CN205203396U - Aircraft engine nacelle steam anti -icing system - Google Patents
Aircraft engine nacelle steam anti -icing system Download PDFInfo
- Publication number
- CN205203396U CN205203396U CN201521033151.3U CN201521033151U CN205203396U CN 205203396 U CN205203396 U CN 205203396U CN 201521033151 U CN201521033151 U CN 201521033151U CN 205203396 U CN205203396 U CN 205203396U
- Authority
- CN
- China
- Prior art keywords
- icing
- temperature sensor
- leading edge
- engine
- temperature
- 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.)
- Active
Links
Abstract
The utility model discloses an aircraft engine nacelle steam anti -icing system relates to the anti -icing technical field of aircraft nacelle steam. Aircraft engine nacelle steam anti -icing system contains anti -icing valve (1), anti -icing controlling means (2) and temperature sensor (3), the leading edge at engine inlets is arranged in temperature sensor (3) to with temperature signal transmission to anti -icing controlling means (2) of engine inlets leading edge, anti -icing controlling means (2) are passed through the aperture of the temperature signal anti -icing valve of control (1) of temperature sensor (3) feedback. The utility model has the advantages of: temperature sensor passes through the aperture of the anti -icing valve of temperature signal control of temperature sensor feedback with temperature signal transmission to the anti -icing controlling means of engine inlets leading edge, anti -icing controlling means, has practiced thrift anti -icing bleed flow, has practiced thrift the energy of engine.
Description
Technical field
The utility model relates to nacelle of airplane hot air anti-icing technical field, is specifically related to a kind of aero-engine nacelle hot gas anti-icing system.
Background technology
The engine nacelle of current transport class adopts hot gas anti-icing system mostly, and its groundwork is the icing warning information provided according to aircraft icing detection system, and by aviator, nacelle anti icing system opened automatically by manual or aircraft.After nacelle anti icing system is opened, all the time with a metastable hot air flowrate heating nacelle leading edge, keep leading edge temperature higher than the anti-ice temperature of dry state to reach anti-icing object.
Because traditional nacelle hot gas anti-icing system is in order to reach the anti-icing effect of the complete non-icing dry state of leading edge, need very large energy, and anti-icing bleed flow is unadjustable, can only according to the demand supplies hot air maximum in whole flight envelope of aircraft.Therefore in hot gas anti-icing system use procedure, under causing most of icing condition, the actual anti-icing bleed flow provided is much larger than the anti-icing bleed flow of demand, cause aero-engine bleed excessively to use, waste the bleed energy of aircraft, reduce the engine thrust of aircraft.In addition, the use of traditional nacelle hot gas anti-icing system is the icing information provided according to icing detection system opportunity.Icing detection system is generally arranged on head both sides, therefore also directly cannot reflect the truth that nacelle leading edge is frozen.
Utility model content
The purpose of this utility model is to provide a kind of aero-engine nacelle hot gas anti-icing system, to solve or at least to alleviate the problem at least one place existing in existing background technology.
The technical solution of the utility model is: provide a kind of aero-engine nacelle hot gas anti-icing system, comprise anti-icing valve, anti-icing control device and temperature sensor, described temperature sensor is arranged in the leading edge of engine inlets, and the temperature signal of engine inlets leading edge is transferred to anti-icing control device, anti-icing control device controls the aperture of anti-icing valve.
Preferably, described temperature sensor is binary channel temperature sensor.
Preferably, described temperature sensor is provided with multiple in the leading edge of engine inlets according to ice forming locations, and multiple temperature sensor works alone.
Preferably, described anti-icing control device is provided with the anti-icing temperature range of dry state, after aircraft enters icing area, after the icing detector of aircraft detects and freezes, information transmission of freezing is to anti-icing control device, nacelle anti icing system is opened, anti-icing valve predetermined aperture with setting charge air heated engine inlet channel leading edge;
If the temperature of the engine inlets leading edge of temperature sensor feedback is higher than the upper limit of the anti-icing temperature range of dry state, anti-icing control device sends signal, reduces the aperture of anti-icing valve, to reduce anti-icing hot gas flow;
If the temperature of the engine inlets leading edge of temperature sensor feedback is lower than the lower limit of the anti-icing temperature range of dry state, anti-icing control device sends signal, increases the aperture of anti-icing valve, to increase anti-icing hot gas flow.
Preferably, the charge air of described predetermined aperture and setting refers to, anti-icing valve is when predetermined aperture is with the charge air heated engine inlet channel leading edge of setting, and the temperature of engine inlets leading edge should within the anti-icing temperature range of dry state arranged.
The utility model has the advantage of: aero-engine nacelle hot gas anti-icing system of the present utility model is provided with temperature sensor in the leading edge of engine inlets, the temperature signal of engine inlets leading edge is transferred to anti-icing control device by temperature sensor, anti-icing control device controls the aperture of anti-icing valve by the temperature signal of temperature sensor feedback, save anti-icing bleed flow, save the energy of driving engine.
Temperature sensor is set to dual channel sensor, improves systems axiol-ogy safety factor.
Temperature sensor is provided with multiple in the leading edge of engine inlets according to ice forming locations, and multiple temperature sensor works alone.Detection Information is more comprehensive, anti-icing effective.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of aero-engine nacelle hot gas anti-icing system one embodiment of the present utility model.
Wherein: the anti-icing valve of 1-, 2-anti-icing control device, 3-temperature sensor.
Detailed description of the invention
The object implemented for making the utility model, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technical scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
As shown in Figure 1, a kind of aero-engine nacelle hot gas anti-icing system, comprise anti-icing valve 1 and anti-icing control device 2 and temperature sensor 3, temperature sensor 3 is arranged in the leading edge of engine inlets, and the temperature signal of engine inlets leading edge is transferred to anti-icing control device 2, anti-icing control device 2 controls the aperture of anti-icing valve 1 by the temperature signal that temperature sensor 3 feeds back.Save anti-icing bleed flow, save the energy of driving engine.
In the present embodiment, temperature sensor 3 is binary channel temperature sensor.One of them is as main channel, and another is as alternate channel, and after breaking down in main channel, alternate channel can complete temperature detection equally, improves systems axiol-ogy safety factor.
In the present embodiment, the temperature-measuring element in temperature sensor adopts thermocouple, and its advantage is, thermocouple measuring temperature scope is comparatively wide, and anti shock and vibration is good, is more suitable for dangerous rugged environment.Response is fast, because their volume is little, heat absorption capacity is low, and thermocouple is fast to temperature traverse response, especially when induced junction chalaza is exposed, can make response in hundreds of millisecond to temperature traverse.Because thermocouple does not need excitation power supply, therefore not easily spontaneous heating, uses safer.
Be understandable that, temperature sensor 3 can be provided with multiple in the leading edge of engine inlets according to ice forming locations, and multiple temperature sensor 3 works alone.Be understandable that, the layout density of temperature sensor can be increased in the region that icing area is comparatively serious, to improve accuracy of detection and to add survey safety factor.
Anti-icing control device 2 is provided with the anti-icing temperature range of dry state, after aircraft enters icing area, after the icing detector of aircraft detects and freezes, information transmission of freezing is to anti-icing control device 2, nacelle anti icing system is opened, anti-icing valve 1 predetermined aperture with setting charge air heated engine inlet channel leading edge.
If the temperature of the engine inlets leading edge that temperature sensor 3 feeds back is higher than the upper limit of the anti-icing temperature range of dry state, anti-icing control device 2 sends signal, reduces the aperture of anti-icing valve 1, to reduce anti-icing hot gas flow, reduces the loss of the driving engine energy.
If the temperature of the engine inlets leading edge that temperature sensor 3 feeds back is lower than the lower limit of the anti-icing temperature range of dry state, anti-icing control device 2 sends signal, increases the aperture of anti-icing valve 1, to increase anti-icing hot gas flow, ensures the normal operation of driving engine.
The charge air of described predetermined aperture and setting refers to, anti-icing valve 1 is when predetermined aperture is with the charge air heated engine inlet channel leading edge of setting, and the temperature of engine inlets leading edge should within the anti-icing temperature range of dry state arranged.
The reason that the utility model saves energy is: traditional nacelle hot gas anti-icing system is according to bleed flow design maximum in whole flight envelope, therefore under a lot of anti-icing state, the actual anti-icing bleed flow provided, much larger than the anti-icing bleed flow of demand, causes airplane air entraining energy dissipation.Feature of the present utility model is the surface temperature by Real-time Obtaining nacelle leading edge, according to the surface temperature information detected, regulate anti-icing valve opening, the surface temperature of nacelle leading edge is made to maintain the anti-icing temperature range of dry state of setting all the time, anti-icing performance can be ensured, again can under most of ice-formation condition, make actually to be less than design discharge with gas supply flow, save the energy of aircraft.
Principle of work of the present utility model is: the nacelle leading edge surface temperature information utilizing surface temperature sensor to provide, regulate anti-icing valve opening to control gas supply flow, the surface temperature of nacelle leading edge is made to maintain the anti-icing temperature range of dry state of setting all the time, to reduce energy resource consumption, improve anti-icing effect.Under icing meteorology condition, connect nacelle hot gas anti-icing system, nacelle leading edge surface temperature measured in real time by the surface temperature sensor 2 being arranged on nacelle leading edge, and surface temperature information is passed to anti-icing control device 3, the aperture controlling anti-icing valve 2 regulates gas supply flow, makes the surface temperature of nacelle leading edge maintain the anti-icing interval of dry state temperature of setting all the time.When surface temperature is lower than the lower limit of the anti-icing temperature range of dry state, the aperture increasing anti-icing valve 1, to increase anti-ice discharge, makes nacelle leading edge surface temperature reach the anti-ice temperature of dry state.When nacelle leading edge temperature is higher than the upper limit of the anti-icing temperature range of dry state, the aperture reducing anti-icing valve 1, to reduce anti-ice discharge, makes nacelle leading edge surface temperature be down to the anti-icing temperature range of setting dry state.
Finally it is to be noted: above embodiment only in order to the technical solution of the utility model to be described, is not intended to limit.Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment technical scheme of the utility model.
Claims (5)
1. an aero-engine nacelle hot gas anti-icing system, comprise anti-icing valve (1) and anti-icing control device (2), it is characterized in that: also comprise temperature sensor (3), described temperature sensor (3) is arranged in the leading edge of engine inlets, and the temperature signal of engine inlets leading edge is transferred to anti-icing control device (2), anti-icing control device (2) controls the aperture of anti-icing valve (1) by the temperature signal that described temperature sensor (3) feeds back.
2. aero-engine nacelle hot gas anti-icing system as claimed in claim 1, is characterized in that: described temperature sensor (3) is binary channel temperature sensor.
3. aero-engine nacelle hot gas anti-icing system as claimed in claim 1, it is characterized in that: described temperature sensor (3) is provided with multiple in the leading edge of engine inlets according to ice forming locations, and multiple temperature sensor (3) works alone.
4. aero-engine nacelle hot gas anti-icing system as claimed in claim 1, it is characterized in that: described anti-icing control device (2) is provided with the anti-icing temperature range of dry state, after aircraft enters icing area, after the icing detector of aircraft detects and freezes, information transmission of freezing is to anti-icing control device (2), nacelle anti icing system is opened, anti-icing valve (1) predetermined aperture with setting charge air heated engine inlet channel leading edge;
If the temperature of the engine inlets leading edge that temperature sensor (3) feeds back is higher than the upper limit of the anti-icing temperature range of dry state, anti-icing control device (2) sends signal, reduce the aperture of anti-icing valve (1), to reduce anti-icing hot gas flow;
If the temperature of the engine inlets leading edge that temperature sensor (3) feeds back is lower than the lower limit of the anti-icing temperature range of dry state, anti-icing control device (2) sends signal, increase the aperture of anti-icing valve (1), to increase anti-icing hot gas flow.
5. aero-engine nacelle hot gas anti-icing system as claimed in claim 4, it is characterized in that: the charge air of described predetermined aperture and setting refers to, anti-icing valve (1) is when predetermined aperture is with the charge air heated engine inlet channel leading edge of setting, and the temperature of engine inlets leading edge should within the anti-icing temperature range of dry state arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521033151.3U CN205203396U (en) | 2015-12-11 | 2015-12-11 | Aircraft engine nacelle steam anti -icing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521033151.3U CN205203396U (en) | 2015-12-11 | 2015-12-11 | Aircraft engine nacelle steam anti -icing system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205203396U true CN205203396U (en) | 2016-05-04 |
Family
ID=55841128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521033151.3U Active CN205203396U (en) | 2015-12-11 | 2015-12-11 | Aircraft engine nacelle steam anti -icing system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205203396U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184768A (en) * | 2016-07-22 | 2016-12-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of adaptive wing steam deicing system |
| CN107560822A (en) * | 2017-10-31 | 2018-01-09 | 中国商用飞机有限责任公司 | The anti-icing icing mnncl tcst equipment of engine inlets leading edge and its test method |
| CN107764574A (en) * | 2017-09-08 | 2018-03-06 | 中国飞行试验研究院 | A kind of anti-icing functional verification flight test method of pusher airscrew |
| CN108035829A (en) * | 2017-11-08 | 2018-05-15 | 中国航发北京航科发动机控制系统科技有限责任公司 | A kind of airliner engine fuel control unit |
| CN109583034A (en) * | 2018-11-02 | 2019-04-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of method for numerical simulation of aircraft hot air anti-icing part temperatures field |
| CN114394241A (en) * | 2021-12-15 | 2022-04-26 | 中航(成都)无人机系统股份有限公司 | Aircraft environmental control system |
| CN114771871A (en) * | 2022-06-14 | 2022-07-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for debugging icing sensor of air inlet channel, sensor and control system |
-
2015
- 2015-12-11 CN CN201521033151.3U patent/CN205203396U/en active Active
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184768A (en) * | 2016-07-22 | 2016-12-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of adaptive wing steam deicing system |
| CN107764574A (en) * | 2017-09-08 | 2018-03-06 | 中国飞行试验研究院 | A kind of anti-icing functional verification flight test method of pusher airscrew |
| CN107764574B (en) * | 2017-09-08 | 2021-09-14 | 中国飞行试验研究院 | Test method for verifying anti-icing function of propulsion type aviation propeller during test flight |
| CN107560822A (en) * | 2017-10-31 | 2018-01-09 | 中国商用飞机有限责任公司 | The anti-icing icing mnncl tcst equipment of engine inlets leading edge and its test method |
| CN108035829A (en) * | 2017-11-08 | 2018-05-15 | 中国航发北京航科发动机控制系统科技有限责任公司 | A kind of airliner engine fuel control unit |
| CN108035829B (en) * | 2017-11-08 | 2021-08-06 | 中国航发北京航科发动机控制系统科技有限公司 | Fuel control device for large passenger plane engine |
| CN109583034A (en) * | 2018-11-02 | 2019-04-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of method for numerical simulation of aircraft hot air anti-icing part temperatures field |
| CN109583034B (en) * | 2018-11-02 | 2023-06-23 | 中国航空工业集团公司西安飞机设计研究所 | Numerical simulation method for temperature field of aircraft hot gas anti-icing component |
| CN114394241A (en) * | 2021-12-15 | 2022-04-26 | 中航(成都)无人机系统股份有限公司 | Aircraft environmental control system |
| CN114771871A (en) * | 2022-06-14 | 2022-07-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for debugging icing sensor of air inlet channel, sensor and control system |
| CN114771871B (en) * | 2022-06-14 | 2022-10-04 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for debugging icing sensor of air inlet channel, sensor and control system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205203396U (en) | Aircraft engine nacelle steam anti -icing system | |
| CN107745816B (en) | A kind of aircraft wing automatic deicer | |
| CN103448912B (en) | The aircraft anti-icing optimization of input is detected based on ice | |
| US7124983B2 (en) | Hybrid electrical ice protection system and method including an energy saving mode | |
| CN102431650B (en) | Aircraft wing ultrasonic assistant hot gas associating de-icing device | |
| US9656757B2 (en) | Propeller deicing system | |
| CN101695959B (en) | Ice preventing and removing device for helicopter rotors | |
| CN105691620B (en) | Utilize the ultrasonic combined anti-icing and de-icing device of the heat pipe of aircraft engine waste heat and method | |
| CN105416593A (en) | Aircraft deicing system | |
| CN202557799U (en) | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device | |
| EP3028944B1 (en) | Fuel tank of an aircraft and cooling system | |
| CN202863770U (en) | Aerofoil hot gas anti-icing system | |
| CN107543649B (en) | Hot air deicing total pressure sensor | |
| US11242152B2 (en) | Method and apparatus for detecting ice accretion | |
| CN109696290A (en) | A kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system | |
| CN105966626A (en) | Novel helicopter rotor wing hot-air expansion film and electricity and heat combination ice preventing/removing device | |
| CN105443246B (en) | A kind of engine inlets anti-icing system | |
| CN104787344A (en) | Automatic airplane surface heating device | |
| CN107745828A (en) | A kind of anti-deicing experiment air entraining device of hot gas | |
| CN110963044B (en) | Wing deicing device based on nanocomposite phase change material and working method thereof | |
| EP1873060B1 (en) | Hybrid electrical ice protection system and method including an energy saving mode | |
| CN106184768A (en) | A kind of adaptive wing steam deicing system | |
| CN204821482U (en) | Anti -icing defogging system of hybrid aircraft windscreen | |
| CN211711091U (en) | Automatic anti-icing and deicing device for fuel wing of aircraft | |
| CN110963045B (en) | Automatic deicing device for fuel wing of quoted aircraft and working method of automatic deicing device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |