CN106762147A - A kind of engine anti-icing system - Google Patents
A kind of engine anti-icing system Download PDFInfo
- Publication number
- CN106762147A CN106762147A CN201710095140.5A CN201710095140A CN106762147A CN 106762147 A CN106762147 A CN 106762147A CN 201710095140 A CN201710095140 A CN 201710095140A CN 106762147 A CN106762147 A CN 106762147A
- Authority
- CN
- China
- Prior art keywords
- chamber
- compartment
- rectification
- air inlet
- support plate
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
- Air-Conditioning For Vehicles (AREA)
Abstract
The invention discloses a kind of engine anti-icing system.The engine anti-icing system includes：Rectification support plate, rectification support plate includes the first chamber, the second chamber and the 3rd chamber, and first chamber, the second chamber and the 3rd chamber are disposed adjacent, and second chamber and the 3rd chamber of rectification support plate are provided with steam vent；Rectification calotte, rectification calotte is connected with the rectification support plate, demarcation strip is provided with the rectification calotte, rectification calotte is separated into the first compartment and the second compartment by the demarcation strip, first compartment and the second compartment are interconnected, first compartment is connected with the first chamber, and the second compartment is connected with the second chamber, the 3rd chamber respectively.Engine anti-icing system of the invention is carried out anti-icing using pipe stream heat exchange mode, hot air temperature is high, flow is big, it is ensured that the coefficient of heat transfer and the whole chamber of rectification support plate first of rectification support plate support plate leading edge and the first chamber of rectification support plate side wall heat transfer effect from the top to the bottom.
Description
Technical field
The present invention relates to Engine Anti-Ice technical field, more particularly to a kind of engine anti-icing system.
Background technology
When flight at aircraft is in temperature less than zero degree and small Mach said conditions, due to there is super-cooling waterdrop, meeting in air
Engine intake rectification support plate and rectification calotte surface is set to freeze.Rectification support plate and calotte freeze and can change the gas of support plate and calotte
Dynamic profile, causes aeroperformance to decline, while support plate freezes can reduce the air inlet area of air-flow.Additionally, the product of support plate and calotte
Ice comes off may injure or damage engine core part, and the performance and flight stability to engine produce great shadow
Ring.Therefore need to carry out ice prevention structure design to engine intake rectification support plate and calotte.
In the prior art, the hot air anti-icing method that engine anti-icing system is used is mainly from engine compresses part draws heat
Gas enters anti-icing support plate back cavity, and a part of hot gas flows into ante-chamber, impingement heat transfer carried out to support plate ante-chamber and by different by support plate back cavity
The anti-icing hole discharge of shape；Another part hot gas flows into calotte after being heated to support plate back cavity, through calotte after being heated to calotte
Steam vent is discharged.
The anti-icing method has the following disadvantages：First, due to the particularity of rectification support plate inner-cavity structure, impact opening distance impact
Target surface farther out, and the size of impingement heat transfer coefficient be hit hole and impact target identity distance from influence it is larger, therefore punching cannot be ensured
Hit the heating effect that heat exchange is optimal；2nd, because the structure in anti-icing hole is abnormity, anti-icing hole surface integrality reduction is caused,
It is likely to result in potential safety hazard；3rd, because most of hot gas is discharged through support plate ante-chamber, only the hot gas of fraction flows into calotte,
And it is relatively low into the hot air temperature of calotte, the anti-icing ability of calotte will certainly be caused not good enough.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
Overcome it is an object of the invention to provide a kind of engine anti-icing system or at least mitigate prior art at least
One drawbacks described above.
To achieve the above object, the invention provides a kind of engine anti-icing system, the engine anti-icing system includes：
Rectification support plate, the rectification support plate includes the first chamber, the second chamber and the 3rd chamber, first chamber, the second chamber and the 3rd chamber
It is disposed adjacent, the lumen and back cavity of the rectification support plate are provided with steam vent；Rectification calotte, the demarcation strip is by the rectification
Calotte is separated into the first compartment and the second compartment, and first compartment is interconnected with second compartment, institute
State the first compartment to be connected with first chamber, second compartment is connected with second chamber, the 3rd chamber respectively；Wherein,
First chamber includes air inlet and gas outlet, and second chamber includes that air inlet, the 3rd chamber include air inlet, described
First compartment includes that air inlet and gas outlet, second compartment include air inlet and gas outlet；First chamber
Air inlet be used for enter hot gas；The air inlet of first compartment is used to make to enter simultaneously from the air inlet in first chamber
The hot gas flowed out from the gas outlet in first chamber enters；The air inlet of second compartment is used to make to separate from described first
The air inlet in chamber enters and enters from the gas outlet outflow hot gas of first compartment；The air inlet in second chamber is used to make
The hot gas for entering from the air inlet of second compartment and being flowed out from the gas outlet of second compartment enters；Described 3rd
The air inlet in chamber is used to make what is entered from the air inlet of second compartment and flowed out from the gas outlet of second compartment
Hot gas enters.
Preferably, the engine anti-icing system further includes anti-icing air entraining pipe.
Preferably, it is provided with temperature sensor in first chamber.
Preferably, it is provided with temperature sensor in first compartment.
Preferably, first chamber shares a cavity wall with second chamber, and second chamber shares with the 3rd chamber
One cavity wall.
Preferably, it is provided with spoiler in second chamber.
Preferably, it is provided with spoiler in the 3rd chamber.
Engine anti-icing system of the invention is carried out anti-icing using pipe stream heat exchange mode, and hot air temperature is high, flow is big, it is ensured that
The coefficient of heat transfer and the whole chamber of rectification support plate first of rectification support plate support plate leading edge and the first chamber of rectification support plate side wall from top to
The heat transfer effect of bottom；Present invention eliminates the special-shaped steam vent of rectification support plate blade, it is ensured that the intensity of support plate blade；The present invention
Calotte hot gas flow is big, hot air temperature is high, it is ensured that the heat transfer effect of calotte.
Brief description of the drawings
Fig. 1 is the structural representation of engine anti-icing system according to an embodiment of the invention.
Reference：
| 1 | Rectification support plate | 3 | Rectification calotte |
| 11 | First chamber | 31 | Demarcation strip |
| 12 | Second chamber | 32 | First compartment |
| 13 | 3rd chamber | 33 | Second compartment |
| 2 | Steam vent |
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Face is described in detail with reference to accompanying drawing to embodiments of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
Fig. 1 is the structural representation of engine anti-icing system according to an embodiment of the invention.
Engine anti-icing system as shown in Figure 1 includes rectification support plate 1 and rectification calotte 3, and rectification support plate 1 includes first
Chamber 11, the second chamber 12 and the 3rd chamber 13, the first chamber 11, the second chamber 12 and the 3rd chamber 13 are disposed adjacent, and the of rectification support plate 1
Two chambers 12 and the 3rd chamber 13 are provided with steam vent 2；It is provided with demarcation strip in rectification calotte, demarcation strip 31 is by 3 points of rectification calotte
The first compartment 32 and the second compartment 33 are divided into, the first compartment 32 and the second compartment 33 are interconnected, and first separates
Chamber 32 is connected with the first chamber 11, and the second compartment 33 is connected with the second chamber 12, the 3rd chamber 13 respectively；Wherein, the first chamber 11 includes
Air inlet and gas outlet, the second chamber 12 include that air inlet, the 3rd chamber 13 include that air inlet, the first compartment 32 include air inlet
And gas outlet, the second compartment 33 include air inlet and gas outlet；The air inlet in the first chamber 11 is used to enter hot gas；The
The air inlet of one compartment 32 is used to make the hot gas for entering from the air inlet in the first chamber 11 and being flowed out from the gas outlet in the first chamber to enter
Enter；The air inlet of the second compartment is used to make to enter and flowed from the gas outlet of the first compartment 32 from the air inlet of the first compartment
Go out hot gas entrance；The air inlet in the second chamber 12 is used to make entering from the air inlet of the second compartment 33 and from the second compartment 33
The hot gas of gas outlet outflow enters, and the air inlet in the 3rd chamber 13 is used to make entering from the air inlet of the second compartment 33 and from second
The hot gas of the gas outlet outflow of compartment 33 enters.
Engine anti-icing system of the invention is carried out anti-icing using pipe stream heat exchange mode, and hot air temperature is high, flow is big, it is ensured that
The coefficient of heat transfer and the whole chamber of rectification support plate first of rectification support plate support plate leading edge and the first chamber of rectification support plate side wall from top to
The heat transfer effect of bottom；Present invention eliminates the special-shaped steam vent of rectification support plate blade, it is ensured that the intensity of support plate blade；The present invention
Calotte hot gas flow is big, hot air temperature is high, it is ensured that the heat transfer effect of calotte.
In the present embodiment, engine anti-icing system further includes anti-icing air entraining pipe.
Referring to Fig. 1, by taking Fig. 1 as an example, the hot gas stream of anti-icing system is：From the bleed of engine compresses part through anti-icing bleed
Pipe enters to rectification support plate ante-chamber, is flowed to gas outlet from the air inlet in the first chamber of rectification support plate, to the first of rectification support plate
Heated in chamber.Hot gas enters rectification support plate bottom after being flowed out by the first chamber of rectification support plate, then is flowed into by rectification support plate bottom
First compartment of rectification calotte, heats to rectification calotte.Hot gas is along the first compartment of rectification calotte to rectification calotte
Leading edge flows, and is flowed to the second compartment in rectification calotte edge hot gas.Hot gas flows back to rectification support plate through the second compartment, so
Hot gas is divided into two-way and respectively enters the second chamber and the 3rd chamber afterwards.Hot gas is along the bottom in the chamber of rectification support plate second and the 3rd chamber to rectification
The top flowing of support plate, heats to the chamber of support plate second and the 3rd chamber, and by the exhaust on second chamber and the 3rd chamber of rectification support plate
Discharge in hole.
The hot gas flow in the first chamber of rectification support plate of the present invention is big, the coefficient of heat transfer is high, it is ensured that the chamber of rectification support plate first
Overall good effect of heat exchange.Meanwhile, into rectification calotte flow is big, temperature is high, heat transfer effect can also be guaranteed.
Advantageously, in an alternative embodiment, it is provided with temperature sensor in the first chamber.So, can supervise in real time
The temperature surveyed in the first chamber.
Advantageously, in an alternative embodiment, it is provided with temperature sensor in the first compartment.So, Ke Yishi
When monitor temperature in the first compartment.
Referring to Fig. 1, in the present embodiment, the first chamber shares a cavity wall with second chamber, and the second chamber is total to the 3rd chamber
With a cavity wall.
In an alternative embodiment, it is provided with spoiler in the second chamber.Hot gas flow velocity can be reduced by spoiler, from
And heat is further transferred on the second chamber.
In an alternative embodiment, it is provided with spoiler in the 3rd chamber.Thermal current can be reduced by spoiler
Speed, so that heat is further transferred on the 3rd chamber.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, do not make the essence of the essence disengaging various embodiments of the present invention technical scheme of appropriate technical solution
God and scope.
Claims (7)
1. a kind of engine anti-icing system, it is characterised in that the engine anti-icing system includes：
Rectification support plate (1), the rectification support plate (1) includes the first chamber (11), the second chamber (12) and the 3rd chamber (13), described
One chamber (11), the second chamber (12) and the 3rd chamber (13) are disposed adjacent, second chamber (12) and the 3rd of the rectification support plate (1)
Chamber (13) is provided with steam vent (2)；
Rectification calotte (3), the rectification calotte is connected with the rectification support plate, is provided with demarcation strip in the rectification calotte, institute
State demarcation strip (31) and the rectification calotte (3) is separated into the first compartment (32) and the second compartment (33), described first
Compartment (32) is interconnected with second compartment (33), and first compartment (32) is with first chamber (11) even
Logical, second compartment (33) connects with second chamber (12), the 3rd chamber (13) respectively；Wherein,
First chamber (11) includes air inlet and gas outlet, and second chamber (12) includes air inlet, the 3rd chamber
(13) include including air inlet and gas outlet, second compartment (33) including air inlet, first compartment (32)
Air inlet and gas outlet；
The air inlet of first chamber (11) is used to enter hot gas；
The air inlet of first compartment (32) is used to make entering from the air inlet of first chamber (11) and from described first
The hot gas of the gas outlet outflow in chamber enters；
The air inlet of second compartment is used to make to enter and separate from described first from the air inlet of first compartment
The gas outlet outflow hot gas in chamber (32) enters；
The air inlet of second chamber (12) is used to make entering from the air inlet of second compartment (33) and from described second
The hot gas of the gas outlet outflow of compartment (33) enters；
The air inlet of the 3rd chamber (13) is used to make entering from the air inlet of second compartment (33) and from described second
The hot gas of the gas outlet outflow of compartment (33) enters.
2. engine anti-icing system as claimed in claim 1, it is characterised in that the engine anti-icing system is further included
Anti-icing air entraining pipe.
3. engine anti-icing system as claimed in claim 2, it is characterised in that be provided with TEMP in first chamber
Device.
4. engine anti-icing system as claimed in claim 2, it is characterised in that temperature biography is provided with first compartment
Sensor.
5. engine anti-icing system as claimed in claim 1, it is characterised in that first chamber and second chamber share
Individual cavity wall, second chamber shares a cavity wall with the 3rd chamber.
6. engine anti-icing system as claimed in claim 5, it is characterised in that be provided with spoiler in second chamber.
7. engine anti-icing system as claimed in claim 5, it is characterised in that be provided with spoiler in the 3rd chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710095140.5A CN106762147B (en) | 2017-02-22 | 2017-02-22 | A kind of engine anti-icing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710095140.5A CN106762147B (en) | 2017-02-22 | 2017-02-22 | A kind of engine anti-icing system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106762147A true CN106762147A (en) | 2017-05-31 |
| CN106762147B CN106762147B (en) | 2019-04-23 |
Family
ID=58958792
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710095140.5A Active CN106762147B (en) | 2017-02-22 | 2017-02-22 | A kind of engine anti-icing system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106762147B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108104886A (en) * | 2017-11-28 | 2018-06-01 | 中国航发沈阳发动机研究所 | A kind of anti-icing rectification support plate and with its engine pack |
| CN109630273A (en) * | 2018-11-23 | 2019-04-16 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine rectification calotte based on Magnus effect |
| CN110318882A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of calotte leading edge inner passage ice prevention structure with pentalpha impact opening |
| CN111577463A (en) * | 2020-05-25 | 2020-08-25 | 中国航发沈阳发动机研究所 | Engine air inlet casing structure |
| CN112343717A (en) * | 2020-11-05 | 2021-02-09 | 中国航发沈阳发动机研究所 | Inner ring front section and aeroengine air inlet casing bearing frame |
| CN112556728A (en) * | 2019-09-25 | 2021-03-26 | 中国航发商用航空发动机有限责任公司 | Anti-icing sensor and have its engine |
| CN112983649A (en) * | 2019-12-17 | 2021-06-18 | 中国航发商用航空发动机有限责任公司 | Aeroengine rotating cap cover anti-icing system and aeroengine |
| CN114151149A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Gas turbine engine fuel oil heat management and anti-icing integrated control system |
| CN114893299A (en) * | 2022-05-17 | 2022-08-12 | 中国航发沈阳发动机研究所 | Anti-icing structure of composite material inlet part of aircraft engine |
| CN114922734A (en) * | 2022-06-10 | 2022-08-19 | 南京航空航天大学 | Uniform temperature nature rectification extension board steam anti-icing structure based on rib post subregion vortex |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB637598A (en) * | 1947-08-27 | 1950-05-24 | Nelson Hector Kent | Improvements relating to gas turbine power plant installations |
| GB702546A (en) * | 1951-04-18 | 1954-01-20 | Bristol Aeroplane Co Ltd | Improvements in or relating to gas turbine engines |
| GB741336A (en) * | 1953-07-03 | 1955-11-30 | Armstrong Siddeley Motors Ltd | Anti-icing means for a gas turbine engine of an aircraft |
| GB1012909A (en) * | 1962-12-07 | 1965-12-08 | Gen Electric | Improvements in anti-icing means for the compressor of a gas turbine engine |
| GB2152150A (en) * | 1983-12-27 | 1985-07-31 | Gen Electric | Anti-icing inlet guide vane |
| CN105927389A (en) * | 2016-04-20 | 2016-09-07 | 上海交通大学 | Anti-icing system and method for aero-engine intake support plate |
-
2017
- 2017-02-22 CN CN201710095140.5A patent/CN106762147B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB637598A (en) * | 1947-08-27 | 1950-05-24 | Nelson Hector Kent | Improvements relating to gas turbine power plant installations |
| GB702546A (en) * | 1951-04-18 | 1954-01-20 | Bristol Aeroplane Co Ltd | Improvements in or relating to gas turbine engines |
| GB741336A (en) * | 1953-07-03 | 1955-11-30 | Armstrong Siddeley Motors Ltd | Anti-icing means for a gas turbine engine of an aircraft |
| GB1012909A (en) * | 1962-12-07 | 1965-12-08 | Gen Electric | Improvements in anti-icing means for the compressor of a gas turbine engine |
| GB2152150A (en) * | 1983-12-27 | 1985-07-31 | Gen Electric | Anti-icing inlet guide vane |
| CN105927389A (en) * | 2016-04-20 | 2016-09-07 | 上海交通大学 | Anti-icing system and method for aero-engine intake support plate |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108104886A (en) * | 2017-11-28 | 2018-06-01 | 中国航发沈阳发动机研究所 | A kind of anti-icing rectification support plate and with its engine pack |
| CN109630273A (en) * | 2018-11-23 | 2019-04-16 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine rectification calotte based on Magnus effect |
| CN110318882B (en) * | 2019-07-10 | 2021-09-07 | 西北工业大学 | Cap cover front edge internal channel anti-icing structure with pentagram-shaped impact holes |
| CN110318882A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of calotte leading edge inner passage ice prevention structure with pentalpha impact opening |
| CN112556728B (en) * | 2019-09-25 | 2022-07-19 | 中国航发商用航空发动机有限责任公司 | Anti-icing sensor and have its engine |
| CN112556728A (en) * | 2019-09-25 | 2021-03-26 | 中国航发商用航空发动机有限责任公司 | Anti-icing sensor and have its engine |
| CN112983649A (en) * | 2019-12-17 | 2021-06-18 | 中国航发商用航空发动机有限责任公司 | Aeroengine rotating cap cover anti-icing system and aeroengine |
| CN111577463A (en) * | 2020-05-25 | 2020-08-25 | 中国航发沈阳发动机研究所 | Engine air inlet casing structure |
| CN111577463B (en) * | 2020-05-25 | 2021-08-17 | 中国航发沈阳发动机研究所 | Engine air inlet casing structure |
| CN112343717B (en) * | 2020-11-05 | 2022-03-04 | 中国航发沈阳发动机研究所 | Inner ring front section and aeroengine air inlet casing bearing frame |
| CN112343717A (en) * | 2020-11-05 | 2021-02-09 | 中国航发沈阳发动机研究所 | Inner ring front section and aeroengine air inlet casing bearing frame |
| CN114151149A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Gas turbine engine fuel oil heat management and anti-icing integrated control system |
| CN114893299A (en) * | 2022-05-17 | 2022-08-12 | 中国航发沈阳发动机研究所 | Anti-icing structure of composite material inlet part of aircraft engine |
| CN114893299B (en) * | 2022-05-17 | 2023-11-28 | 中国航发沈阳发动机研究所 | Anti-icing structure of composite material inlet part of aero-engine |
| CN114922734A (en) * | 2022-06-10 | 2022-08-19 | 南京航空航天大学 | Uniform temperature nature rectification extension board steam anti-icing structure based on rib post subregion vortex |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106762147B (en) | 2019-04-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106762147A (en) | A kind of engine anti-icing system | |
| CN101124448B (en) | Drying equipment for drying web | |
| US10870491B2 (en) | Eductor driven anti-ice system | |
| EP3539635B1 (en) | Non-horizontal water extractor | |
| CN208134635U (en) | A kind of anti-deicing system for medium-and-large-sized fixed-wing unmanned plane | |
| CN104802996B (en) | Dehumidification system in aviation device assembly and its assemble method | |
| CN202624640U (en) | Ice prevention cavity for air inlet channel | |
| CN105927389B (en) | The anti-icing system and anti-icing method of aero-engine air intake duct support plate | |
| CN108090246A (en) | A kind of anti-ice components Calculation Method of Temperature Field | |
| CN104833444A (en) | Total air temperature sensor | |
| CN105781790B (en) | A kind of curved two end number mixing exhaust systems of double S of segmentation reducing-pitch thread | |
| CN107061013B (en) | A kind of hot air anti-icing method for engine intake rotary rectifier calotte | |
| US10252807B2 (en) | Runback control | |
| CN208778104U (en) | Engine intake rectifies calotte | |
| CN105443246B (en) | A kind of engine inlets anti-icing system | |
| CN208778101U (en) | Hot air anti-icing engine intake adjustable vane | |
| CN106741967A (en) | A kind of controllable air circulation system of injection radiating | |
| CN104566873A (en) | Air conditioning system condensate recycling system | |
| CN208803910U (en) | Flow splitter air film anti-icing equipment | |
| CN209013603U (en) | Grain storage temperature control unit | |
| EP2805884B1 (en) | Improved galley cooling | |
| CN209726354U (en) | Air conditioner | |
| CN207568685U (en) | A kind of helicopter exhaust system | |
| CN208635446U (en) | A kind of drying system with heat recovery function | |
| CN209142399U (en) | A kind of helicopter air-conditioning system condenser assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |