CN207164219U - One kind is used for aviation alternator test tool - Google Patents
One kind is used for aviation alternator test tool Download PDFInfo
- Publication number
- CN207164219U CN207164219U CN201721005595.5U CN201721005595U CN207164219U CN 207164219 U CN207164219 U CN 207164219U CN 201721005595 U CN201721005595 U CN 201721005595U CN 207164219 U CN207164219 U CN 207164219U
- Authority
- CN
- China
- Prior art keywords
- mounting disc
- transformation
- test tool
- spacer
- way
- 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
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
It the utility model is related to one kind and be used for aviation alternator test tool, the transformation of the way mounting disc being connected including mounting disc, with mounting disc, transformation of the way mounting disc is hollow-core construction, mounting disc is provided with bearing chamber, one end of bearing chamber is connected with bearing cap and the other end is connected with copper rod, the spacer axially engaged is arranged with the middle part of bearing cap, transformation of the way shaft coupling is installed, mounting disc is provided with into delivery connection on spacer.The utility model has stronger operability, corresponding rotating speed and flow can be provided, performance test is carried out to aviation alternator with shirtsleeve operation step, the fault location of aerogenerator is easier and better, the utility model is designed reasonably, it is simple in construction, with reference to produce reality, strong operability.
Description
Technical field
Technical field of aerospace is the utility model is related to, specifically one kind is used for aviation alternator test tool.
Background technology
Aerogenerator is made up of aviation alternator and constant speed drive device two parts, and certain type aerogenerator is repaired
Initial stage, aviation alternator will be assemblied in constant speed drive device and be tested, and constant speed drive device need to assemble special during experiment
Ring flange, then carry out performance test with performance test console.Occur during product testing performance parameter it is unqualified or
Certain type aerogenerator need to integrally be pulled down during other failures, substantially analysis is likely to occur the part of failure, and then aviation is handed over
Stream generator separates with constant speed drive device, the part for being likely to occur failure is changed, then by aviation alternator and constant speed
Transmission device is assembled, then carries out performance test.If it is faulty that failure does not reappear the part that explanation is changed, if fault recurrence,
Illustrate that failure appears in the part not changed.But this aviation alternator is integrally carried out with constant speed drive device
The method of experiment, its operating process is not only complicated but also is not easy to fault location.
The content of the invention
In order to avoid with solve above-mentioned technical problem, the utility model proposes one kind be used for aviation alternator test
Frock.
Technical problem to be solved in the utility model is realized using following technical scheme：
One kind is used for aviation alternator test tool, including mounting disc, the transformation of the way mounting disc that is connected with mounting disc, institute
It is hollow-core construction to state transformation of the way mounting disc, and the mounting disc is provided with bearing chamber, one end of the bearing chamber be connected with bearing cap and
The other end is connected with copper rod, is arranged with the spacer axially engaged in the middle part of the bearing cap, transformation of the way shaft coupling is provided with the spacer
Section, the mounting disc are provided with into delivery connection.
As further improvement of the utility model, the mounting disc is provided with fixation with transformation of the way mounting disc junction
Clip is changed a social system, the transformation of the way clip is the semicircle ring structure of two connections.
As further improvement of the utility model, the transformation of the way mounting disc is provided with the cone being connected with performance testing platform
Shape screw.
As further improvement of the utility model, the deep groove ball bearing coordinated with bearing chamber is installed on the spacer.
As further improvement of the utility model, the deep groove ball bearing is two, is set between the deep groove ball bearing
There is the cylinder-shaped bearing spacer that cut-off acts on.
As further improvement of the utility model, the bearing cap is provided with boss structure with bearing chamber junction.It is described
Mounting disc and transformation of the way mounting disc connecting portion use boss structure.
As further improvement of the utility model, the spacer be provided with to change a social system shaft coupling tightening pin, to every
Cover the circlip of positioning.The spacer uses drum forms.
As further improvement of the utility model, the transformation of the way shaft coupling includes small splined shaft, the transition being sequentially connected
Axle and the big splined shaft provided with centre bore.The small splined shaft is provided with O-ring.
As further improvement of the utility model, the mounting disc is provided with two circular ports.
As further improvement of the utility model, the mounting disc is provided with the hollow pins communicated with entering delivery connection.
The hollow pins use trench structure.
A kind of application method for aviation alternator test tool, the application method comprise the following steps：
The first step：Test tool is connected by changing a social system the big splined shaft of shaft coupling with the mounting hole on performance test console
Connect, and be fixed with cone screw.
Second step：By the oil inlet of aviation alternator, oil-out installation corresponding with the hollow pins in mounting disc, and make
It is fixed with screw.
3rd step：The outlet line of entering of performance test console is connected with entering delivery connection respectively.
The powered pump of hydraulic pressure source of supply itself of fuel system in the utility model for result of performance test console
Lubricating oil is provided to aviation alternator, the electric-motor pump is controlled by console, and required volume is provided to aviation alternative electric generation
Constant flow.
Result of performance test console control function load box realizes the inspection to aviation alternator in the utility model
Survey and safeguard.
The beneficial effects of the utility model are：
The utility model is simple in construction and reasonable in design, is combined with produce reality, has stronger operability, Neng Gougeng
Meet requirement well, corresponding rotating speed and flow can be directly provided by console, with shirtsleeve operation step to aviation
Alternating current generator carries out performance test, the fault location of aerogenerator is easier and better.
Brief description of the drawings
The utility model is further illustrated with reference to the accompanying drawings and examples.
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the structural representation that clip is changed a social system in the utility model；
Fig. 3 is the schematic diagram that shaft coupling is changed a social system in the utility model；
Fig. 4 is connection diagram when the utility model uses with performance test console.
Embodiment
In order that technological means, creation characteristic, reached purpose and effect that the utility model is realized are easy to understand, under
It is expanded on further in face of the utility model.
As shown in Figures 1 to 4, it is a kind of to be used for aviation alternator test tool, including mounting disc 5, connect with mounting disc 5
The transformation of the way mounting disc 3 connect, the transformation of the way mounting disc 3 is hollow-core construction, and the mounting disc 5 is provided with bearing chamber 8, the bearing chamber
8 one end is connected with bearing cap 12 and the other end is connected with copper rod 15, the middle part of bearing cap 12 be arranged with axially engage every
11 are covered, transformation of the way shaft coupling 1 is installed on the spacer 11, the mounting disc 5 is provided with into delivery connection 6.
Wherein, because driving the output end of platform different from aviation alternator input shaft size, shaft coupling is changed a social system by setting
Section 1 so that driving platform can drive aviation alternator, while in order to which stable transmission is efficient, sets spacer 11, preferably meet
Requirement.Because copper material is soft, copper rod 15 is set preferably to protect product plane of rotation.
The mounting disc 5 is provided with the transformation of the way clip 4 of fixation with transformation of the way mounting disc 3 junction, and the transformation of the way clip 4 is
The semicircle ring structure of two connections.Mounting disc 5 and transformation of the way mounting disc 3 are fixed by changing a social system clip 4, can so try performance
Test console driving platform to be steadily driven with aviation alternator, and by changing a social system the overall transmission of shaft coupling 1, ensure properties of product
Concentricity during trial run.Transformation of the way mounting disc 3 uses hollow-core construction, can mitigate frock total quality, be easily installed operation.
The transformation of the way mounting disc 3 is provided with the cone screw 2 being connected with performance testing platform.
The deep groove ball bearing 9 coordinated with bearing chamber 8 is installed on the spacer 11.
The deep groove ball bearing 9 is two, and the cylinder-shaped bearing spacer of cut-off effect is provided between the deep groove ball bearing 9
20。
The bearing cap 12 is provided with boss structure with the junction of bearing chamber 8.The mounting disc 5 and transformation of the way mounting disc 3 connect
Position uses boss structure.Using boss structure, install and fix reliably, preferably bearing can be fixed.
The spacer 11 is provided with pin 14, the circlip 10 to the positioning of spacer 11 to changing a social system the tightening of shaft coupling 1.Institute
State spacer 11 and use drum forms, can preferably protect product armature spindle and efficient transmission efficiency.Pin 14 on spacer 11,
Transformation of the way shaft coupling 1 and spacer 11 are fixed, ensure concentricity during transmission.
The transformation of the way shaft coupling 1 includes small splined shaft 19, transition axis 18 and the great Hua provided with centre bore 17 being sequentially connected
Key axle 16, the small splined shaft 19 are provided with O-ring 13.In this way, wherein big splined shaft 16 controls with performance test
Drive the mounting hole of platform to be attached on platform, meet the test requirements document of aviation alternator, aviation alternator and installation
Disk 5 is connected, and transmission is attached by small splined shaft 19, and is fixed by screw, so as to which performance test console can pass through examination
Frock is tested to be driven aviation alternator.O-ring 13 is set to can ensure that small splined shaft 19 and aviation alternator
Coordinate, and product is played a protective role.
The mounting disc 5 is provided with two circular ports 21, on the premise of proof strength, alleviates frock quality, and easily
Tightened in cone screw 2.
The mounting disc 5 is provided with the hollow pins 7 communicated with entering delivery connection 6.The hollow pins 7 use trench structure,
Sealing can be ensured by coordinating with sealing ring.
A kind of application method for aviation alternator test tool, the application method comprise the following steps：
The first step：Test tool is connected with performance test console, by the big splined shaft 16 and property of changing a social system shaft coupling 1
Mounting hole alignment connection on driving platform in energy test console, and be fixed with cone screw 2.
Second step：By the oil inlet of aviation alternator, oil-out installation corresponding with the hollow pins 7 in mounting disc 5, and
It is fixed using screw, stationarity when ensureing to rotate.
3rd step：The outlet line of entering of performance test console is connected with entering delivery connection 6 respectively.
Fuel system：Set in mounting disc 5 into delivery connection 6 and hollow pins 7, enter delivery connection 6 and controlled with performance test
Platform fuel feeding is connected with return line, and the fuel feeding, return line are communicated to hydraulic pressure fuel feeding in-car, and aviation alternator enters flowline
Mouth is relative with hollow pins 7 respectively to be connected, and performance test console is switched to self-loopa state, result of performance test console
Hydraulic car itself the powered pump of institute provides lubricating oil to aviation alternator, could be to navigating because only when providing lubricating oil
Empty alternating current generator provides rotating speed, in order to avoid human error, sets defence program to performance test console, is not providing rule
During fixed flow of lubrication, it is impossible to which rotating speed is provided.The electric-motor pump is controlled by console, required to the offer of aviation alternative electric generation
Metered flow.
The application method is to drive platform to be connected with performance test console by the test tool, by console to boat
Empty alternating current generator directly inputs rotating speed, controls its rotating speed and direction, result of performance test console control function load box reality
The now detection and maintenance to aviation alternator.
It is simple to operate by aviation alternator routine tests, can precisely find trouble point, and routine tests.
The advantages of general principle of the present utility model, principal character and the utility model has been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Simply principle of the present utility model, on the premise of the spirit and scope of the utility model is not departed from, the utility model also has
Various changes and modifications, these changes and improvements are both fallen within claimed the utility model.The requires of the utility model is protected
Scope is by appended claims and its equivalent thereof.
Claims (8)
1. one kind is used for aviation alternator test tool, including mounting disc (5), the transformation of the way that is connected with mounting disc (5) are installed
Disk (3), it is characterised in that：The transformation of the way mounting disc (3) is hollow-core construction, and the mounting disc (5) is provided with bearing chamber (8), institute
The one end for stating bearing chamber (8) is connected with bearing cap (12) and the other end is connected with copper rod (15), is covered in the middle part of the bearing cap (12)
Provided with the spacer (11) axially engaged, transformation of the way shaft coupling (1) is installed on the spacer (11), the mounting disc (5) is provided with
Enter delivery connection (6).
2. one kind according to claim 1 is used for aviation alternator test tool, it is characterised in that：The mounting disc
(5) transformation of the way clip (4) of fixation is provided with transformation of the way mounting disc (3) junction, the transformation of the way clip (4) is two connections
Semicircle ring structure.
3. one kind according to claim 1 is used for aviation alternator test tool, it is characterised in that：The spacer
(11) deep groove ball bearing (9) coordinated with bearing chamber (8) is installed on.
4. one kind according to claim 3 is used for aviation alternator test tool, it is characterised in that：The deep-groove ball
Bearing (9) is two, and the cylinder-shaped bearing spacer (19) of cut-off effect is provided between the deep groove ball bearing (9).
5. one kind according to claim 1 is used for aviation alternator test tool, it is characterised in that：The bearing cap
(12) it is provided with boss structure with bearing chamber (8) junction.
6. one kind according to claim 1 is used for aviation alternator test tool, it is characterised in that：The spacer
(11) pin (14), the circlip (10) to spacer (11) positioning to changing a social system shaft coupling (1) tightening are provided with.
7. one kind according to claim 1 or 6 is used for aviation alternator test tool, it is characterised in that：It is described to change
Shaft coupling (1) processed includes small splined shaft (19), transition axis (18) and the big splined shaft provided with centre bore (17) being sequentially connected
(16)。
8. one kind according to claim 1 is used for aviation alternator test tool, it is characterised in that：The mounting disc
(5) hollow pins (7) communicated with entering delivery connection (6) are provided with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721005595.5U CN207164219U (en) | 2017-08-12 | 2017-08-12 | One kind is used for aviation alternator test tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721005595.5U CN207164219U (en) | 2017-08-12 | 2017-08-12 | One kind is used for aviation alternator test tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207164219U true CN207164219U (en) | 2018-03-30 |
Family
ID=61716554
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721005595.5U Active CN207164219U (en) | 2017-08-12 | 2017-08-12 | One kind is used for aviation alternator test tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207164219U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107346000A (en) * | 2017-08-12 | 2017-11-14 | 芜湖双翼航空装备科技有限公司 | One kind is used for aviation alternator test tool and its application method |
| 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 |
-
2017
- 2017-08-12 CN CN201721005595.5U patent/CN207164219U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107346000A (en) * | 2017-08-12 | 2017-11-14 | 芜湖双翼航空装备科技有限公司 | One kind is used for aviation alternator test tool and its application method |
| CN107346000B (en) * | 2017-08-12 | 2023-12-05 | 芜湖双翼航空装备科技有限公司 | Test tool for aviation alternating-current generator and application method thereof |
| 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109406152B (en) | Aeroengine counter-rotating dual-rotor dynamic characteristic experiment platform | |
| KR101890955B1 (en) | A non-lubricated architecture for a turboshaft engine | |
| CN104964824B (en) | The aeroplane engine main bearing exerciser with outer casing is supported with turbine | |
| CN107346000A (en) | One kind is used for aviation alternator test tool and its application method | |
| CN106500972B (en) | A kind of land united test equipment of tuning for Controllable Pitch Propeller | |
| CN207164219U (en) | One kind is used for aviation alternator test tool | |
| JP6462024B2 (en) | Turbo compressor train with rolling bearings and associated assembly method | |
| CN109612655A (en) | A kind of between centers sealing dynamic testing equipment | |
| JP2013516572A (en) | Counter-rotating propeller system for aircraft turbine engines | |
| CN203745202U (en) | Rear power takeoff of engine for test | |
| CN101930231A (en) | Test device of fuel controller | |
| US20200247529A1 (en) | System and method of locating feathering propeller blade angular position | |
| CN105793543A (en) | Turbine engine provided with means for absorbing stresses from the thrust of the engine thereof | |
| CN101520002A (en) | Methods and apparatus for regulating gas turbine engine fluid flow | |
| US20130174575A1 (en) | Gas turbine engine starter-generator with integrated lube oil scavenge functionality | |
| RU2689229C2 (en) | Turbomachine units drives box equipped with centrifugal pump | |
| CN107725454A (en) | Two-spool compressor testing stand | |
| CN105065649A (en) | Flexible hinge pin lubrication oil path structure | |
| CN110686075B (en) | System and method for gear assembly lubrication system failure detection | |
| US20190211750A1 (en) | Blade positioning system for a gas turbine engine | |
| CN114964787A (en) | Stress measurement structure for whole-machine low-vortex rotor blade of aero-engine | |
| US20190063317A1 (en) | Fluid communication between a stationary structure and a rotating structure | |
| CN112304610B (en) | Bearing test device for low temperature | |
| CN106769044B (en) | Hydraulic and pneumatic auxiliary device for flexible thin-wall bearing life testing machine | |
| CN110254730B (en) | Generator installation device and aviation aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |