use requirement, can directly provide corresponding rotating speed and flow through the control console, and can test the performance of the aviation alternating-current generator by simple operation steps, thereby being easier to locate the fault of the aviation alternating-current generator and having better effect.
Drawings
The invention will be further described with reference to the drawings and examples.
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of the structure of the retrofit clip of the present invention;
FIG. 3 is a schematic illustration of a retrofit coupling of the present invention;
FIG. 4 is a schematic diagram of the connection of the present invention to a performance test console.
Detailed Description
The present invention will be further described in the following to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the present invention easy to understand.
As shown in fig. 1 to 4, the test fixture for the aviation alternator comprises a mounting disc 5 and a modified mounting disc 3 connected with the mounting disc 5, wherein the modified mounting disc 3 is of a hollow structure, a bearing chamber 8 is arranged on the mounting disc 5, one end of the bearing chamber 8 is connected with a bearing cover 12, the other end of the bearing chamber is connected with a copper bar 15, an axially matched spacer bush 11 is sleeved at the middle part of the bearing cover 12, a modified coupling 1 is arranged on the spacer bush 11, and an oil inlet and outlet joint 6 is arranged on the mounting disc 5.
Wherein, because of the output of drive table and aviation alternator input shaft size difference, through setting up the modification shaft coupling 1 for the drive table can drive aviation alternator, for the transmission is stable high-efficient simultaneously, sets up spacer 11, better satisfied the operation requirement. The copper bar 15 is arranged to better protect the rotating surface of the product because the copper material is soft.
The connection part of the mounting plate 5 and the remanufacturing mounting plate 3 is provided with a remanufacturing clamp 4 with a fixing function, and the remanufacturing clamp 4 is of a two-connected semicircular structure. The installation plate 5 and the remanufacturing installation plate 3 are fixed through the remanufacturing clamp 4, so that the performance test control console driving table and the aviation alternating-current generator can stably drive, and the concentricity of the product during performance test operation is ensured through the integral drive of the remanufacturing coupling 1. The modified mounting plate 3 adopts a hollow structure, so that the whole quality of the tool can be reduced, and the mounting operation is easy.
The modified mounting plate 3 is provided with a conical screw 2 connected with a performance test platform.
And the spacer bush 11 is provided with a deep groove ball bearing 9 matched with the bearing chamber 8.
The number of the deep groove ball bearings 9 is two, and cylindrical bearing spacers 20 with a partition function are arranged between the deep groove ball bearings 9.
The joint of the bearing cover 12 and the bearing chamber 8 is provided with a boss structure. The connection part of the mounting plate 5 and the modified mounting plate 3 adopts a boss structure. The boss structure is adopted, the installation is reliable, and the bearing can be better limited and fixed.
The spacer bush 11 is provided with a pin 14 for fastening the reformed coupling 1 and a circlip 10 for positioning the spacer bush 11. The spacer bush 11 is in a cylindrical form, so that a rotor shaft of a product and high-efficiency transmission efficiency can be well protected. The pin 14 on the spacer bush 11 fixes the reformed coupling 1 and the spacer bush 11, so that concentricity during transmission is ensured.
The modified coupling 1 comprises a small spline shaft 19, a transition shaft 18 and a large spline shaft 16 with a central hole 17, which are sequentially connected, wherein an O-shaped ring 13 is arranged on the small spline shaft 19. In this way, the large spline shaft 16 is connected with the mounting hole of the driving platform on the performance test console, so that the test requirement of the aviation alternator is met, the aviation alternator is connected with the mounting plate 5, the connection transmission is performed through the small spline shaft 19, and the connection transmission is fixed through screws, so that the performance test console can transmit the aviation alternator through a test fixture. The provision of the O-ring 13 ensures the engagement of the small spline shaft 19 with the aero-alternator and protects the product.
The mounting plate 5 is provided with two circular holes 21, so that the tooling quality is reduced on the premise of ensuring the strength, and the conical screw 2 is easy to screw down.
The mounting plate 5 is provided with a hollow pin 7 communicated with the oil inlet and outlet joint 6. The hollow pin 7 adopts a groove structure, and can ensure tightness by matching with a sealing ring.
A method of use for an aircraft alternator test fixture, the method of use comprising the steps of:
the first step: the test fixture is connected with a performance test console, aligned and connected with a mounting hole on a driving table in the performance test console through a large spline shaft 16 of the modified coupling 1, and fixed by using a conical screw 2.
And a second step of: and an oil inlet and an oil outlet of the aviation alternating-current generator are correspondingly arranged with the hollow pins 7 on the mounting plate 5, and are fixed by using screws, so that the stability during rotation is ensured.
And a third step of: and the oil inlet and outlet pipelines of the performance test control table are respectively connected with the oil inlet and outlet joint 6.
Oil supply mode: the installation disk 5 is provided with an oil inlet and outlet joint 6 and a hollow pin 7, the oil inlet and outlet joint 6 is connected with an oil supply and return pipeline of the performance test control platform, the oil supply and return pipeline is communicated into the hydraulic oil supply vehicle, an oil inlet and outlet pipeline of the aviation alternating-current generator is respectively and oppositely connected with the hollow pin 7, the performance test control platform is switched to a self-circulation state, and the hydraulic vehicle passing through the performance test control platform is provided with lubricating oil by a motor pump to the aviation alternating-current generator. The motor pump is controlled by a control console to provide the required rated flow for aviation alternating current power generation.
The use method is that the test tool is connected with a performance test control console driving table, the control console directly inputs the rotating speed to the aviation alternating-current generator, the rotating speed and the direction of the aviation alternating-current generator are controlled, and the performance test control console controls a functional load box to realize the detection and the maintenance of the aviation alternating-current generator.
Through the independent test to aviation alternator, can accurately find the fault point, and independent test, easy operation.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (4)
1. Be used for experimental frock of aviation alternator, including mounting disc (5), with the adaptation mounting disc (3) that mounting disc (5) are connected, its characterized in that: the improved mounting disc (3) is of a hollow structure, a bearing chamber (8) is arranged on the mounting disc (5), one end of the bearing chamber (8) is connected with a bearing cover (12) and the other end of the bearing chamber is connected with a copper bar (15), an axially matched spacer bush (11) is sleeved at the middle part of the bearing cover (12), an improved coupling (1) is arranged on the spacer bush (11), and an oil inlet and outlet joint (6) is arranged on the mounting disc (5); the joint of the mounting disc (5) and the reworking mounting disc (3) is provided with a reworking clamp (4) with a fixing function, and the reworking clamp (4) is of two connected semicircular ring structures; a deep groove ball bearing (9) matched with the bearing chamber (8) is arranged on the spacer bush (11); the modified coupling (1) comprises a small spline shaft (19), a transition shaft (18) and a large spline shaft (16) with a central hole (17) which are connected in sequence;
the mounting disc (5) is provided with a hollow pin (7) communicated with the oil inlet and outlet joint (6);
the application method for the aviation alternator test fixture comprises the following steps:
the first step: the test tool is connected with a mounting hole on a performance test console through a large spline shaft (16) of the modified coupling (1), and is fixed by a conical screw;
and a second step of: an oil inlet and an oil outlet of the aviation alternating-current generator are correspondingly arranged with hollow pins (7) on the mounting disc (5), and are fixed by using screws;
and a third step of: the oil inlet and outlet pipelines of the performance test console are respectively connected with an oil inlet and outlet joint (6);
the oil supply mode is to supply lubricating oil to the aviation alternating current generator through a motor pump which is arranged on a hydraulic supply source of the performance test control console, and the motor pump is controlled by the performance test control console to supply required rated flow to aviation alternating current power generation.
2. The tooling for an aircraft alternator test as in claim 1, wherein: the number of the deep groove ball bearings (9) is two, and cylindrical bearing spacers (20) with a partition effect are arranged between the deep groove ball bearings (9).
3. The tooling for an aircraft alternator test as in claim 1, wherein: a boss structure is arranged at the joint of the bearing cover (12) and the bearing chamber (8).
4. The tooling for an aircraft alternator test as in claim 1, wherein: the spacer bush (11) is provided with a pin (14) for fastening the reformed coupling (1) and an elastic retainer ring (10) for positioning the spacer bush (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710688116.2A CN107346000B (en) | 2017-08-12 | 2017-08-12 | Test tool for aviation alternating-current generator and application method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710688116.2A CN107346000B (en) | 2017-08-12 | 2017-08-12 | Test tool for aviation alternating-current generator and application method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107346000A CN107346000A (en) | 2017-11-14 |
| CN107346000B true CN107346000B (en) | 2023-12-05 |
Family
ID=60257584
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710688116.2A Active CN107346000B (en) | 2017-08-12 | 2017-08-12 | Test tool for aviation alternating-current generator and application method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107346000B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110377008A (en) * | 2019-07-24 | 2019-10-25 | 芜湖双翼航空装备科技有限公司 | A kind of test fixture of rudder servo controller |
| CN112563859A (en) * | 2020-12-27 | 2021-03-26 | 陕西航空电气有限责任公司 | Device for fine grinding electric brush of three-phase brush type synchronous generator |
| CN114354155B (en) * | 2021-12-13 | 2024-03-19 | 陕西航空电气有限责任公司 | Independent verification tool for three-way lubricating oil parameters of oil injection motor |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4262224A (en) * | 1978-06-29 | 1981-04-14 | Robert Bosch Gmbh | Oil cooling for an electrical generator |
| GB9416722D0 (en) * | 1991-06-14 | 1994-10-12 | Baker Hughes Inc | Method and apparatus for communicating data in a wellbore and for detecting the influx of gas |
| KR20050036828A (en) * | 2003-10-16 | 2005-04-20 | 도요다 지도샤 가부시끼가이샤 | Oil feeding device |
| CN1987152A (en) * | 2005-12-21 | 2007-06-27 | 比亚迪股份有限公司 | High speed driving mechanism |
| RU81804U1 (en) * | 2008-10-08 | 2009-03-27 | Николай Николаевич Галкин | STAND FOR TESTING TELEMETRIC SYSTEMS GENERATORS |
| CN101738313A (en) * | 2009-12-03 | 2010-06-16 | 洛阳轴研科技股份有限公司 | Method for testing bearing low-temperature lean oil resistance start-up performance for aircraft engine |
| CN203297197U (en) * | 2013-05-20 | 2013-11-20 | 武汉诺尔曼科技有限公司 | Service life test simulation platform of rotation type electronic speed regulation actuator |
| CN203519334U (en) * | 2013-10-31 | 2014-04-02 | 中国船舶重工集团公司第七�三研究所 | Switching mechanical structure |
| CN203745202U (en) * | 2014-01-25 | 2014-07-30 | 潍柴动力股份有限公司 | Rear power takeoff of engine for test |
| CN104076279A (en) * | 2013-03-28 | 2014-10-01 | 深圳市万新科技有限公司 | Test device for alternating current generator |
| CN205449154U (en) * | 2016-03-17 | 2016-08-10 | 北京昆仑凯利科技有限公司 | High -speed direct current motor test platform of unmanned aerial vehicle |
| CN205679392U (en) * | 2016-06-15 | 2016-11-09 | 上虞市东星齿轮减速电机有限公司 | A kind of load-carrying gear reduction unit performance testing device |
| CN207164219U (en) * | 2017-08-12 | 2018-03-30 | 芜湖双翼航空装备科技有限公司 | One kind is used for aviation alternator test tool |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NL1005721C2 (en) * | 1997-04-03 | 1998-10-07 | Kema Nv | Method and device for detecting partial discharges. |
-
2017
- 2017-08-12 CN CN201710688116.2A patent/CN107346000B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4262224A (en) * | 1978-06-29 | 1981-04-14 | Robert Bosch Gmbh | Oil cooling for an electrical generator |
| GB9416722D0 (en) * | 1991-06-14 | 1994-10-12 | Baker Hughes Inc | Method and apparatus for communicating data in a wellbore and for detecting the influx of gas |
| KR20050036828A (en) * | 2003-10-16 | 2005-04-20 | 도요다 지도샤 가부시끼가이샤 | Oil feeding device |
| CN1987152A (en) * | 2005-12-21 | 2007-06-27 | 比亚迪股份有限公司 | High speed driving mechanism |
| RU81804U1 (en) * | 2008-10-08 | 2009-03-27 | Николай Николаевич Галкин | STAND FOR TESTING TELEMETRIC SYSTEMS GENERATORS |
| CN101738313A (en) * | 2009-12-03 | 2010-06-16 | 洛阳轴研科技股份有限公司 | Method for testing bearing low-temperature lean oil resistance start-up performance for aircraft engine |
| CN104076279A (en) * | 2013-03-28 | 2014-10-01 | 深圳市万新科技有限公司 | Test device for alternating current generator |
| CN203297197U (en) * | 2013-05-20 | 2013-11-20 | 武汉诺尔曼科技有限公司 | Service life test simulation platform of rotation type electronic speed regulation actuator |
| CN203519334U (en) * | 2013-10-31 | 2014-04-02 | 中国船舶重工集团公司第七�三研究所 | Switching mechanical structure |
| CN203745202U (en) * | 2014-01-25 | 2014-07-30 | 潍柴动力股份有限公司 | Rear power takeoff of engine for test |
| CN205449154U (en) * | 2016-03-17 | 2016-08-10 | 北京昆仑凯利科技有限公司 | High -speed direct current motor test platform of unmanned aerial vehicle |
| CN205679392U (en) * | 2016-06-15 | 2016-11-09 | 上虞市东星齿轮减速电机有限公司 | A kind of load-carrying gear reduction unit performance testing device |
| CN207164219U (en) * | 2017-08-12 | 2018-03-30 | 芜湖双翼航空装备科技有限公司 | One kind is used for aviation alternator test tool |
Non-Patent Citations (2)
| Title |
|---|
| Online Overvoltage Prevention Control of Photovoltaic Generators in Microgrids;Yang Wang 等;《 IEEE Transactions on Smart Grid》;全文 * |
| 基于三维实体有限元的某机车柴油发电机组轴系扭转振动研究;明章杰 等;《柴油机》;全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107346000A (en) | 2017-11-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107346000B (en) | Test tool for aviation alternating-current generator and application method thereof | |
| US8113005B2 (en) | Jet engine with detachably arranged generator unit | |
| CN102518583B (en) | Test bench for control oil pump of automatic transmission | |
| CN204405319U (en) | A kind of wheel box pump valve high-low temperature tester | |
| CN203745202U (en) | Rear power takeoff of engine for test | |
| RU2689229C2 (en) | Turbomachine units drives box equipped with centrifugal pump | |
| CN207164219U (en) | One kind is used for aviation alternator test tool | |
| CN113877773A (en) | High-precision screw valve | |
| CN106059249B (en) | Magnetic coupling and its installation method | |
| CN109538744A (en) | A kind of electric vehicle input shaft spline self-lubricating device | |
| CN102042346A (en) | Flexible coupling | |
| CN104089780A (en) | Air inflow pipe used for model turbine tester and model turbine tester | |
| CN208421176U (en) | A kind of bringing onto load fault detection means of AC microsynchronous motor | |
| CN207538923U (en) | Energy saving conversion double-purpose unit and refrigeration system | |
| GB2541065A (en) | Assembly for an engine which can define a blade break-off test device | |
| CN105065649A (en) | Flexible hinge pin lubrication oil path structure | |
| CN109342947A (en) | A kind of rotor separation motor test fixture | |
| US10767749B2 (en) | System and apparatus for interchangeable smart gearbox | |
| CN201031813Y (en) | Spring mechanical sealing member with helical burr pump effect | |
| CN107370337B (en) | Vertical installation structure and method of permanent magnet coupler and online separation and resetting method | |
| CN106481374B (en) | Turbine device | |
| CN206023470U (en) | A kind of attachment means of servomotor | |
| CN205779680U (en) | A kind of lubricant pump test-bed | |
| CN220552925U (en) | Testing device for single-side output of EMC on-load test of electric drive system | |
| CN110254730A (en) | A kind of generator mounting device and a kind of aviation aircraft |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |