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 PDF

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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
Authority
CN
China
Prior art keywords
actuating motor
pressure cowling
flange
support
cloche
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.)
Pending
Application number
CN2013102520082A
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Chinese (zh)
Inventor
陈先增
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BEIJING SHUGUANG AERO ELECTRICAL Co Ltd
Original Assignee
BEIJING SHUGUANG AERO ELECTRICAL Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by BEIJING SHUGUANG AERO ELECTRICAL Co Ltd filed Critical BEIJING SHUGUANG AERO ELECTRICAL Co Ltd
Priority to CN2013102520082A priority Critical patent/CN103411738A/en
Publication of CN103411738A publication Critical patent/CN103411738A/en
Pending legal-status Critical Current

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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

The air-tightness detection device of airplane auxiliary power engine starting motor
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.
CN2013102520082A 2013-06-24 2013-06-24 Air tightness detection device of aircraft auxiliary power engine starting motor Pending CN103411738A (en)

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)

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CN103411738A true CN103411738A (en) 2013-11-27

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CN (1) CN103411738A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
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

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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 Method and device for inspecting liquid container
CN1514162A (en) * 2002-12-31 2004-07-21 中国科学院广州能源研究所 Liquid sealing device
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

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 The detection that 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 Method and device for inspecting liquid container
CN1514162A (en) * 2002-12-31 2004-07-21 中国科学院广州能源研究所 Liquid sealing device
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

Cited By (9)

* Cited by examiner, † Cited by third party
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
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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