CN106769063B - A kind of integrative installation technology frame for aeroengine test run - Google Patents
A kind of integrative installation technology frame for aeroengine test run Download PDFInfo
- Publication number
- CN106769063B CN106769063B CN201611193138.3A CN201611193138A CN106769063B CN 106769063 B CN106769063 B CN 106769063B CN 201611193138 A CN201611193138 A CN 201611193138A CN 106769063 B CN106769063 B CN 106769063B
- Authority
- CN
- China
- Prior art keywords
- fulcrum
- redundant
- main
- adapter
- plane
- 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
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
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The present invention relates to a kind of integrative installation technology framves for aeroengine test run, it is characterized in that, including itself symmetrical hanger bracket 1, the left main fulcrum adapter 2 and right main fulcrum adapter 3 being left and right symmetrically arranged, the left main fulcrum support seat 4 and right main fulcrum support seat 5 being left and right symmetrically arranged, the left redundant fulcrum adapter 6 and right redundant fulcrum adapter 7 being left and right symmetrically arranged, the left redundant fulcrum support seat 8 and right redundant fulcrum support seat 9 and itself symmetrical bottom plate 10 being left and right symmetrically arranged.The mounting rack that the present invention designs is suitable for the use of brace type and suspension type rack, can also directly carry on operating platform, meet the use of the close engine of structure size, installation in advance, transhipment are convenient.
Description
Technical field
The invention belongs to a kind of testing equipment designing techniques of aero-engine complete machine ground experiment, and in particular to Yi Zhongyong
In the integrative installation technology frame of aeroengine test run.
Background technique
During Aero Engine Testing, engine installation and adjustment of appearing on the stage occupy the plenty of time, greatly reduce examination
The service efficiency of ride.The engine tested for the first time, time of appearing on the stage are longer.For needing in (the suspension of different test bays
Formula, brace type) on for the engine tested, the difference of mounting means also leverages appear on the stage time and test effect
Rate.
Current mounting means is directly to lift engine to appear on the stage, and engine is all nonstandard by " special frame is dedicated "
Frame is fixed.Such rack lacks versatility, is all needed before test every time according to different model engine or different test bay knots
Structure carries out redesign processing, and bed size is larger, installs time-consuming and laborious.
Summary of the invention
The technical problem to be solved in the present invention:
It designs that a versatility is good, the simple integrative installation technology frame of structure, the similar engine examination of structure can be met
The rack prepackage demand tested, while can be realized by different usage modes and be used in different structure form test bay.To improve
Its aeroengine test run is appeared on the stage installation effectiveness and versatility.
Technical solution of the present invention:
A kind of integrative installation technology frame for aeroengine test run, including itself symmetrical hanger bracket 1, left and right pair
Claim left main fulcrum adapter 2 and right main fulcrum adapter 3, the left main fulcrum support seat 4 being left and right symmetrically arranged and the right master of installation
Fulcrum support seat 5, the left redundant fulcrum adapter 6 and right redundant fulcrum adapter 7 being left and right symmetrically arranged, is left and right symmetrically arranged
Left redundant fulcrum support seat 8 and right redundant fulcrum support seat 9 and itself symmetrical bottom plate 10, wherein hanger bracket 1 include
Girder 1-1, drive a vehicle flap seat 1-2, auxiliary connecting rod 1-3, symmetrical left main supporting leg 1-4 and right main supporting leg 1-5, symmetrical
Left main fulcrum 1-6 and right main fulcrum 1-7, symmetrical left redundant supporting leg 1-8 and right redundant supporting leg 1-9, and bilateral symmetry
Left positioning seat 1-10 and right positioning seat 1-11.
Bottom plate 10 is placed horizontally in ground, shipping platform or brace type test bay plane；Left main 4 He of fulcrum support seat
Right main fulcrum support seat 5 is symmetrically arranged in the left and right sides of 10 front of bottom plate, left redundant fulcrum support seat 8 and right redundant fulcrum branch
Support seat 9 is symmetrically arranged in the left and right sides at 10 rear portion of bottom plate；
Left main 2 lower plane of fulcrum adapter is bolt-connected to plane on left main fulcrum support seat 4, left main fulcrum switching
Plane is bolt-connected to left main supporting leg 1-4 lower plane on seat 2；Right main 3 lower plane of fulcrum adapter is bolt-connected to
Plane on right main fulcrum support seat 5, plane is bolt-connected to right main supporting leg 1-5 lower plane on right main fulcrum adapter 3；
6 lower plane of left redundant fulcrum adapter is bolt-connected to plane on left redundant fulcrum support seat 8, left redundant branch
Plane is bolt-connected to left redundant supporting leg 1-8 lower plane on point adapter 6, and 7 lower plane of right redundant fulcrum adapter passes through
It is bolted to plane on right redundant fulcrum support seat 9, plane is bolt-connected to right redundant on right redundant fulcrum adapter 7
Supporting leg 1-9 lower plane；
Left main fulcrum 1-6 by bolt be mounted on left main supporting leg 1-4 lower plane and left main fulcrum adapter 2 plane it
Between, right main fulcrum 1-7 is mounted on right main supporting leg 1-5 lower plane and right main fulcrum adapter 3 between plane by bolt, described
Left main fulcrum 1-6 and right main fulcrum 1-7 are supported jointly in the left and right sides by spreadsheet engine；
Left main supporting leg 1-4 and right main supporting leg 1-5 are symmetrically welded at girder 1-1 front lower portion two sides, left redundant supporting leg 1-8 and the right side
Auxiliary leg 1-9 is symmetrically welded at girder 1-1 rear lower two sides, and auxiliary connecting rod 1-3 is fixed by bolts in girder 1-1 rear lower
Auxiliary fulcrum tie point, the auxiliary fulcrum tie point is located at the position of left redundant supporting leg 1-8 and the middle right redundant supporting leg 1-9
It sets, the fixed top with the middle girder 1-1 driving flap seat 1-2, left positioning seat 1-10 and right positioning seat 1-11 bilateral symmetry are welded
It connects in girder 1-1 side wall.
Beneficial effects of the present invention:
Advantage:
A) mounting rack is suitable for the use of brace type and suspension type rack, can also directly carry on operating platform.
B) the high adjusting of engine center may be implemented by the adapter of different height, auxiliary fulcrum peace can also be passed through
Holding position and pull rod elongation micro-positioning regulators, meet the use of the close engine of structure size.
C) compact-sized, installation in advance, transhipment are convenient.
Effect:
The integrative installation technology frame for being used for aeroengine test run is reasonable in design, and easy to operate, versatility is good.?
Installation effect is good in the preliminary use of test bay, tests preparation efficiency greatly improves.
Detailed description of the invention
Fig. 1 is integrated mounting rack front view；
Fig. 2 is integrated mounting rack side view；
Fig. 3 is integrated mounting rack top view.
Specific embodiment
Integrative installation technology frame is that the pre- of rocket engine ground test is shelved, the technical characteristics of the integrative installation technology frame,
It include: main fulcrum, auxiliary fulcrum, driving interface, suspension type interface, brace type gantry interface, transferring platform interface etc..Installation
When, hanger bracket is hung to spreadsheet engine top by driving, and complete the installation of major-minor fulcrum；Hanger bracket and engine is whole
Body is adjusted on the support base of bottom plate, after the installment work of engine accessory power rating to be done and test line；It can be by integrative installation technology
Frame and engine are integrally transported to test bay and carry out test installation, according to stand structure (suspension type or brace type) selection one
The mounting plane and interface of body mounting rack, dismountable extra support base and adapter in installation process.
A kind of integrative installation technology frame for aeroengine test run, it is characterised in that: the installation frame mechanism includes certainly
The symmetrical hanger bracket 1 of body, symmetrical left main fulcrum adapter 2 and right main fulcrum adapter 3, symmetrical left master
Fulcrum support seat 4 and right main fulcrum support seat 5, symmetrical left redundant fulcrum adapter 6 and right redundant fulcrum adapter 7,
Symmetrical left redundant fulcrum support seat 8 and right redundant fulcrum support seat 9 and symmetrical bottom plate 10, wherein hanging
Frame 1 includes girder 1-1, and drive a vehicle flap seat 1-2, auxiliary connecting rod 1-3, symmetrical left main supporting leg 1-4 and right main supporting leg 1-5, left
Right symmetrical left main fulcrum 1-6 and right main fulcrum 1-7, symmetrical left redundant supporting leg 1-8 and right redundant supporting leg 1-9, and
Symmetrical left positioning seat 1-10 and right positioning seat 1-11.
Bottom plate 10 is placed horizontally in ground, shipping platform or brace type test bay plane；Left main 4 He of fulcrum support seat
Right main fulcrum support seat 5 is symmetrically arranged in the left and right sides of 10 front of bottom plate, left redundant fulcrum support seat 8 and right redundant fulcrum branch
Support seat 9 is symmetrically arranged in the left and right sides at 10 rear portion of bottom plate.Left main 2 lower plane of fulcrum adapter is bolt-connected to left main branch
Plane on support base 4 is put, plane is bolt-connected to left main supporting leg 1-4 lower plane on left main fulcrum adapter 2；Right main fulcrum
3 lower plane of adapter is bolt-connected to plane on right main fulcrum support seat 5, and plane passes through spiral shell on right main fulcrum adapter 3
It tethers and is connected to right main supporting leg 1-5 lower plane.6 lower plane of left redundant fulcrum adapter is bolt-connected to left redundant fulcrum support
Plane on seat 8, plane is bolt-connected to left redundant supporting leg 1-8 lower plane, right redundant fulcrum on left redundant fulcrum adapter 6
7 lower plane of adapter is bolt-connected to plane on right redundant fulcrum support seat 9, and plane is logical on right redundant fulcrum adapter 7
It crosses and is bolted to right redundant supporting leg 1-9 lower plane.Left main fulcrum 1-6 is mounted on left main supporting leg 1-4 lower plane by bolt, with
Support the main branch at left and right sides of by spreadsheet engine jointly by the right main fulcrum 1-7 that bolt is mounted on right main supporting leg 1-5 lower plane
Point.Left main supporting leg 1-4 and right main supporting leg 1-5 are symmetrically welded at girder 1-1 front lower portion, left redundant supporting leg 1-8 and right redundant supporting leg
1-9 is symmetrically welded at girder 1-1 rear lower, and auxiliary connecting rod 1-3 is fixed by bolts in girder 1-1 rear lower middle, driving
The fixed top with the middle girder 1-1 flap seat 1-2, left positioning seat 1-10 and right positioning seat 1-11 bilateral symmetry are welded on girder
1-1 side wall.
Claims (1)
1. a kind of integrative installation technology frame for aeroengine test run, which is characterized in that including itself symmetrical suspension
Frame (1), the left main fulcrum adapter (2) and right main fulcrum adapter (3) being left and right symmetrically arranged, the left main branch being left and right symmetrically arranged
Point support base (4) and right main fulcrum support seat (5), the left redundant fulcrum adapter (6) and right redundant fulcrum being left and right symmetrically arranged
Adapter (7), the left redundant fulcrum support seat (8) and right redundant fulcrum support seat (9) that are left and right symmetrically arranged and itself left and right
Symmetrical bottom plate (10), wherein hanger bracket (1) includes girder (1-1), is driven a vehicle flap seat (1-2), auxiliary connecting rod (1-3), left and right pair
The left main supporting leg (1-4) claimed and right main supporting leg (1-5), symmetrical left main fulcrum (1-6) and right main fulcrum (1-7), left and right
Symmetrical left redundant supporting leg (1-8) and right redundant supporting leg (1-9) and symmetrical left positioning seat (1-10) and right positioning seat
(1-11)；
Bottom plate (10) is placed horizontally in ground, shipping platform or brace type test bay plane；Left main fulcrum support seat (4) and
Right main fulcrum support seat (5) is symmetrically arranged in the left and right sides of bottom plate (10) front, left redundant fulcrum support seat (8) and right redundant
Fulcrum support seat (9) is symmetrically arranged in the left and right sides at bottom plate (10) rear portion；
Left main fulcrum adapter (2) lower plane is bolt-connected to plane on left main fulcrum support seat (4), left main fulcrum switching
Plane is bolt-connected to left main supporting leg (1-4) lower plane on seat (2)；Right main fulcrum adapter (3) lower plane passes through bolt
It is connected to plane on right main fulcrum support seat (5), plane is bolt-connected to right main supporting leg on right main fulcrum adapter (3)
(1-5) lower plane；
Left redundant fulcrum adapter (6) lower plane is bolt-connected to plane on left redundant fulcrum support seat (8), left redundant branch
Plane is bolt-connected to left redundant supporting leg (1-8) lower plane on point adapter (6), puts down under right redundant fulcrum adapter (7)
Face is bolt-connected to plane on right redundant fulcrum support seat (9), and plane is connected by bolt on right redundant fulcrum adapter (7)
It is connected to right redundant supporting leg (1-9) lower plane；
Left main fulcrum (1-6) by bolt be mounted on left main supporting leg (1-4) lower plane and left main fulcrum adapter (2) plane it
Between, right main fulcrum (1-7) by bolt be mounted on right main supporting leg (1-5) lower plane and right main fulcrum adapter (3) plane it
Between, the left main fulcrum (1-6) and right main fulcrum (1-7) are supported jointly in the left and right sides by spreadsheet engine；
Left main supporting leg (1-4) and right main supporting leg (1-5) are symmetrically welded at girder (1-1) front lower portion two sides, left redundant supporting leg (1-8)
Girder (1-1) rear lower two sides are symmetrically welded at right redundant supporting leg (1-9), auxiliary connecting rod (1-3) is fixed by bolts in master
The auxiliary fulcrum tie point of beam (1-1) rear lower, the auxiliary fulcrum tie point are located at left redundant supporting leg (1-8) and right redundant branch
The position of the middle leg (1-9), the fixed top with the middle girder (1-1) of driving flap seat (1-2), left positioning seat (1-10) and
Right positioning seat (1-11) is symmetrically welded on girder (1-1) side wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611193138.3A CN106769063B (en) | 2016-12-21 | 2016-12-21 | A kind of integrative installation technology frame for aeroengine test run |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611193138.3A CN106769063B (en) | 2016-12-21 | 2016-12-21 | A kind of integrative installation technology frame for aeroengine test run |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106769063A CN106769063A (en) | 2017-05-31 |
| CN106769063B true CN106769063B (en) | 2019-01-25 |
Family
ID=58896965
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611193138.3A Active CN106769063B (en) | 2016-12-21 | 2016-12-21 | A kind of integrative installation technology frame for aeroengine test run |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106769063B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110441064B (en) * | 2019-08-13 | 2021-06-22 | 中国航发贵阳发动机设计研究所 | Auxiliary hanging pull rod assembling method for optimizing vibration of aircraft engine |
| CN112145285B (en) * | 2020-08-14 | 2021-09-24 | 武汉司南翼航航空工程技术有限责任公司 | Low-oil-consumption long-endurance aircraft engine |
| CN112985816A (en) * | 2021-03-18 | 2021-06-18 | 北京航空航天大学 | Variable-size universal miniature turbine engine test bed |
| CN114136634B (en) * | 2021-11-30 | 2024-04-05 | 中国航发湖南动力机械研究所 | Engine pylon direction positioner |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6164418A (en) * | 1998-03-31 | 2000-12-26 | Chen; Ching Hung | Elevating work platform structure |
| DE112005000728T5 (en) * | 2004-03-31 | 2007-03-22 | Kobelco Cranes Co., Ltd. | Crane and method of assembling the crane |
| CN2839997Y (en) * | 2005-10-24 | 2006-11-22 | 成都发动机（集团）有限公司 | Suspension type engine test run rack |
| CN203216724U (en) * | 2013-04-02 | 2013-09-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Suspension type process inlet channel rack mounting structure |
| CN105222974B (en) * | 2014-06-06 | 2018-03-09 | 上海新力动力设备研究所 | Engine vertical vibration test tool mounting platform |
| CN105626269A (en) * | 2015-12-29 | 2016-06-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Supporting device of gas turbine |
-
2016
- 2016-12-21 CN CN201611193138.3A patent/CN106769063B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106769063A (en) | 2017-05-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106769063B (en) | A kind of integrative installation technology frame for aeroengine test run | |
| CN201755731U (en) | Automobile instrument panel support welding clamp | |
| CN106240841A (en) | A kind of gear test charger | |
| CN205498841U (en) | Supplementary support assembly of cabin electrical apparatus before electric automobile | |
| CN109696237A (en) | Automobile power assembly suspension system vibration noise experimental rig | |
| CN109406150A (en) | A kind of Used For Turbojet Engine Test Bench rack | |
| CN207274845U (en) | A kind of motorcycle and its side box bracket | |
| CN107161037B (en) | A kind of wire casing dismounting erecting by overhang used for rail vehicle | |
| CN209342322U (en) | Vibration test fixture for ultra-high aeronautical actuator components | |
| CN208352853U (en) | Flexible direct current converter valve module apparatus for examination and repair | |
| CN203616451U (en) | Electrical motor test stand | |
| CN217331619U (en) | Aeroengine ground test bench | |
| CN206767472U (en) | Automobile chassis attaches together positioning device of hoist | |
| CN209264287U (en) | A kind of Used For Turbojet Engine Test Bench rack | |
| CN214748895U (en) | Modular detects with simulation aircraft device | |
| CN104889651B (en) | Locomotive guide flange location tooling | |
| CN209459848U (en) | A kind of bus seat strength test multipurpose test system | |
| CN210608255U (en) | GIS terminal installation device for training | |
| CN203875823U (en) | Torque box type solar heat accumulator general assembly tool bench | |
| CN208616213U (en) | The vibration experiment of mixed power plant | |
| CN205254404U (en) | Automobile -used rear axle assembly welding jig supporting seat | |
| CN208632041U (en) | A kind of power engineering installation vehicle | |
| CN207419279U (en) | A kind of anti-horizontal sliding supporting rack of bridge construction | |
| CN214729714U (en) | Helicopter engine combined bracket | |
| CN107053076B (en) | Hydrogenerator brakes the disassembly of air lock, installation method |
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 | ||
| CP03 | Change of name, title or address |
Address after: 610500 Xindu Xuefu Road, Xindu District, Chengdu, Sichuan Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 P.O. Box 305, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |
|
| CP03 | Change of name, title or address |