CN105927389A - Anti-icing system and method for aero-engine intake support plate - Google Patents
Anti-icing system and method for aero-engine intake support plate Download PDFInfo
- Publication number
- CN105927389A CN105927389A CN201610248452.0A CN201610248452A CN105927389A CN 105927389 A CN105927389 A CN 105927389A CN 201610248452 A CN201610248452 A CN 201610248452A CN 105927389 A CN105927389 A CN 105927389A
- Authority
- CN
- China
- Prior art keywords
- support plate
- thermal medium
- cavity
- air intake
- intake duct
- 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)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention provides an anti-icing system for an aero-engine intake support plate. The anti-icing system comprises an isolating unit and a thermal medium conveying unit. The intake support plate is provided with a cavity. The cavity is provided with an inlet end and an outlet end. The isolating unit is fixed into the cavity and used for dividing the cavity into multiple channel cavity bodies communicating with one another. A thermal medium conveyed by the thermal medium conveying unit enters the channel cavity bodies through the inlet end and is discharged from the outlet end. The anti-icing system comprises the channel cavity bodies communicating with one another, on the one hand, the flowing time of the thermal medium in the cavity is prolonged, and accordingly the heat exchange effect of the thermal medium and the intake support plate is increased; and on the other hand, relative to the integrated cavity structure, the division type structure with the channel cavity bodies has the acceleration effect on the thermal medium, the temperature of the intake support plate can be increased through the thermal medium of which the flowing speed is increased, and the heat exchange effect is further improved.
Description
Technical field
The present invention relates to the anti-icing system of a kind of aero-engine, especially a kind of aero-engine air intake duct props up
The anti-icing system of plate and anti-icing method.
Background technology
Aircraft ice formation issues is the serious problems jeopardizing flight safety, and the aircraft accident relevant with icing is annual all
There is generation.Aero gas turbine engine is part most sensitive in aircraft icing parts, due to engine
High Rotation Speed, makes air intake duct air be in aspiration phases, and air-flow accelerates, and static temperature declines so that aeroplane engine
Machine gas handling system is affected more susceptible to icing weather, it is easier to freeze.Once engine aspirating system knot
Ice, can change the aerodynamic characteristics of gas handling system, increases flow resistance, makes inlet flow field skewness,
Flow distortion occurring time light, thus affects the job stability of engine, time serious, it may cause flame-out stopping
Car, causes lethal effect.If engine aspirating system freezes, anti-icing system is opened delayed, also can cause
Melt the ice cube come off to be sucked by engine, produce engine by the serious problems of Foreign Object Damage.According to the U.S.
NTSB NTSB adds up between 1998-2007, the aircraft accident caused due to icing
Reach 264, wherein cause major accident 94, dead 202 people.Russia is to aero-engine icing thing
Therefore investigation finds, aero-engine aerodynamic stability auto extinguishing not enough, aerial usually can be caused owing to freezing
Accident Deng serious threat flight safety.
The icing of aero-engine gas handling system and the research of anti-ice problem are related to aviation safety problem, therefore
In aviation developed country, its research is paid much attention to.Affect aero-engine air inlet component freeze and anti-icing because of
Element is a lot, and the duty and the flight environment of vehicle that are required for engine do concrete analysis and design.For boat
The icing of empty engine aspirating system and anti-icing performance, researcher has carried out substantial amounts of computational analysis and experiment
Research.More American-European aviation developed countries for affect the meteorological condition of aero-engine icing, flight parameter,
Modular construction parameter etc. there has been certain understanding, but is affected, such as cloud layer liquid by very many factors owing to freezing
Content (LWC), the temperature of super-cooling waterdrop, the size of super-cooling waterdrop, the flying speed of aircraft and the appearance of state water
State, engine charge modular construction form and the surface characteristic etc. of material, aero-engine gas handling system freezes
It is still an extremely complex problem with mechanism of anti-icing research.
In the last few years, the calculating that the domestic water impact characteristics at aircraft wing, ice increased, anti-icing load Analysis
Etc. aspect all make some progress, as carried out entirely for China's first feeder liner ARJ21
The computational analysis of machine three-dimensional water impact characteristics, and the accumulated ice computational analysis of critical component, carried out ice type pair
Aircraft aerodynamic performance affect wind tunnel experimental research etc..For comparing the ice formation issues research of aircraft wing, state
Icing/anti-icing the research work of inherent aircraft engine parts is the most fewer.
Aero-engine imported equipments and parts (such as air intake duct support plate) anti-icing employing hot gas anti-icing system, heat
Gas is to draw from compressor intergrade, and being imported by pipeline needs anti-icing components interior passage, heater block
Make component surface temperature be maintained on freezing point, thus anti-stagnant ice is in the gathering on imported equipments and parts surface.Hot gas is prevented
Ice system, owing to needing the bleed air from engine, can make the efficiency of engine decline.Additionally,
The cavity structure of available engine imported equipments and parts is relatively simple, and hot gas is merely capable of carrying out heat friendship with imported equipments and parts
Change, and heat exchanger effectiveness is the highest.Therefore, it is necessary to provide a kind of more preferable anti-icing system of heat transfer effect.
Summary of the invention
It is an object of the invention to provide the anti-icing system of a kind of aero-engine air intake duct support plate and anti-icing side
Method, the problem poor to solve existing anti-icing system heat transfer effect.
In order to achieve the above object, the invention provides the anti-icing system of a kind of aero-engine air intake duct support plate
System, including isolated location and thermal medium supply unit, described air intake duct support plate has cavity, and described cavity has
Arrival end and the port of export, described isolated location is had to be fixed in described cavity, for being divided into many by described cavity
The individual channel cavity being interconnected, the thermal medium of described thermal medium supply unit conveying enters through described arrival end
In described channel cavity, and discharge from the described port of export.
Further, at least one described channel cavity, be fixed with spoiler, described spoiler be fixed on into
On air flue support plate or be fixed on isolated location.
Further, the quantity of described spoiler is multiple, on described air intake duct support plate and isolated location respectively
It is fixed with described spoiler.
Further, the width of a described channel cavity of described air intake duct support plate edge it is positioned at less than it
The width of his described channel cavity.
Further, the described channel cavity being positioned at described air intake duct support plate edge is fixed with flow-disturbing
Sheet, described spoiler is fixed on air intake duct support plate or is fixed on isolated location, is positioned at described air intake duct and props up
One described channel cavity of plate edge is connected with described arrival end, is positioned at described air intake duct support plate trailing edge
A described channel cavity be connected with the described port of export.
Further, described isolated location uses partition plate structure.
Further, described thermal medium is hot gas or deep fat.
Further, described thermal medium is deep fat, and described thermal medium supply unit is used for carrying engine lubrication
The hot lubricating oil that system provides.
Further, described air intake duct support plate includes support plate body, entrance pipe, entrance transition, outlet
Guide section, outlet transition and outlet pipe, described support plate body has described cavity, described support plate body
Being connected with entrance pipe by entrance transition, described support plate body also passes sequentially through export orientation section, outlet
Transition is connected with outlet pipe, and thermal medium enters support plate originally through described entrance pipe and entrance transition successively
In the cavity of body, and successively through described export orientation section, outlet transition and outlet pipe discharge, described in go out
Mouth guide section is for changing the outflow direction of thermal medium.
Present invention also offers a kind of anti-icing method of aero-engine air intake duct support plate, apply and prevent described
In ice system, carrying thermal medium by described thermal medium supply unit, described thermal medium enters from described arrival end
Enter in described channel cavity, and discharge from the described port of export.
The invention provides the anti-icing system of a kind of aero-engine air intake duct support plate and anti-icing method, in aviation
When engine enters easy freezing environment or when aero-engine air intake duct support plate produces icing phenomenon, by high
Temperature medium pumps into support plate inner air, to improve air intake duct support plate hull-skin temperature, thus prevents support plate appearance
Face produces icing phenomenon or eliminates the icing phenomenon of air intake duct support plate outer surface.This anti-icing system includes multiple phase
Intercommunicated channel cavity, on the one hand, add thermal medium flowing time in the cavities, add accordingly
Thermal medium and the heat transfer effect of air intake duct support plate；On the other hand, relative to all-in-one-piece cavity structure, segmentation
The structure with multiple channel cavity of formula can have the effect of acceleration to thermal medium, the thermal medium that flow velocity strengthens
The temperature of air intake duct support plate can be improved, further increase heat transfer effect.
Accompanying drawing explanation
The stereogram of the air intake duct support plate that Fig. 1 provides for the embodiment of the present invention；
The sectional view of the air intake duct support plate that Fig. 2 provides for the embodiment of the present invention.
In figure, 1: entrance pipe, 2: entrance transition, 3: support plate body, 4: export orientation section, 5:
Outlet transition, 6: outlet pipe, 7: entrance pipe inner chamber, 8: entrance transition inner chamber, 9: the first
Internal channel, 10: spoiler, 11: the first dividing plates, 12: the second internal channels, 13: second partition, 14:
3rd internal channel, 15: export orientation section inner chamber, 16: outlet transition inner chamber, 17: outlet pipe inner chamber.
Detailed description of the invention
Below in conjunction with schematic diagram, the detailed description of the invention of the present invention is described in more detail.According to following
Description and claims, advantages and features of the invention will be apparent from.It should be noted that, accompanying drawing all uses
The form that simplifies very much and all use non-ratio accurately, only in order to convenient, aid in illustrating the present invention lucidly
The purpose of embodiment.
As shown in Fig. 1～2, present embodiments provide the anti-icing system of a kind of aero-engine air intake duct support plate,
Including isolated location and thermal medium supply unit (not shown), described air intake duct support plate has cavity, described sky
Chamber has arrival end and the port of export, and described isolated location is fixed in described cavity, for being divided by described cavity
For multiple channel cavity being interconnected, the thermal medium of described thermal medium supply unit conveying is through described arrival end
Enter in described channel cavity, and discharge from the described port of export.
This anti-icing system includes multiple channel cavity being interconnected, on the one hand, add thermal medium at cavity
In flowing time, add the heat transfer effect of thermal medium and air intake duct support plate accordingly；On the other hand, relatively
In all-in-one-piece cavity structure, the structure with multiple channel cavity of partition type can have acceleration to thermal medium
Effect, the thermal medium that flow velocity strengthens can improve the temperature of air intake duct support plate, further increase heat transfer effect.
Preferably, at least one described channel cavity, it is fixed with spoiler 10, for strengthening channel cavity
The perturbation of internal high temperature medium (alternatively referred to as thermal medium), thus further enhance high-temperature medium and passage
The heat transfer effect of cavity inner wall.Specifically, in like manner, spoiler 10 is set and can increase thermal medium in channel cavity
In time, improve heat transfer effect, it is possible to because shorten channel cavity at spoiler 10 width and then
Add the flow velocity of thermal medium, improve the temperature of air intake duct support plate accordingly.Described spoiler is fixed on air inlet
On road support plate or be fixed on isolated location.
In the present embodiment, the quantity of described spoiler 10 is multiple, described air intake duct support plate and isolated location
On be respectively fixed with described spoiler, but be not limited to this.
It is preferably located at the width of a described channel cavity of described air intake duct support plate edge less than other
The width of described channel cavity.Owing in a practical situation, air intake duct support plate leading edge is easier to freeze, therefore leans on
When nearby a channel cavity width of edge is less than other channel cavity, in this channel cavity of edge, heat is situated between
Faster, the temperature of edge air intake duct support plate is the highest, it is easier to anti-icing for the flow velocity of matter.
In the present embodiment, be positioned at a described channel cavity of described air intake duct support plate edge with described enter
Mouth end connects, and described spoiler 10 is arranged in a described channel cavity of described air intake duct support plate edge,
It is positioned at a described channel cavity at described air intake duct support plate trailing edge to be connected with the described port of export.
Isolated location can be various ways, and such as, described isolated location uses partition plate structure, but does not limits
In this.In the present embodiment, isolated location includes the first dividing plate 11 and second partition 13, and isolated location is by sky
Chamber is divided into three channel cavity, the respectively first internal channel the 9, second internal channel 12 and the 3rd internal channel 14,
First internal channel 9 is near leading edge, and is provided with spoiler in the first internal channel 9.
Described thermal medium is hot gas or deep fat.In the present embodiment, described thermal medium is deep fat, and described heat is situated between
Matter supply unit is for carrying the hot lubricating oil that engine lubrication system provides.Use engine lubrication system institute energy
The hot lubricating oil provided carries out heating anti-icing, both can reduce the engine anti-icing system demand to hot gas, and carry
The efficiency of high pressure mechanism of qi, can also play the effect of cooling lubricating oil simultaneously.
In the present embodiment, described air intake duct support plate includes support plate body 3, entrance pipe 1, entrance transition
2, export orientation section 4, outlet transition 5 and outlet pipe 6, described support plate body has described cavity,
Described support plate body 3 is connected with entrance pipe 1 by entrance transition 2, and described support plate body leads to the most successively
Cross export orientation section 4, outlet transition 5 is connected with outlet pipe 6, and thermal medium is successively through described entrance pipe
1 and entrance transition 2 enter in the cavity of support plate body 3, and successively through described export orientation section 4, outlet
Transition 5 and outlet pipe 6 are discharged, and described export orientation section 4 is for changing the outflow direction of thermal medium.
Wherein, entrance pipe 1 has entrance pipe inner chamber 7, and entrance transition 2 has entrance transition inner chamber
8, export orientation section 4 has export orientation section inner chamber 15, and outlet transition 5 has outlet transition inner chamber
16, outlet pipe 6 has outlet pipe inner chamber 17, entrance transition 2 and outlet transition 5 can be reduced
The resistance of high-temperature medium pump into and out air intake duct support plate, entrance pipe 1 and outlet pipe 6 are conducive to connecting
High-temperature resistant tube, to prevent high-temperature medium from producing leakage problem.
The present embodiment additionally provides a kind of anti-icing method of aero-engine air intake duct support plate, applies described
In anti-icing system, carrying thermal medium by described thermal medium supply unit, described thermal medium is from described arrival end
Enter in described channel cavity, and discharge from the described port of export.
Anti-icing system and anti-icing method that the present embodiment provides may be used for preventing freezing and can be used for removing knot
Ice.Specifically, in order to prevent aero-engine air intake duct support plate outer surface from producing icing phenomenon, send out in aviation
Motivation enter easy freezing environment time, by high-temperature medium is pumped into air intake duct support plate internal cavities, with improve into
Air flue support plate hull-skin temperature, thus prevent support plate outer surface from producing icing phenomenon.When aero-engine air inlet
Road support plate (in general, when aero-engine air inflow reduces, can determine that as air inlet when producing icing phenomenon
Road support plate produces icing phenomenon), logical by what high-temperature medium was pumped into that air intake duct props up that intralamellar part three is interconnected
Road cavity, can promptly improve the temperature of support plate outer surface, thus eliminate the knot of air intake duct support plate outer surface
Ice phenomenon, and then can prevent engine from producing the problem stopped in high-altitude because inspiratory capacity die-offs.
The invention provides the anti-icing system of a kind of aero-engine air intake duct support plate and anti-icing method, in aviation
When engine enters easy freezing environment or when aero-engine air intake duct support plate produces icing phenomenon, by high
Temperature medium pumps into support plate inner air, to improve air intake duct support plate hull-skin temperature, thus prevents support plate appearance
Face produces icing phenomenon or eliminates the icing phenomenon of air intake duct support plate outer surface.This anti-icing system includes multiple phase
Intercommunicated channel cavity, on the one hand, add thermal medium flowing time in the cavities, add accordingly
Thermal medium and the heat transfer effect of air intake duct support plate；On the other hand, relative to all-in-one-piece cavity structure, segmentation
The structure with multiple channel cavity of formula can have the effect of acceleration to thermal medium, the thermal medium that flow velocity strengthens
The temperature of air intake duct support plate can be improved, further increase heat transfer effect.
Above are only the preferred embodiments of the present invention, the present invention is not played any restriction effect.Appoint
What person of ordinary skill in the field, in the range of without departing from technical scheme, to the present invention
The technical scheme disclosed and technology contents make the variation such as any type of equivalent or amendment, all belong to without departing from
The content of technical scheme, within still falling within protection scope of the present invention.
Claims (10)
1. the anti-icing system of an aero-engine air intake duct support plate, it is characterised in that include isolated location and
Thermal medium supply unit, described air intake duct support plate has cavity, and described cavity has arrival end and the port of export,
Described isolated location is fixed in described cavity, for described cavity is divided into multiple passage being interconnected empty
Chamber, the thermal medium of described thermal medium supply unit conveying enters in described channel cavity through described arrival end, and
Discharge from the described port of export.
2. anti-icing system as claimed in claim 1, it is characterised in that at least one described channel cavity
Being fixed with spoiler, described spoiler is fixed on air intake duct support plate or is fixed on isolated location.
3. anti-icing system as claimed in claim 2, it is characterised in that the quantity of described spoiler is multiple,
It is respectively fixed with described spoiler on described air intake duct support plate and isolated location.
4. the anti-icing system as according to any one of claims 1 to 3, it is characterised in that be positioned at described air inlet
The width of one described channel cavity of road support plate edge is less than the width of other described channel cavity.
5. anti-icing system as claimed in claim 4, it is characterised in that be positioned at described air intake duct support plate leading edge
Being fixed with spoiler in one described channel cavity at place, described spoiler is fixed on air intake duct support plate or solid
It is scheduled on isolated location, is positioned at a described channel cavity of described air intake duct support plate edge and described entrance
End connects, and is positioned at a described channel cavity at described air intake duct support plate trailing edge and is connected with the described port of export.
6. anti-icing system as claimed in claim 1, it is characterised in that described isolated location uses division board
Structure.
7. anti-icing system as claimed in claim 1, it is characterised in that described thermal medium is hot gas or deep fat.
8. anti-icing system as claimed in claim 7, it is characterised in that described thermal medium is deep fat, described
Thermal medium supply unit is for carrying the hot lubricating oil that engine lubrication system provides.
9. anti-icing system as claimed in claim 1, it is characterised in that described air intake duct support plate includes support plate
Body, entrance pipe, entrance transition, export orientation section, outlet transition and outlet pipe, described
Plate body has described cavity, and described support plate body is connected with entrance pipe by entrance transition, described
Plate body also passes sequentially through export orientation section, outlet transition is connected with outlet pipe, and thermal medium is successively through institute
State in the cavity that entrance pipe and entrance transition enter support plate body, and successively through described export orientation section,
Outlet transition and outlet pipe are discharged, and described export orientation section is for changing the outflow direction of thermal medium.
10. an anti-icing method for aero-engine air intake duct support plate, applies and appoints in such as claim 1～9
In one described anti-icing system, it is characterised in that carry thermal medium by described thermal medium supply unit,
Described thermal medium enters described channel cavity from described arrival end, and discharges from the described port of export.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610248452.0A CN105927389B (en) | 2016-04-20 | 2016-04-20 | The anti-icing system and anti-icing method of aero-engine air intake duct support plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610248452.0A CN105927389B (en) | 2016-04-20 | 2016-04-20 | The anti-icing system and anti-icing method of aero-engine air intake duct support plate |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105927389A true CN105927389A (en) | 2016-09-07 |
| CN105927389B CN105927389B (en) | 2017-11-24 |
Family
ID=56838703
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610248452.0A Expired - Fee Related CN105927389B (en) | 2016-04-20 | 2016-04-20 | The anti-icing system and anti-icing method of aero-engine air intake duct support plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105927389B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106703997A (en) * | 2016-12-19 | 2017-05-24 | 北京航空航天大学 | Forward-gap hot-air anti-icing structure with supporting plate for engine |
| CN106762147A (en) * | 2017-02-22 | 2017-05-31 | 中国航发沈阳发动机研究所 | A kind of engine anti-icing system |
| CN113047960A (en) * | 2021-03-22 | 2021-06-29 | 南京航空航天大学 | Novel aeroengine backward flow formula lubricating oil anti-icing extension board inner chamber structure |
| CN114458450A (en) * | 2022-02-10 | 2022-05-10 | 中国航发沈阳发动机研究所 | Aeroengine air inlet machine casket anti-icing structure |
| 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 |
|---|---|---|---|---|
| US5029440A (en) * | 1990-01-26 | 1991-07-09 | The United States Of America As Represented By The Secretary Of The Air Force | Acoustical anti-icing system |
| US20020071766A1 (en) * | 2000-12-12 | 2002-06-13 | Snecma Moteurs | Turbomachine stator flap, and a method of manufacturing it |
| FR2857699A1 (en) * | 2003-07-17 | 2005-01-21 | Snecma Moteurs | Turbine intake guide wheel blade de-icer has at least one emission slot in a fore and aft direction along trailing edge of blade's fixed section |
| US20100329836A1 (en) * | 2009-06-30 | 2010-12-30 | Wayne Garcia Edmondson | Method of operating a heated guide vane assembly |
| CN102418603A (en) * | 2011-10-19 | 2012-04-18 | 中国航空动力机械研究所 | Blade anti-icing device and blade anti-icing system with same |
| CN104088704A (en) * | 2014-06-26 | 2014-10-08 | 北京航空航天大学 | Aero-engine hot-air anti-icing cavity device with conformal anti-icing wall surface |
-
2016
- 2016-04-20 CN CN201610248452.0A patent/CN105927389B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5029440A (en) * | 1990-01-26 | 1991-07-09 | The United States Of America As Represented By The Secretary Of The Air Force | Acoustical anti-icing system |
| US20020071766A1 (en) * | 2000-12-12 | 2002-06-13 | Snecma Moteurs | Turbomachine stator flap, and a method of manufacturing it |
| FR2857699A1 (en) * | 2003-07-17 | 2005-01-21 | Snecma Moteurs | Turbine intake guide wheel blade de-icer has at least one emission slot in a fore and aft direction along trailing edge of blade's fixed section |
| US20100329836A1 (en) * | 2009-06-30 | 2010-12-30 | Wayne Garcia Edmondson | Method of operating a heated guide vane assembly |
| CN102418603A (en) * | 2011-10-19 | 2012-04-18 | 中国航空动力机械研究所 | Blade anti-icing device and blade anti-icing system with same |
| CN104088704A (en) * | 2014-06-26 | 2014-10-08 | 北京航空航天大学 | Aero-engine hot-air anti-icing cavity device with conformal anti-icing wall surface |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106703997A (en) * | 2016-12-19 | 2017-05-24 | 北京航空航天大学 | Forward-gap hot-air anti-icing structure with supporting plate for engine |
| CN106703997B (en) * | 2016-12-19 | 2018-08-24 | 北京航空航天大学 | Lean forward seam engine support plate hot air anti-icing structure |
| CN106762147A (en) * | 2017-02-22 | 2017-05-31 | 中国航发沈阳发动机研究所 | A kind of engine anti-icing system |
| CN113047960A (en) * | 2021-03-22 | 2021-06-29 | 南京航空航天大学 | Novel aeroengine backward flow formula lubricating oil anti-icing extension board inner chamber structure |
| CN114458450A (en) * | 2022-02-10 | 2022-05-10 | 中国航发沈阳发动机研究所 | Aeroengine air inlet machine casket anti-icing structure |
| 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 |
|---|---|
| CN105927389B (en) | 2017-11-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105927389A (en) | Anti-icing system and method for aero-engine intake support plate | |
| US10737792B2 (en) | Turbofan engine fluid ice protection delivery system | |
| RU2529927C1 (en) | Aircraft de-icing system and aircraft with such system | |
| EP3179074A1 (en) | Thermal management system | |
| US10087841B2 (en) | Nacelle equipped with an oil-cooling circuit comprising an intermediate heat exchanger | |
| CN208134635U (en) | A kind of anti-deicing system for medium-and-large-sized fixed-wing unmanned plane | |
| US8297038B2 (en) | Gas turbine aircraft engines and operation thereof | |
| EP2866011A2 (en) | Temperature sensors | |
| US10683084B2 (en) | System for dual management of anti-icing and boundary layer suction on an aerofoil of an aircraft, including a function of collecting the anti-icing air | |
| EP3656674B1 (en) | Leading-edge slat for an aircraft | |
| CN107543649B (en) | Hot air deicing total pressure sensor | |
| CN111577466A (en) | Ice-proof bleed air preheating and turbine cooling bleed air precooling system for aircraft engine | |
| CN202624640U (en) | Ice prevention cavity for air inlet channel | |
| EP1935783B1 (en) | Ice protection system including a plurality of segmented sub-areas and a cyclic diverter valve | |
| CN101590913A (en) | Adopt the anti-icing and deicing method for civil aircraft of loop circuit heat pipe | |
| CN104129504B (en) | A kind of bourdon's tube structure of the angle adjustable for hot air anti-icing | |
| FR2938504B1 (en) | AIR INTAKE OF AN AIRCRAFT ENGINE WITH NON-CARINE PROPELLANT PROPELLERS | |
| CN104088704B (en) | A kind of have the aeroengine hot air anti-icing chamber device conformal with anti-icing wall | |
| CN104833444A (en) | Total air temperature sensor | |
| CN106081122A (en) | A kind of aircraft deicing device | |
| CN109441589A (en) | A kind of tandem oil cooler unit | |
| CN106762146B (en) | A kind of hot air anti-icing structure of engine guide vane | |
| CN203547922U (en) | Shunt ring, engine anti-icing device and turbofan engine | |
| CN105882979A (en) | Anti-icing device for aircraft blade | |
| CN104675524A (en) | Shunting ring, engine anti-icer and turbofan engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171124 Termination date: 20210420 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |