CN202582786U - Test device of aircraft engine bleed air system temperature sensor - Google Patents
Test device of aircraft engine bleed air system temperature sensor Download PDFInfo
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- CN202582786U CN202582786U CN 201220145282 CN201220145282U CN202582786U CN 202582786 U CN202582786 U CN 202582786U CN 201220145282 CN201220145282 CN 201220145282 CN 201220145282 U CN201220145282 U CN 201220145282U CN 202582786 U CN202582786 U CN 202582786U
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- temperature sensor
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- temperature
- bleed air
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Abstract
The utility model discloses a test device of an aircraft engine bleed air system temperature sensor. A first test pipeline inputs compressed air to a test cavity, a second test pipeline excludes compressed gas, and a first shutoff valve and a second shutoff valve can control the flow rate of the compressed air which flows through the first test pipeline and the second test pipeline according to needs, and controls air pressure in the test cavity. A heating controller which is connected with a power supply can control heating quantity of a heating element, and temperature in the test cavity is controlled. So, the simulation of a working environment of the temperature sensor of an aircraft engine bleed air system is realized. Since the test device is simple in structure, used compressed air can be normal compressed air, using expensive bleed air equipment is not needed, and production cost and use cost are low.
Description
Technical field
The utility model relates to a kind of device that is used to detect the parts of aeromotor bleed air system, relates in particular to a kind of proving installation of aeromotor bleed air system temperature sensor.
Background technology
The engine bleed control system is used to adjust the high temperature and high pressure gas that engine compressor is drawn, and with the pressurized air that obtains directly to use, it generally comprises valve, pressure governor, temperature sensor, heating radiator and pipeline.Temperature sensor wherein is the critical piece of control bleed temperature, is used for converting the temperature signal of bleed into pressure signal.It is believed that for a long time and need test down with the on all four analog operation environment of duty the used temperature sensor of engine bleed control system; Also have only through the temperature sensor of test like this and just can guarantee down normal in working order work; Because the working environment of the temperature sensor that the engine bleed control system is used is comparatively complicated, relates to high temperature, high pressure and high velocity air.For this reason in the prior art, the proving installation of the used temperature sensor of engine bleed control system comprises testing conduit, bleed equipment and flow controller at least.With reference to Fig. 1, said flow controller is installed on the said testing conduit, and said testing conduit is connected to the output terminal of said bleed equipment.Said bleed device provides the air of predetermined temperature, pressure and flow in pipeline; Such proving installation is bulky; Need special-purpose factory building to install, production cost and use cost are all higher, what is more important; Such equipment can't cooperate on-the-spot test, and obviously prior art has further improved necessity.
The utility model content
The technical matters that the utility model will solve is to provide a kind of proving installation of aeromotor bleed air system temperature sensor, can reduce production costs and use cost, can cooperate on-the-spot test simultaneously.
For solving the problems of the technologies described above, the utility model adopts following technical proposals.
A kind of proving installation of aeromotor bleed air system temperature sensor; It is characterized in that: comprise test chamber, be connected with power supply add temperature controller, be provided with first turn-off first testing conduit of valve and be provided with second turn-off valve second testing conduit; The mounting groove that said test chamber has gas input end, gas output end, heats element and be used to install temperature sensor to be measured; Said first testing conduit is connected to said gas input end; Said second testing conduit is connected to gas output end, and the said element of heating is connected to and saidly adds temperature controller and be positioned at said test chamber.
The inventor recognizes through research and analysis; Though the gas parameter of the working environment of temperature sensor comprises temperature, pressure and flow; But what influence the temperature sensor operating mode mainly is temperature and pressure; The influence of flow is very little on the one hand, and the influence of flow also is reflected on the pressure to a certain extent on the other hand, gets final product so the temperature of proving installation and pressure can meet the demands.
In the utility model; Said first testing conduit is imported pressurized air to test chamber; Said second testing conduit is got rid of pressure gas; Said first, second turn-offs the compressed-air actuated flow that valve can be controlled flow through first testing conduit and second testing conduit as required, and then the air pressure in the control test chamber.Again, what be connected with power supply adds the thermal value that temperature controller can be controlled the element of heating, and then the temperature in the control test chamber.So, just, realized simulation to the working environment of the temperature sensor of aeromotor bleed air system.Because the utility model is simple in structure, the pressurized air of use can be common pressurized air, need not use expensive bleed equipment, and production cost and use cost are all lower.Obviously, the goal of the invention of the utility model is able to solve.
In the proving installation of this aeromotor bleed air system temperature sensor of the utility model, also comprise the safe pressure relieving valve that is used to control the pressure in the said test chamber, said safety relief valve is fixed on the said test chamber.Said safe pressure relieving valve can be in test chamber air pressure discharge unnecessary gas when surpassing predetermined value.In addition, the flow control through the second shutoff valve also can realize the air pressure control to test chamber.
In the proving installation of this aeromotor bleed air system temperature sensor of the utility model, also comprise the temperature probe that is used to measure said test cavity temperature, the output terminal of said temperature probe is connected to the said temperature controller that adds.Said temperature probe can feed back to the temperature signal in the test chamber and add temperature controller, said add temperature controller according to this temperature signal the heat thermal value of element of adjustment.That is, saidly add temperature controller, the element of heating, temperature probe and test chamber form a closed-loop control system, this closed-loop control system can promote the temperature precision in the test chamber.
Implement the proving installation of this aeromotor bleed air system temperature sensor of the utility model; Have following beneficial effect: said test chamber utilizes common pressurized air; When simulating the working environment of temperature sensor, cancelled the bleed device; Reduce cost and volume, be convenient to on-the-spot test.Because the compression gas flow in the test chamber is small, the gas parameter of each position is comparatively even, only needs near the temperature probe that installation one is used to feed back tested temperature sensor to get final product, and has reduced number of components and parts, has reduced cost.
Description of drawings
Fig. 1 is the work synoptic diagram of the sort of proving installation of prior art, and the direction of arrow is the flow direction of pressure gas among the figure;
Fig. 2 is the work synoptic diagram of proving installation of this aeromotor bleed air system temperature sensor of the utility model, and the direction of arrow is the flow direction of pressure gas among the figure;
Fig. 3 is the structural representation of proving installation among Fig. 2, has mainly showed the primary structure of proving installation.
In the accompanying drawing: test chamber 1, gas input end 11, gas output end 12, the element 13 of heating, temperature sensor 14, safe pressure relieving valve 15, temperature probe 16, power supply 2, add temperature controller 3, first testing conduit 41, second testing conduit 42, first and turn-off valve 51, second and turn-off valve 52, pressure governor 6, tensimeter 7, air supply channel 8.
Embodiment
Below in conjunction with accompanying drawing the utility model is done further detailed description.
Proving installation like this aeromotor bleed air system temperature sensor of Fig. 2, the utility model shown in 3; Comprise test chamber 1, be connected with power supply 2 add temperature controller 3, be provided with first turn-off first testing conduit 41 of valve 51 and be provided with second turn-off valve 52 second testing conduit 42; The mounting groove that said test chamber 1 has gas input end 11, gas output end 12, heats element 13 and be used to install temperature sensor to be measured 14; Said first testing conduit 41 is connected to said gas input end 11; Said second testing conduit 42 is connected to gas output end 12, and the said element 13 of heating is connected to and saidly adds temperature controller 13 and be positioned at said test chamber 1.
The utility model also comprises the safe pressure relieving valve 15 that is used to control the pressure in the said test chamber 1; With the temperature probe 16 that is used to measure temperature in the said test chamber 1; Said safety relief valve 15 is fixed on the said test chamber 1, and the output terminal of said temperature probe 16 is connected to and adds temperature controller 3.
Among the figure; Pressurized air gets into test chamber 1 through first testing conduit 41; And through second testing conduit, 42 outflow test chambers 1; Said first testing conduit 41 and second testing conduit 41 are respectively equipped with the first shutoff valve 51 and second that is used for Control Flow and turn-off valve 52, turn-off the flow of valve 52 according to the first shutoff valve 51 and second and adjust the air pressure in the test chamber.Pressure governor 6 and tensimeter 7 also are installed on said first testing conduit 41.
The duty of proving installation that has shown this aeromotor bleed air system temperature sensor of the utility model like Fig. 2.Temperature sensor 14 to be measured is corresponding to air supply channel 8 and test chamber 1, and said air supply channel 8 is connected to the controlled end of said temperature sensor 14 to be measured, and said test chamber 1 is connected to the control end of said temperature sensor 14 to be measured.That is, regard said air supply channel 8 as working gas that the cabin is provided, regard said test chamber 1 as be connected to engine bleed air system.When gas parameter is identical with the bleed air system gaseous environment in test chamber 1, detect the exhaust condition of said air supply channel 8.
In the proving installation of this aeromotor bleed air system temperature sensor of the utility model; The gas of the working environment of temperature sensor 14 is simulated by test chamber 1; The pressure gas in first testing conduit 41 need not pressure gas and before getting into test chamber 1, just has the predetermined parameters value, so can be the common pressure gas identical with the controlled end of temperature sensor 14.Owing to cancelled bleed equipment, so reduced testing cost and improved the portability of proving installation.
Claims (3)
1. the proving installation of an aeromotor bleed air system temperature sensor; It is characterized in that: comprise test chamber, be connected with power supply add temperature controller, be provided with first turn-off first testing conduit of valve and be provided with second turn-off valve second testing conduit; The mounting groove that said test chamber has gas input end, gas output end, heats element and be used to install temperature sensor to be measured; Said first testing conduit is connected to said gas input end; Said second testing conduit is connected to gas output end, and the said element of heating is connected to and saidly adds temperature controller and be positioned at said test chamber.
2. the proving installation of aeromotor bleed air system temperature sensor according to claim 1 is characterized in that: also comprise the safe pressure relieving valve that is used to control the pressure in the said test chamber, said safety relief valve is fixed on the said test chamber.
3. the proving installation of aeromotor bleed air system temperature sensor according to claim 1 is characterized in that: also comprise the temperature probe that is used to measure said test cavity temperature, the output terminal of said temperature probe is connected to the said temperature controller that adds.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220145282 CN202582786U (en) | 2012-04-09 | 2012-04-09 | Test device of aircraft engine bleed air system temperature sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220145282 CN202582786U (en) | 2012-04-09 | 2012-04-09 | Test device of aircraft engine bleed air system temperature sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202582786U true CN202582786U (en) | 2012-12-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220145282 Expired - Lifetime CN202582786U (en) | 2012-04-09 | 2012-04-09 | Test device of aircraft engine bleed air system temperature sensor |
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| CN (1) | CN202582786U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104108474A (en) * | 2013-04-16 | 2014-10-22 | 通用电气航空系统有限公司 | Method For Predicting A Bleed Air System Fault |
| GB2514108A (en) * | 2013-05-13 | 2014-11-19 | Ge Aviat Systems Ltd | Method for diagnosing a bleed air system fault |
| US9449438B2 (en) | 2013-04-16 | 2016-09-20 | Ge Aviation Systems Limited | Methods for predicting a speed brake system fault |
| CN108593144A (en) * | 2018-03-13 | 2018-09-28 | 安徽瑞鑫自动化仪表有限公司 | A kind of temperature sensor quality detecting system |
| CN111220344A (en) * | 2019-11-05 | 2020-06-02 | 天津航空机电有限公司 | Test system for simulating high-temperature air intake of aircraft engine cabin |
| CN111964910A (en) * | 2020-06-30 | 2020-11-20 | 中国航发南方工业有限公司 | Engine air-entraining test device, design method and test method |
-
2012
- 2012-04-09 CN CN 201220145282 patent/CN202582786U/en not_active Expired - Lifetime
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104108474A (en) * | 2013-04-16 | 2014-10-22 | 通用电气航空系统有限公司 | Method For Predicting A Bleed Air System Fault |
| GB2513132A (en) * | 2013-04-16 | 2014-10-22 | Ge Aviat Systems Ltd | Method for predicting a bleed air system fault |
| GB2513132B (en) * | 2013-04-16 | 2015-05-27 | Ge Aviat Systems Ltd | Method for predicting a bleed air system fault |
| US9449438B2 (en) | 2013-04-16 | 2016-09-20 | Ge Aviation Systems Limited | Methods for predicting a speed brake system fault |
| GB2514108A (en) * | 2013-05-13 | 2014-11-19 | Ge Aviat Systems Ltd | Method for diagnosing a bleed air system fault |
| GB2514108B (en) * | 2013-05-13 | 2015-06-24 | Ge Aviat Systems Ltd | Method for diagnosing a bleed air system fault |
| US9555903B2 (en) | 2013-05-13 | 2017-01-31 | Ge Aviation Systems Limited | Method for diagnosing a bleed air system fault |
| CN108593144A (en) * | 2018-03-13 | 2018-09-28 | 安徽瑞鑫自动化仪表有限公司 | A kind of temperature sensor quality detecting system |
| CN111220344A (en) * | 2019-11-05 | 2020-06-02 | 天津航空机电有限公司 | Test system for simulating high-temperature air intake of aircraft engine cabin |
| CN111964910A (en) * | 2020-06-30 | 2020-11-20 | 中国航发南方工业有限公司 | Engine air-entraining test device, design method and test method |
| CN111964910B (en) * | 2020-06-30 | 2022-04-19 | 中国航发南方工业有限公司 | Engine air-entraining test device, design method and test method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: SHENZHEN AIRLINES CO., LTD. Free format text: FORMER OWNER: CHEN YONG Effective date: 20140317 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20140317 Address after: 518000 Shenzhen Airlines office building, Baoan District International Airport, Shenzhen, Baoan, Guangdong Patentee after: Shenzhen Airlines Address before: 518000, Shenzhen, Guangdong province Futian District Xiang Jing building 2 11H Patentee before: Chen Yong |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121205 |