CN106769063A - 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
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- CN106769063A CN106769063A CN201611193138.3A CN201611193138A CN106769063A CN 106769063 A CN106769063 A CN 106769063A CN 201611193138 A CN201611193138 A CN 201611193138A CN 106769063 A CN106769063 A CN 106769063A
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- fulcrum
- redundant
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- adapter
- plane
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- 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
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The present invention relates to a kind of integrative installation technology frame 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 being left and right symmetrically arranged, and itself symmetrical base plate 10.The mounting bracket of present invention design is suitable for the use of brace type and suspension type stand, can also directly be carried on operating platform, meets the use of the close engine of physical dimension, and installation in advance, transhipment are convenient.
Description
Technical field
The invention belongs to a kind of testing equipment designing technique of the whole machine ground experiment of aero-engine, and in particular to Yi Zhongyong
In the integrative installation technology frame of aeroengine test run.
Background technology
During Aero Engine Testing, engine appear on the stage installation and adjustment occupy the plenty of time, greatly reduce examination
The service efficiency of ride.The engine tested first, its time of appearing on the stage is 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 the time of appearing on the stage and experiment is imitated
Rate.
Current mounting means is directly to lift engine to appear on the stage, and engine is all nonstandard by " special frame is special "
Frame is fixed.Such stand lacks versatility, is all needed before experiment every time according to different model engine or different test bay knots
Structure carries out redesign processing, and bed size is larger, and installation is wasted time and energy.
The content of the invention
The technical problem to be solved in the present invention：
One versatility of design is good, the integrative installation technology frame of simple structure, can meet the similar engine examination of structure
The stand prepackage demand tested, while can realize being used in different structure form test bay by different occupation modes.To improve
Its aeroengine test run is appeared on the stage installation effectiveness and versatility.
Technical scheme：
A kind of integrative installation technology frame for aeroengine test run, including itself symmetrical hanger bracket 1, left and right is right
Claim the left main fulcrum adapter 2 and right main fulcrum adapter 3 installed, a left main fulcrum support being left and right symmetrically arranged 4 and right master
Fulcrum support seat 5, the left redundant fulcrum adapter 6 and right redundant fulcrum adapter 7 being left and right symmetrically arranged are left and right symmetrically arranged
Left redundant fulcrum support seat 8 and right redundant fulcrum support seat 9, and itself symmetrical base 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 it is symmetrical
Left positioning seat 1-10 and right positioning seat 1-11.
Base plate 10 is placed horizontally in ground, shipping platform or brace type test bay plane；4 Hes of left main fulcrum support seat
Right main fulcrum support seat 5 is symmetrically arranged in the left and right sides of the front portion of base plate 10, left redundant fulcrum support seat 8 and right redundant fulcrum branch
Support seat 9 is symmetrically arranged in the left and right sides at the rear portion of base plate 10；
The left main lower plane of fulcrum adapter 2 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 planes on seat 2；The right main lower plane of fulcrum adapter 3 is bolt-connected to
Plane on right main fulcrum support seat 5, plane is bolt-connected to right main supporting leg 1-5 lower planes on right main fulcrum adapter 3；
The lower plane of left redundant fulcrum adapter 6 is bolt-connected to plane, left redundant branch on left redundant fulcrum support seat 8
Plane is bolt-connected to left redundant supporting leg 1-8 lower planes on point adapter 6, and the lower plane of right redundant fulcrum adapter 7 passes through
Plane on right redundant fulcrum support seat 9 is bolted to, plane is bolt-connected to right redundant on right redundant fulcrum adapter 7
Supporting leg 1-9 lower planes；
Left main fulcrum 1-6 by bolt be arranged on left main supporting leg 1-4 lower planes and plane on left main fulcrum adapter 2 it
Between, right main fulcrum 1-7 is arranged on right main supporting leg 1-5 lower planes and right main fulcrum adapter 3 between plane by bolt, described
Left main fulcrum 1-6 is supported by spreadsheet engine jointly with right main fulcrum 1-7 in the left and right sides；
Left main supporting leg 1-4 and right main supporting leg 1-5 are symmetrically welded at girder 1-1 front lower portions both sides, left redundant supporting leg 1-8 and the right side
Auxiliary leg 1-9 is symmetrically welded at girder 1-1 rear lowers both sides, and auxiliary connecting rod 1-3 is secured by bolts in girder 1-1 rear lowers
Auxiliary fulcrum tie point, the auxiliary fulcrum tie point is located at the position of left redundant supporting leg 1-8 and right redundant supporting leg 1-9 middles
Put, driving flap seat 1-2 fixes the top with girder 1-1 middles, left positioning seat 1-10 and the right symmetrical welderings of positioning seat 1-11
It is connected on girder 1-1 sides wall.
Beneficial effects of the present invention：
Advantage：
A) mounting bracket is suitable for the use of brace type and suspension type stand, can also directly be carried on operating platform.
B) engine center regulation high can be realized by the adapter of different height, can also be pacified by aiding in fulcrum
Holding position and pull bar elongation micro-positioning regulators, meet the use of the close engine of physical dimension.
C) compact conformation, installs, transports conveniently in advance.
Effect：
This is used for the integrative installation technology frame reasonable in design of aeroengine test run, and easy to operate, versatility is good.
Installation effect is good in the preliminary use of test bay, test preparation efficiency greatly improves.
Brief description of the drawings
The integrated mounting bracket front views of Fig. 1；
The integrated mounting bracket side views of Fig. 2；
The integrated mounting bracket top views of Fig. 3.
Specific embodiment
Integrative installation technology frame is shelved for the pre- of rocket engine ground test, the technical characteristics of the integrative installation technology frame,
Including：Main fulcrum, auxiliary fulcrum, driving interface, suspension type interface, brace type gantry interface, transferring platform interface etc..Install
When, hanger bracket is hung to by being driven a vehicle treats spreadsheet engine top, and complete the installation of major-minor fulcrum；Hanger bracket and engine is whole
Body is adjusted on the support base of base plate, after the installment work of engine accessory power rating to be done and test line；Can be by integrative installation technology
Frame and engine are integrally transported to test bay and carry out experiment installation, according to stand structure (suspension type or brace type) selection one
The mounting plane and interface of body mounting bracket, dismountable unnecessary 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 is included 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 base 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.
Base plate 10 is placed horizontally in ground, shipping platform or brace type test bay plane；4 Hes of left main fulcrum support seat
Right main fulcrum support seat 5 is symmetrically arranged in the left and right sides of the front portion of base plate 10, left redundant fulcrum support seat 8 and right redundant fulcrum branch
Support seat 9 is symmetrically arranged in the left and right sides at the rear portion of base plate 10.The left main lower plane of fulcrum adapter 2 is bolt-connected to left main branch
Plane on point support base 4, plane is bolt-connected to left main supporting leg 1-4 lower planes on left main fulcrum adapter 2；Right main fulcrum
The lower plane of adapter 3 is bolt-connected to plane on right main fulcrum support seat 5, and plane passes through spiral shell on right main fulcrum adapter 3
Tether and be connected to right main supporting leg 1-5 lower planes.The lower plane of left redundant fulcrum adapter 6 is bolt-connected to left redundant fulcrum support
Plane on seat 8, plane is bolt-connected to left redundant supporting leg 1-8 lower planes, right redundant fulcrum on left redundant fulcrum adapter 6
The lower plane of adapter 7 is bolt-connected to plane on right redundant fulcrum support seat 9, and plane is led on right redundant fulcrum adapter 7
Cross and be bolted to right redundant supporting leg 1-9 lower planes.Left main fulcrum 1-6 is arranged on left main supporting leg 1-4 lower planes by bolt, with
The right main fulcrum 1-7 for being arranged on right main supporting leg 1-5 lower planes by bolt is supported by the main branch of the spreadsheet engine left and right sides jointly
Point.Left main supporting leg 1-4 and right main supporting leg 1-5 are symmetrically welded at girder 1-1 front lower portions, left redundant supporting leg 1-8 and right redundant supporting leg
1-9 is symmetrically welded at girder 1-1 rear lowers, and auxiliary connecting rod 1-3 is secured by bolts in girder 1-1 rear lowers middle, driving
Flap seat 1-2 is fixed and the top of girder 1-1 middles, left positioning seat 1-10 and right positioning seat 1-11 is symmetrical is welded on girder
1-1 sides wall.
Claims (1)
1. a kind of integrative installation technology frame for aeroengine test run, it is characterised in that including itself symmetrical suspension
Frame (1), the left main fulcrum adapter (2) being left and right symmetrically arranged and right main fulcrum adapter (3), the left main branch being left and right symmetrically arranged
Point support base (4) and right main fulcrum support seat (5), left redundant fulcrum adapter (6) and right redundant fulcrum being left and right symmetrically arranged
Adapter (7), left redundant fulcrum support seat (8) and right redundant fulcrum support seat (9) being left and right symmetrically arranged, and itself left and right
Symmetrical base plate (10), wherein hanger bracket (1) include girder (1-1), driving flap seat (1-2), auxiliary connecting rod (1-3), and left and right is right
The left main supporting leg (1-4) and right main supporting leg (1-5) for claiming, 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)。
Base 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 anterior left and right sides of base plate (10), left redundant fulcrum support seat (8) and right redundant
Fulcrum support seat (9) is symmetrically arranged in the left and right sides at base 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
Plane on right main fulcrum support seat (5) is connected to, 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, left redundant branch on left redundant fulcrum support seat (8)
Plane is bolt-connected to left redundant supporting leg (1-8) lower plane on point adapter (6), is put 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 arranged on left main supporting leg (1-4) lower plane and plane on left main fulcrum adapter (2) it
Between, right main fulcrum (1-7) by bolt be arranged on right main supporting leg (1-5) lower plane and plane on right main fulcrum adapter (3) it
Between, the left main fulcrum (1-6) is supported by spreadsheet engine jointly with right main fulcrum (1-7) in the left and right sides；
Left main supporting leg (1-4) and right main supporting leg (1-5) are symmetrically welded at girder (1-1) front lower portion both sides, left redundant supporting leg (1-8)
Girder (1-1) rear lower both sides are symmetrically welded at right redundant supporting leg (1-9), auxiliary connecting rod (1-3) is secured by bolts in master
The auxiliary fulcrum tie point of beam (1-1) rear lower, the auxiliary fulcrum tie point is located at left redundant supporting leg (1-8) and right redundant branch
The position of leg (1-9) middle, the fixed top with girder (1-1) middle of driving flap seat (1-2), left positioning seat (1-10) and
Right positioning seat (1-11) is symmetrical to be 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 true CN106769063A (en) | 2017-05-31 |
| CN106769063B CN106769063B (en) | 2019-01-25 |
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| 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 |
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| CN (1) | CN106769063B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110441064A (en) * | 2019-08-13 | 2019-11-12 | 中国航发贵阳发动机设计研究所 | A kind of auxiliary hanging pull rod assembly method optimizing aeroplane engine machine vibration |
| CN112145285A (en) * | 2020-08-14 | 2020-12-29 | 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 |
| CN114136634A (en) * | 2021-11-30 | 2022-03-04 | 中国航发湖南动力机械研究所 | Engine hanging rack guiding and positioning device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110441064A (en) * | 2019-08-13 | 2019-11-12 | 中国航发贵阳发动机设计研究所 | A kind of auxiliary hanging pull rod assembly method optimizing aeroplane engine machine vibration |
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| CN112985816A (en) * | 2021-03-18 | 2021-06-18 | 北京航空航天大学 | Variable-size universal miniature turbine engine test bed |
| CN114136634A (en) * | 2021-11-30 | 2022-03-04 | 中国航发湖南动力机械研究所 | Engine hanging rack guiding and positioning device |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN106769063B (en) | 2019-01-25 |
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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 |
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