CN203719899U - Reverse thrust test vehicle of aeroturbine fan engine - Google Patents
Reverse thrust test vehicle of aeroturbine fan engine Download PDFInfo
- Publication number
- CN203719899U CN203719899U CN201320824069.7U CN201320824069U CN203719899U CN 203719899 U CN203719899 U CN 203719899U CN 201320824069 U CN201320824069 U CN 201320824069U CN 203719899 U CN203719899 U CN 203719899U
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- China
- Prior art keywords
- thrust
- reverse
- dollies
- push away
- fan engine
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- Expired - Lifetime
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- 238000012360 testing method Methods 0.000 title claims abstract description 43
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- Testing Of Engines (AREA)
Abstract
The utility model relates to a reverse thrust test vehicle of an aeroturbine fan engine. The test vehicle comprises a large reverse-thrust car (1) and two reverse-thrust dollies (2), wherein two reverse-thrust spiral cases (3) are respectively mounted on the two reverse-thrust dollies (2), a transverse track (4) is arranged at the upper surface of the large reverse-thrust car (1), the two reverse-thrust dollies (2) move relative to each other lengthwise or in the opposite directions along the track (4), the large reverse-thrust car (1) moves vertically to a test position along ground rails (5) of an aeroturbine fan engine testing workshop and is fixed to the ground, and the two reverse-thrust dollies (2) move relative to each other lengthwise to test positions along the track (4) to enable that the two reverse-thrust spiral cases (3) respectively correspond reverse-thrust exhaust openings (6) of the aeroturbine fan engine and that the two reverse-thrust dollies (2) are positioned and locked with the large reverse-thrust car (1). The test vehicle is compact in structure, and convenient to install and transport, reduces the total weight of equipment, and ensures the using performance.
Description
Technical field
The utility model is a kind of aerial turbo fan engine reaction thrust instruction carriage, belongs to Aviation Test equipment.
Background technology
Aerial turbo fan engine anti-thrust system produces deboost by the direction that changes fan exhaust, for aircraft landing or end take-off process and reduce the speed of aircraft.Each engine respectively has a set of anti-pushing system, the anti-pushing system of every cover is divided into left and right two parts, two parts simultaneously but work alone, every part has an anti-radome fairing that pushes away, when counter when pushing away radome fairing and moving backward to expanded position, engine by-pass air duct fan exhaust is radial discharges forward, produces reaction thrust; According to testing requirements, need accurately to measure engine reverse thrust size, for ensureing that the reaction thrust air-flow of engine ejection does not affect the normal work of engine, it need be turned back to 180 ° by guiding device, discharge backward.Push away when experiment when engine by-pass air duct is counter, reaction thrust guiding device should counter to push away exhausr port corresponding with engine.
Current domestic reaction thrust water conservancy diversion test unit all adopts fixed, test mainly for main duct, there is no the proving installation of the engine of large bypass ratio band by-pass air duct THR REV, fixed reaction thrust water conservancy diversion test unit can not be tested by-pass air duct, because reaction thrust test is an important tests content of development aeromotor, add domestic without similar experience, foreign data scarcity, for engine reverse thrust is measured accurately, be therefore necessary to design the testing equipment of a set of measurement reaction thrust.
Summary of the invention
The utility model designs a kind of aerial turbo fan engine reaction thrust laboratory vehicle is provided for above-mentioned prior art situation just, the reaction thrust test of the engine of the large bypass ratio band of the realization by-pass air duct THR REV of its object makes test cell can also carry out conventional test simultaneously.
The purpose of this utility model realizes by following technical measures:
This kind of aerial turbo fan engine reaction thrust instruction carriage, it is characterized in that: this instruction carriage comprises anti-cart (1) and two the anti-dollies (2) that push away of pushing away, two anti-spiral cases (3) that push away are arranged on respectively two counter pushing away on dolly (2), at the anti-upper surface that pushes away cart (1), cross track (4) is set, do in opposite directions or counter motion along track (4) at two anti-dollies (2) that push away, the anti-cart (1) that pushes away is along aerial turbo fan engine test cell track (5) testing position that travels longitudinally, and fix with ground, two anti-dollies (2) that push away are made move toward one another to testing position along track (4), make two instead to push away spiral case (3) and aerial turbo fan engine counter to push away exhausr port (6) corresponding, and by two anti-dolly (2) and anti-cart (1) positioning and lockings that push away of pushing away.
The utility model is by anti-cart (1), anti-dolly (2) and anti-spiral case (3) the modular combination mode that pushes away of pushing away of pushing away, and has realized the test of aerial turbo fan engine reaction thrust.The utility model has the advantages that: when engine reverse thrust test, reaction thrust cart (1) and the anti-dolly (2) that pushes away are driven to testing position, counter to push away exhausr port (6) corresponding with engine, and now test cell has just become the test cell that can complete reaction thrust test mission; After test completes, the anti-dolly (2) that pushes away is laterally divided right and left, instead push away cart (1) and the anti-dolly (2) that pushes away drives to rear portion, test cell Kao Qiang, at this time conventional test just can be carried out in test cell, ensure the compatibility of test cell, greatly improved test cell capacity utilization.In addition, this instruction carriage compact conformation, has alleviated Whole Equipment weight, is convenient to install and transport, has guaranteed the usability of device simultaneously.
Brief description of the drawings
Fig. 1 is the schematic diagram of instruction carriage in test cell idle condition
Fig. 2 is the schematic diagram of instruction carriage at test cell trystate
Fig. 3 be in Fig. 2 K to view
Embodiment
Below with reference to drawings and Examples, the utility model product is further described:
Shown in accompanying drawing 1～3, this kind of aerial turbo fan engine reaction thrust instruction carriage, it is characterized in that: this instruction carriage comprises anti-cart 1 and two the anti-dollies 2 that push away of pushing away, two anti-spiral cases 3 that push away are arranged on respectively two counter pushing away on dolly 2, at the anti-upper surface that pushes away cart 1, cross track 4 is set, do in opposite directions or counter motion along track 4 at two anti-dollies 2 that push away, before test, will instead push away cart 1 along aerial turbo fan engine test cell track 5 testing position that travels longitudinally, and fix with ground, two anti-dollies 2 that push away are made move toward one another to testing position along track 4, make two instead to push away spiral case 3 and aerial turbo fan engine counter to push away exhausr port 6 corresponding, the exhausr port of the by-pass air duct thrust reverser of aerial turbo fan engine is generally positioned in engine middle part, and by two anti-dolly 2 and anti-cart 1 positioning and lockings that push away of pushing away.
After having tested, two anti-dollies 2 that push away are dismantled with anti-cart 1 positioning and locking device that pushes away, two anti-dollies 2 that push away are laterally moved to test front position along track 4, and positioning and locking.To instead push away cart 1 and ground connection disassembling, being along the longitudinal movement to is rear portion, workshop and metope laminating, and and ground lock.
Claims (1)
1. an aerial turbo fan engine reaction thrust instruction carriage, it is characterized in that: this instruction carriage comprises anti-cart (1) and two the anti-dollies (2) that push away of pushing away, two anti-spiral cases (3) that push away are arranged on respectively two counter pushing away on dolly (2), at the anti-upper surface that pushes away cart (1), cross track (4) is set, do in opposite directions or counter motion along track (4) at two anti-dollies (2) that push away, the anti-cart (1) that pushes away is along aerial turbo fan engine test cell track (5) testing position that travels longitudinally, and fix with ground, two anti-dollies (2) that push away are made move toward one another to testing position along track (4), make two instead to push away spiral case (3) and aerial turbo fan engine counter to push away exhausr port (6) corresponding, and by two anti-dolly (2) and anti-cart (1) positioning and lockings that push away of pushing away.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320824069.7U CN203719899U (en) | 2013-12-12 | 2013-12-12 | Reverse thrust test vehicle of aeroturbine fan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320824069.7U CN203719899U (en) | 2013-12-12 | 2013-12-12 | Reverse thrust test vehicle of aeroturbine fan engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203719899U true CN203719899U (en) | 2014-07-16 |
Family
ID=51159038
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320824069.7U Expired - Lifetime CN203719899U (en) | 2013-12-12 | 2013-12-12 | Reverse thrust test vehicle of aeroturbine fan engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203719899U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043781A (en) * | 2014-12-05 | 2015-11-11 | 中国航空规划建设发展有限公司 | Volute for conducting reaction thrust test on external duct in aircraft engine |
| CN107588955A (en) * | 2017-10-18 | 2018-01-16 | 中国航发成都发动机有限公司 | It is a kind of to push away experimental rig for the counter of engine THR REV life performance detection |
| CN107869410A (en) * | 2016-09-28 | 2018-04-03 | 中国航发商用航空发动机有限责任公司 | Contain outside fast changeable and contain outside the composite technology of runner |
| CN111706715A (en) * | 2020-06-24 | 2020-09-25 | 中航工程集成设备有限公司 | High-temperature large-caliber calibration high-pipeline support |
| CN112747933A (en) * | 2020-12-23 | 2021-05-04 | 襄阳航顺航空科技有限公司 | Test stand for gas turbine starter of Jianhong seven aircraft |
| CN114112404A (en) * | 2021-11-11 | 2022-03-01 | 中国航发沈阳发动机研究所 | Test run baffle structure of engine thrust reverser and assembling method thereof |
-
2013
- 2013-12-12 CN CN201320824069.7U patent/CN203719899U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043781A (en) * | 2014-12-05 | 2015-11-11 | 中国航空规划建设发展有限公司 | Volute for conducting reaction thrust test on external duct in aircraft engine |
| CN107869410A (en) * | 2016-09-28 | 2018-04-03 | 中国航发商用航空发动机有限责任公司 | Contain outside fast changeable and contain outside the composite technology of runner |
| CN107588955A (en) * | 2017-10-18 | 2018-01-16 | 中国航发成都发动机有限公司 | It is a kind of to push away experimental rig for the counter of engine THR REV life performance detection |
| CN111706715A (en) * | 2020-06-24 | 2020-09-25 | 中航工程集成设备有限公司 | High-temperature large-caliber calibration high-pipeline support |
| CN111706715B (en) * | 2020-06-24 | 2021-12-24 | 中航工程集成设备有限公司 | High-temperature large-caliber calibration high-pipeline support |
| CN112747933A (en) * | 2020-12-23 | 2021-05-04 | 襄阳航顺航空科技有限公司 | Test stand for gas turbine starter of Jianhong seven aircraft |
| CN112747933B (en) * | 2020-12-23 | 2023-02-10 | 襄阳航顺航空科技有限公司 | Test stand for gas turbine starter of Jianhong seven aircraft |
| CN114112404A (en) * | 2021-11-11 | 2022-03-01 | 中国航发沈阳发动机研究所 | Test run baffle structure of engine thrust reverser and assembling method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 100011 Beijing Xicheng District Dewai Street No. 12 Patentee after: CHINA AVIATION PLANNING AND DESIGN INSTITUTE (Group) Co.,Ltd. Patentee after: AVIC APC INTEGRATION EQUIPMENT Co.,Ltd. Address before: 100011 Beijing Xicheng District Dewai Street No. 12 Patentee before: China Aviation Planning and Construction Development Co.,Ltd. Patentee before: AVIC APC INTEGRATION EQUIPMENT Co.,Ltd. |
|
| CX01 | Expiry of patent term |
Granted publication date: 20140716 |
|
| CX01 | Expiry of patent term |