CN2913183Y - Booster low-pressure water-removing environment-control device with anti-icing cavity - Google Patents
Booster low-pressure water-removing environment-control device with anti-icing cavity Download PDFInfo
- Publication number
- CN2913183Y CN2913183Y CNU2006201181397U CN200620118139U CN2913183Y CN 2913183 Y CN2913183 Y CN 2913183Y CN U2006201181397 U CNU2006201181397 U CN U2006201181397U CN 200620118139 U CN200620118139 U CN 200620118139U CN 2913183 Y CN2913183 Y CN 2913183Y
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- passage valve
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- temperature
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 7
- 230000008676 import Effects 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 abstract description 4
- 230000007613 environmental effect Effects 0.000 description 4
- 230000001276 controlling effect Effects 0.000 description 3
- 238000002156 mixing Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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Abstract
The utility model relates to a formula of stepping up low pressure removes water ring accuse device in ice chamber is prevented in area for aircraft ring accuse system. The temperature control device consists of a hot path valve, a primary radiator, a secondary radiator, a boosting turbine, a temperature control box, a temperature sensor, a temperature selector and a cold path valve, wherein the hot path valve is connected to a hot path branch conduit, and the cold path valve is connected to a main conduit behind a leading-out point of a hot path branch conduit. The utility model discloses increased a valve in the cold road, through certain temperature control law, when the ability of heating of system is not enough, close little system cold road flow, make the hot road flow strengthen simultaneously to strengthen the system ability of heating. Meanwhile, a structure that a cavity is arranged at the outlet of the turbine is adopted to form a pressure-boosting turbine with an anti-icing cavity, so that the outlet of the turbine is prevented from icing, and the working stability and reliability of the system are improved.
Description
Technical field: the utility model relates to a kind of boost type low pressure with anti-icing chamber that is used for the aircraft environmental control system and removes water ring control device.
Background technology
A few days ago, the boost type low pressure de-watering apparatus that is used for the aircraft environmental control system, mainly by primary heat sink, secondary radiator, the boost type turbine, water separator, hot passage valve, temp. controlling box, temperature sensor, compositions such as temperature selector, system's bleed is divided into cold, hot two-way, hot passage valve is connected on the brasnch conduct of hot road, the primary heat sink outlet is connected with the air compressor end of boost type turbine, blower outlet is connected with the inlet of secondary radiator, the outlet of secondary radiator is connected with the turbine end of boost type turbine, the hot passage valve delivery channel is connected with the exit end of boost type turbine, temperature sensor is connected cold, on the mixed supply conduit in hot road, temperature control box and hot passage valve, cool passage valve, temperature sensor, temperature selector passes through cable connection.The exit end of boost type turbine is an individual layer staving, connects supply conduit behind the staving, and hot road air is by connecing mouth and cold road air-blending on the supply conduit.The air of drawing from driving engine cools off by primary heat sink, secondary radiator, boost type turbine, the temperature that temperature sensor is experienced is passed to temp. controlling box with electric signal, temp. controlling box is after the temperature and temperature selector chosen temperature that the C.T sensor is experienced, the aperture of control hot passage valve is regulated the flow of hot road air, reaches chosen temperature after hot and cold road is mixed.The boost type low pressure de-watering apparatus of this kind structure, the flow on cold road is uncontrollable, therefore, make aircraft when high-altitude flight, the ability of heating of aircraft environmental control system can not be guaranteed, and, hot road air directly feeds on the conduit of turbine outlet, easily make turbo driving unstable or easily icing, damage turbine, influence the normal operation of system at the turbine outlet place.
Summary of the invention: the purpose of this utility model provides a kind of ability of heating that improves the aircraft environmental control system, prevents that the boost type low pressure with anti-icing chamber that the turbine outlet place freezes from removing water ring control device.Technical solution of the present utility model is, system is by hot passage valve, primary heat sink, secondary radiator, the boost type turbine, temperature control box, temperature sensor, temperature selector, cool passage valve is formed, system's bleed is divided into cold, hot two-way, hot passage valve is connected on the brasnch conduct of hot road, cool passage valve is connected on the trunk line behind the branched pipe leading point, hot road, the cool passage valve delivery channel is connected with the primary heat sink import, the primary heat sink outlet is connected with the air compressor end of boost type turbine, blower outlet is connected with the inlet of secondary radiator, the outlet of secondary radiator is connected with the turbine end of boost type turbine, the hot passage valve delivery channel is connected with the exit end of boost type turbine, temperature sensor is connected cold, on the mixed supply conduit in hot road, temperature control box and hot passage valve, cool passage valve, temperature sensor, temperature selector passes through cable connection.
The turbine outlet end of boost type turbine is made up of staving and outer cover, and staving places outer cover, and is sealed at both ends, and the middle cavity that forms is evenly distributed with inclined hole on the staving, have one to connect mouth on the outer cover.
The utility model has increased a valve in cold road, by certain temperature control law, when the system warm-up scarce capacity, close the cold road of mini system flow, makes hot road flow strengthen the ability thereby strengthening system is heated simultaneously.Adopt the structure that cavity is set at turbine outlet with the boost type turbine of formation simultaneously, prevent that turbine outlet from freezing, and improves the stability and the reliability of system works with anti-icing chamber.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
Fig. 2 is the turbine structure scheme drawing in the anti-icing chamber of the utility model band.
The specific embodiment:
System is by hot passage valve 3, primary heat sink 7, secondary radiator 9, boost type turbine 8, temperature control box 12, temperature sensor 10, temperature selector 13, cool passage valve 5 is formed, system's bleed trunk line 1 is cold in branch point 2 punishment, hot two-way, hot passage valve 3 is connected on the hot road brasnch conduct 4, cool passage valve 5 is connected on the cold road conduit 6, cool passage valve 5 delivery channels 6 are connected with primary heat sink 7 imports, primary heat sink 7 outlets are connected with the air compressor end of boost type turbine 8, blower outlet is connected with the inlet of secondary radiator 9, the outlet of secondary radiator 9 is connected with the turbine end of boost type turbine 8, hot passage valve 3 delivery channels 4 are connected with the exit end of boost type turbine 8, temperature sensor 10 is connected cold, on the mixed supply conduit 11 in hot road, temperature control box 12 and hot passage valve 3, cool passage valve 5, temperature sensor 10, temperature selector 13 connects by cable 14.
The turbine outlet end of boost type turbine 8 is made up of staving 15 and outer cover 19, and staving 15 places outer cover 19, and is sealed at both ends, and the middle cavity 16 that forms is evenly distributed with inclined hole 18 on the staving 15, have one to connect mouth 17 on the outer cover 16.
The air of drawing from driving engine is divided into cold and hot two-way, cold road air at first passes through cool passage valve 5, after primary heat sink 7 heat radiation, the air compressor end supercharging that enters boost type turbine 8, the turbine end that enters boost type turbine 8 after dispel the heat once more by secondary radiator 9 expands and lowers the temperature.Hot road air supplies toward passenger cabin behind the cold and hot air-blending through entering the anti-icing chamber of boost type turbine 8 behind the hot passage valve 3.
Feed air temperature is regulated by the aperture of temperature control box 12 control hot passage valves 3 and cool passage valve 5.When temperature selector 13 chosen temperature are higher than the temperature that temperature sensor 10 experiences, temperature control box 12 at first strengthens the aperture of hot passage valve 3, when hot passage valve 3 standard-sized sheets, it can send an endpoint signal and give temperature control box 12, and expression hot passage valve 3 has reached maximum.If feed air temperature did not also reach the set point value of temperature selector 13 when temperature control box 12 was received this signal, temperature control box 12 begins to turn down the aperture of cool passage valve 5, makes the feed air temperature of system continue to rise, and reaches the purpose that improves the system warm-up ability.
The turbine outlet end of boost type turbine forms a cavity by staving and outer cover, when hot air enters in the cavity by the mouth that connects on the outer cover, in the anti-icing chamber of turbine end interruption-forming, when making hot air pass through cavity between turbine staving and outer cover, heat turbine outlet and impeller equably, prevent that the gap generation between the icing obstruction of turbine outlet or turbine blade-tip and the housing is icing stuck, and avoid the direct impulse turbine blade of hot air to cause the turbo driving instability, improve the stability and the reliability of system works.
Claims (2)
1. the boost type low pressure with anti-icing chamber is removed water ring control device, it is characterized in that, system is by hot passage valve, primary heat sink, secondary radiator, the boost type turbine, temperature control box, temperature sensor, temperature selector, cool passage valve is formed, hot passage valve is connected on the brasnch conduct of hot road, cool passage valve is connected on the trunk line behind the branched pipe leading point, hot road, the cool passage valve delivery channel is connected with the primary heat sink import, the primary heat sink outlet is connected with the air compressor end of boost type turbine, blower outlet is connected with the inlet of secondary radiator, the outlet of secondary radiator is connected with the turbine end of boost type turbine, the hot passage valve delivery channel is connected with the exit end of boost type turbine, temperature sensor is connected cold, on the mixed supply conduit in hot road, temperature control box and hot passage valve, cool passage valve, temperature sensor, temperature selector passes through cable connection.
2. the boost type low pressure with anti-icing chamber according to claim 1 is removed water ring control device, it is characterized in that the turbine outlet end of boost type turbine is made up of staving and outer cover, staving places outer cover, and is sealed at both ends, the middle cavity that forms, be evenly distributed with inclined hole on the staving, have one to connect mouth on the outer cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2006201181397U CN2913183Y (en) | 2006-06-02 | 2006-06-02 | Booster low-pressure water-removing environment-control device with anti-icing cavity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2006201181397U CN2913183Y (en) | 2006-06-02 | 2006-06-02 | Booster low-pressure water-removing environment-control device with anti-icing cavity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2913183Y true CN2913183Y (en) | 2007-06-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2006201181397U Expired - Fee Related CN2913183Y (en) | 2006-06-02 | 2006-06-02 | Booster low-pressure water-removing environment-control device with anti-icing cavity |
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| CN (1) | CN2913183Y (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101952171A (en) * | 2007-12-28 | 2011-01-19 | 空中巴士运作简易股份有限公司 | Aircraft propulsion assembly comprising hot air bleed systems |
| CN102348600A (en) * | 2009-03-27 | 2012-02-08 | 空中客车运营简化股份公司 | Aircraft nacelle comprising a reinforced outer wall |
| CN108058832A (en) * | 2017-11-03 | 2018-05-22 | 中航通飞研究院有限公司 | A kind of combined type anti-freeze fluid-anti-deicing system of air bag |
| CN110388752A (en) * | 2019-07-09 | 2019-10-29 | 广东万家乐燃气具有限公司 | Strong pumping type gas heater distributor and burner |
| CN112407296A (en) * | 2020-10-30 | 2021-02-26 | 新乡航空工业(集团)有限公司 | Cold and hot medium mixed structure of aviation refrigeration turbine |
| CN113417891A (en) * | 2021-08-03 | 2021-09-21 | 中国航发湖南动力机械研究所 | Centrifugal compressor anti-icing air entraining structure and engine |
| CN114256487A (en) * | 2021-12-27 | 2022-03-29 | 上海重塑能源科技有限公司 | Anti-freezing fuel cell cold start system, fuel cell system and ice melting method |
-
2006
- 2006-06-02 CN CNU2006201181397U patent/CN2913183Y/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101952171A (en) * | 2007-12-28 | 2011-01-19 | 空中巴士运作简易股份有限公司 | Aircraft propulsion assembly comprising hot air bleed systems |
| CN101952171B (en) | 2007-12-28 | 2014-01-29 | 空中巴士运作简易股份有限公司 | Aircraft propulsion assembly comprising hot air bleed systems |
| CN102348600A (en) * | 2009-03-27 | 2012-02-08 | 空中客车运营简化股份公司 | Aircraft nacelle comprising a reinforced outer wall |
| CN108058832A (en) * | 2017-11-03 | 2018-05-22 | 中航通飞研究院有限公司 | A kind of combined type anti-freeze fluid-anti-deicing system of air bag |
| CN108058832B (en) * | 2017-11-03 | 2022-06-28 | 中航通飞研究院有限公司 | Combined type anti-icing liquid-air bag anti-icing and deicing system |
| CN110388752A (en) * | 2019-07-09 | 2019-10-29 | 广东万家乐燃气具有限公司 | Strong pumping type gas heater distributor and burner |
| CN112407296A (en) * | 2020-10-30 | 2021-02-26 | 新乡航空工业(集团)有限公司 | Cold and hot medium mixed structure of aviation refrigeration turbine |
| CN112407296B (en) * | 2020-10-30 | 2024-05-28 | 新乡航空工业(集团)有限公司 | Aviation refrigeration turbine cold and hot medium mixing structure |
| CN113417891A (en) * | 2021-08-03 | 2021-09-21 | 中国航发湖南动力机械研究所 | Centrifugal compressor anti-icing air entraining structure and engine |
| CN114256487A (en) * | 2021-12-27 | 2022-03-29 | 上海重塑能源科技有限公司 | Anti-freezing fuel cell cold start system, fuel cell system and ice melting method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Aviation Industry Limited by Share Ltd Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract fulfillment period: 2008.8.20 to 2013.8.19 Contract record no.: 2008360000056 Denomination of utility model: Booster low-pressure de-watering ring-control apparatus with ice proof cavity Granted publication date: 20070620 License type: Exclusive license Record date: 20081110 |
|
| LIC | Patent licence contract for exploitation submitted for record |
Free format text: EXCLUSIVE LICENSE; TIME LIMIT OF IMPLEMENTING CONTACT: 2008.8.20 TO 2013.8.19; CHANGE OF CONTRACT Name of requester: JIANGXI HONGDOU SPACE INDUSTRIAL STOCK CO., LTD. Effective date: 20081110 |
|
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20070620 Termination date: 20130602 |