CN103411738A - Air tightness detection device of aircraft auxiliary power engine starting motor - Google Patents
Air tightness detection device of aircraft auxiliary power engine starting motor Download PDFInfo
- Publication number
- CN103411738A CN103411738A CN2013102520082A CN201310252008A CN103411738A CN 103411738 A CN103411738 A CN 103411738A CN 2013102520082 A CN2013102520082 A CN 2013102520082A CN 201310252008 A CN201310252008 A CN 201310252008A CN 103411738 A CN103411738 A CN 103411738A
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- Prior art keywords
- actuating motor
- pressure cowling
- flange
- support
- cloche
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Links
- 238000001514 detection method Methods 0.000 title claims abstract description 22
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 10
- 238000012423 maintenance Methods 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000007789 sealing Methods 0.000 abstract description 2
- 208000034423 Delivery Diseases 0.000 abstract 1
- 239000011521 glass Substances 0.000 abstract 1
- FGRBYDKOBBBPOI-UHFFFAOYSA-N 10,10-dioxo-2-[4-(N-phenylanilino)phenyl]thioxanthen-9-one Chemical compound O=C1c2ccccc2S(=O)(=O)c2ccc(cc12)-c1ccc(cc1)N(c1ccccc1)c1ccccc1 FGRBYDKOBBBPOI-UHFFFAOYSA-N 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 210000003141 lower extremity Anatomy 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- Examining Or Testing Airtightness (AREA)
Abstract
The invention relates to an air tightness detection device of an aircraft auxiliary power engine starting motor, and the air tightness detection device belongs to the air tightness detection technology. The air tightness detection device is characterized by comprising a water tank (1), a bracket (2), a glass cover (3), a pressurizing cover (4), a pressurizing hose (5), a clamping hoop assembly (6), a sealing ring (7), a V-shaped block (8), an exhaust hose (9) and a detection cup (10). The air tightness detection device solves the difficulty of carrying out air tightness detection on novel starting motors, and ensures the normal delivery of the starting motor.
Description
Technical field
The invention belongs to the impermeability detection technique, relate to a kind of air-tightness detection device of airplane auxiliary power engine starting motor.
Background technology
A kind of actuating motor be arranged on certain type aircraft auxiliary power unit enters motor internal in order to prevent from the lubricating oil of casing, at its front end end cover motor output shaft end, seal assembly is housed, all must the sealing property of motor front end cover output shaft be detected while requiring Motor Production Test to check and accept and after some environmental test end.At present do not carry out the device of above-mentioned detection, affected the payment of this actuating motor.
Summary of the invention
The objective of the invention is: propose a kind of air-tightness detection device of airplane auxiliary power engine starting motor, to solve the difficult problem that the Novel starting motor is carried out to the impermeability detection, guarantee the normal payment of this type actuating motor.
Technical scheme of the present invention is: the air-tightness detection device of airplane auxiliary power engine starting motor is characterized in that: it is comprised of tank 1, support 2, cloche 3, pressure cowling 4, forcing hose 5, hoop component 6, O-ring seal 7, V-block 8, exhaust hose 9 and detection cup 10, tank 1 is the rectangular parallelepiped that a upper end is opened wide, in tank 1, fill water, in tank 1, placing the support 2 with rectangular parallelepiped profile, the upper surface of support 2 is the plane higher than the water surface, cloche 3 is rectangular parallelepipeds that a lower end is opened wide, the cross-sectional profiles of cloche 3 is surrounded by the cross-sectional profiles of tank 1, simultaneously, the cross-sectional profiles of cloche 3 surrounds the cross-sectional profiles of support 2, exhaust fitting with an exhaust pipe collar 3a is arranged on the upper surface of cloche 3, one end of exhaust hose 9 is enclosed within exhaust fitting 3a and goes up and be deflated pipe collar locking, detecting the cup 10 interior suds of containing, the other end of exhaust hose 9 inserts and detects in cup 10 suds, pressure cowling 4 is a plectane and the cap member that annulus connects to form, the left port of annulus and the circumference of plectane are connected to integral body, a pressurized joint for pipeline 4a with the pressurization pipe collar is arranged on the left side of pressure cowling 4, one end of forcing hose 5 is enclosed within the upper also pressurized pipe collar locking of pressurized joint for pipeline 4a, the external diameter of pressure cowling 4 annulus parts is identical with the external diameter of detected actuating motor 11, right output port in pressure cowling 4 annulus parts has the pressure cowling flange, the external diameter of pressure cowling flange is identical with the external diameter of detected actuating motor 11 mounting flanges, the mounting flange of pressure cowling flange and detected actuating motor 11 is involutory, between the mounting flange of pressure cowling flange and detected actuating motor 11, O-ring seal 7 is arranged, by hoop component 6, the mounting flange of pressure cowling flange and detected actuating motor 11 is connected to integral body, V-block 8 is placed on the right part of the detected actuating motor 11 of support 2 upper supports, makes detected actuating motor 11 maintenance levels.
Advantage of the present invention is: proposed a kind of air-tightness detection device of airplane auxiliary power engine starting motor, solved a difficult problem of the Novel starting motor being carried out to the impermeability detection, guaranteed the normal payment of this type actuating motor.
The accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Embodiment
Below the present invention is described in further details.Referring to Fig. 1, the air-tightness detection device of airplane auxiliary power engine starting motor is characterized in that: it is comprised of tank 1, support 2, cloche 3, pressure cowling 4, forcing hose 5, hoop component 6, O-ring seal 7, V-block 8, exhaust hose 9 and detection cup 10, tank 1 is the rectangular parallelepiped that a upper end is opened wide, in tank 1, fill water, in tank 1, placing the support 2 with rectangular parallelepiped profile, the upper surface of support 2 is the plane higher than the water surface, cloche 3 is rectangular parallelepipeds that a lower end is opened wide, the cross-sectional profiles of cloche 3 is surrounded by the cross-sectional profiles of tank 1, simultaneously, the cross-sectional profiles of cloche 3 surrounds the cross-sectional profiles of support 2, exhaust fitting with an exhaust pipe collar 3a is arranged on the upper surface of cloche 3, one end of exhaust hose 9 is enclosed within exhaust fitting 3a and goes up and be deflated pipe collar locking, detecting the cup 10 interior suds of containing, the other end of exhaust hose 9 inserts and detects in cup 10 suds, pressure cowling 4 is a plectane and the cap member that annulus connects to form, the left port of annulus and the circumference of plectane are connected to integral body, a pressurized joint for pipeline 4a with the pressurization pipe collar is arranged on the left side of pressure cowling 4, one end of forcing hose 5 is enclosed within the upper also pressurized pipe collar locking of pressurized joint for pipeline 4a, the external diameter of pressure cowling 4 annulus parts is identical with the external diameter of detected actuating motor 11, right output port in pressure cowling 4 annulus parts has the pressure cowling flange, the external diameter of pressure cowling flange is identical with the external diameter of detected actuating motor 11 mounting flanges, the mounting flange of pressure cowling flange and detected actuating motor 11 is involutory, between the mounting flange of pressure cowling flange and detected actuating motor 11, O-ring seal 7 is arranged, by hoop component 6, the mounting flange of pressure cowling flange and detected actuating motor 11 is connected to integral body, V-block 8 is placed on the right part of the detected actuating motor 11 of support 2 upper supports, makes detected actuating motor 11 maintenance levels.
Using method of the present invention is: first with hoop component 6, the front end of pressure cowling 4 and detected actuating motor 11 is fixed, erect with V-block 8 rear end of detected actuating motor 11, keeps detected actuating motor 11 to lie in a horizontal plane on support 2.In tank 1, inject suitable quantity of water, the water surface is lower than the upper surface of support 2, then cloche 3 covered on to the outside of support 2.Forcing hose 5 reaches the outside of tank 1 from the lower limb of cloche 3.Until cloche 3 inner and outer air pressures, equate after (the inside and outside water surface is parallel), by 5 pairs of pressure cowlings 4 of forcing hose, be pressurized to and be not less than 1.8 atmospheric pressure, and pressurize 1 minute, whether observation is placed on exhaust hose 9 one ends that detect in cup 10 suds and leaks gas, if the phenomenon increased does not appear in the bubble in suds, judge that the actuating motor impermeability is qualified; Otherwise judge that the actuating motor impermeability is defective.
Embodiments of the invention, through evidence, can detect the impermeability that is detected actuating motor reliably, solved a difficult problem of the Novel starting motor being carried out to the impermeability detection, guaranteed the normal payment of this type actuating motor.
Claims (1)
1. the air-tightness detection device of airplane auxiliary power engine starting motor is characterized in that: it is by tank (1), support (2), cloche (3), pressure cowling (4), forcing hose (5), hoop component (6), O-ring seal (7), V-block (8), exhaust hose (9) and detect cup (10) and form, tank (1) is the rectangular parallelepiped that a upper end is opened wide, tank fills water in (1), in tank (1), placing the support (2) with rectangular parallelepiped profile, the upper surface of support (2) is the plane higher than the water surface, cloche (3) is the rectangular parallelepiped that a lower end is opened wide, the cross-sectional profiles of cloche (3) is surrounded by the cross-sectional profiles of tank (1), simultaneously, the cross-sectional profiles of cloche (3) surrounds the cross-sectional profiles of support (2), an exhaust fitting with the exhaust pipe collar (3a) is arranged on the upper surface of cloche (3), one end of exhaust hose (9) is enclosed within exhaust fitting (3a) and goes up and be deflated pipe collar locking, in detecting cup (10), containing suds, the other end of exhaust hose (9) inserts and detects in cup (10) suds, pressure cowling (4) is a plectane and the cap member that annulus connects to form, the left port of annulus and the circumference of plectane are connected to integral body, a pressurized joint for pipeline (4a) with the pressurization pipe collar is arranged on the left side of pressure cowling (4), one end of forcing hose (5) is enclosed within the upper also pressurized pipe collar locking of pressurized joint for pipeline (4a), the external diameter of pressure cowling (4) annulus part is identical with the external diameter of detected actuating motor (11), right output port in pressure cowling (4) annulus part has the pressure cowling flange, the external diameter of pressure cowling flange is identical with the external diameter of detected actuating motor (11) mounting flange, the mounting flange of pressure cowling flange and detected actuating motor (11) is involutory, between the mounting flange of pressure cowling flange and detected actuating motor (11), O-ring seal (7) is arranged, by hoop component (6), the mounting flange of pressure cowling flange and detected actuating motor (11) is connected to integral body, V-block (8) is placed on the right part of the detected actuating motor (11) of support (2) upper support, makes detected actuating motor (11) maintenance level.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102520082A CN103411738A (en) | 2013-06-24 | 2013-06-24 | Air tightness detection device of aircraft auxiliary power engine starting motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102520082A CN103411738A (en) | 2013-06-24 | 2013-06-24 | Air tightness detection device of aircraft auxiliary power engine starting motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103411738A true CN103411738A (en) | 2013-11-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013102520082A Pending CN103411738A (en) | 2013-06-24 | 2013-06-24 | Air tightness detection device of aircraft auxiliary power engine starting motor |
Country Status (1)
| Country | Link |
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| CN (1) | CN103411738A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034487A (en) * | 2014-06-25 | 2014-09-10 | 江苏协昌电子科技有限公司 | Electrocar motor leakage testing device |
| CN104907956A (en) * | 2015-05-08 | 2015-09-16 | 无锡新宏泰电器科技股份有限公司 | Clamp for examining air tightness of end cover part |
| CN104034487B (en) * | 2014-06-25 | 2016-11-30 | 江苏协昌电子科技有限公司 | A kind of electric vehicle motor leak-checking apparatus |
| CN106226060A (en) * | 2016-08-30 | 2016-12-14 | 成都飞亚航空设备应用研究所有限公司 | Aircraft auxiliary power plant test system |
| CN109622542A (en) * | 2018-12-06 | 2019-04-16 | 中国航发贵州黎阳航空动力有限公司 | Fanjet bearing case bearing insert processes protective device and method |
| CN113340538A (en) * | 2021-08-05 | 2021-09-03 | 南通高扬电机有限公司 | Waterproof detection device of micro motor |
| CN115127740A (en) * | 2021-03-26 | 2022-09-30 | 广达电脑股份有限公司 | System and method for detecting case leakage |
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| CN1030643A (en) * | 1987-07-13 | 1989-01-25 | W·L戈尔及合伙人有限公司 | Detection of Gas Leaks |
| JPH03200039A (en) * | 1989-12-28 | 1991-09-02 | Fujitsu Ltd | Waterproof testing method |
| JP2002168725A (en) * | 2000-11-30 | 2002-06-14 | Dainippon Printing Co Ltd | Inspection method and apparatus for liquid container |
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| RU2308691C1 (en) * | 2006-04-26 | 2007-10-20 | Государственное образовательное учреждение высшего профессионального образования "Оренбургский государственный университет" | Method of tightness testing of articles |
| CN101788370A (en) * | 2010-03-25 | 2010-07-28 | 北京三兴汽车有限公司 | Device and method for detecting subsea valve in laboratory |
| CN102393278A (en) * | 2011-09-19 | 2012-03-28 | 武汉工程大学 | Bidirectional sealing performance testing system of mechanical rapping device |
| CN202719203U (en) * | 2012-07-05 | 2013-02-06 | 中冶南方工程技术有限公司 | Deaerated water tank water seal device |
-
2013
- 2013-06-24 CN CN2013102520082A patent/CN103411738A/en active Pending
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| US4419883A (en) * | 1982-03-01 | 1983-12-13 | Gelston Ii N E | Leak detector |
| CN1030643A (en) * | 1987-07-13 | 1989-01-25 | W·L戈尔及合伙人有限公司 | Detection of Gas Leaks |
| JPH03200039A (en) * | 1989-12-28 | 1991-09-02 | Fujitsu Ltd | Waterproof testing method |
| JP2002168725A (en) * | 2000-11-30 | 2002-06-14 | Dainippon Printing Co Ltd | Inspection method and apparatus for liquid container |
| CN1514162A (en) * | 2002-12-31 | 2004-07-21 | 中国科学院广州能源研究所 | a liquid seal |
| RU2308691C1 (en) * | 2006-04-26 | 2007-10-20 | Государственное образовательное учреждение высшего профессионального образования "Оренбургский государственный университет" | Method of tightness testing of articles |
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| CN102393278A (en) * | 2011-09-19 | 2012-03-28 | 武汉工程大学 | Bidirectional sealing performance testing system of mechanical rapping device |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034487A (en) * | 2014-06-25 | 2014-09-10 | 江苏协昌电子科技有限公司 | Electrocar motor leakage testing device |
| CN104034487B (en) * | 2014-06-25 | 2016-11-30 | 江苏协昌电子科技有限公司 | A kind of electric vehicle motor leak-checking apparatus |
| CN104907956A (en) * | 2015-05-08 | 2015-09-16 | 无锡新宏泰电器科技股份有限公司 | Clamp for examining air tightness of end cover part |
| CN106226060A (en) * | 2016-08-30 | 2016-12-14 | 成都飞亚航空设备应用研究所有限公司 | Aircraft auxiliary power plant test system |
| CN106226060B (en) * | 2016-08-30 | 2019-02-05 | 成都飞亚航空设备应用研究所有限公司 | Aircraft auxiliary power plant test macro |
| CN109622542A (en) * | 2018-12-06 | 2019-04-16 | 中国航发贵州黎阳航空动力有限公司 | Fanjet bearing case bearing insert processes protective device and method |
| CN109622542B (en) * | 2018-12-06 | 2021-11-12 | 中国航发贵州黎阳航空动力有限公司 | Turbofan engine supporting case bearing bush machining protection device and method |
| CN115127740A (en) * | 2021-03-26 | 2022-09-30 | 广达电脑股份有限公司 | System and method for detecting case leakage |
| TWI809479B (en) * | 2021-03-26 | 2023-07-21 | 廣達電腦股份有限公司 | Systems and methods of detecting leakage within chassis |
| US11761842B2 (en) | 2021-03-26 | 2023-09-19 | Quanta Computer Inc. | Systems and methods of detecting leakage within a chassis |
| CN113340538A (en) * | 2021-08-05 | 2021-09-03 | 南通高扬电机有限公司 | Waterproof detection device of micro motor |
| CN113340538B (en) * | 2021-08-05 | 2021-10-01 | 南通高扬电机有限公司 | Waterproof detection device of micro motor |
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Application publication date: 20131127 |