CN105927389B - The anti-icing system and anti-icing method of aero-engine air intake duct support plate - Google Patents
The anti-icing system and anti-icing method of aero-engine air intake duct support plate Download PDFInfo
- Publication number
- CN105927389B CN105927389B CN201610248452.0A CN201610248452A CN105927389B CN 105927389 B CN105927389 B CN 105927389B CN 201610248452 A CN201610248452 A CN 201610248452A CN 105927389 B CN105927389 B CN 105927389B
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- China
- Prior art keywords
- support plate
- air intake
- intake duct
- cavity
- thermal medium
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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
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- 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 a kind of anti-icing system of aero-engine air intake duct support plate, including isolated location and thermal medium supply unit, the air intake duct support plate has cavity, the cavity has arrival end and the port of export, the isolated location is fixed in the cavity, for the cavity to be divided into multiple interconnected channel cavities, the thermal medium of the thermal medium supply unit conveying enters in the channel cavity through the arrival end, and is discharged from the port of export.Anti-icing system provided by the invention includes multiple interconnected channel cavities, on the one hand, adds the flowing time of thermal medium in the cavities, accordingly adds the heat transfer effect of thermal medium and air intake duct support plate；On the other hand, relative to the cavity structure of monoblock type, the structure with multiple channel cavities of partition type can be to thermal medium with the effect accelerated, and the thermal medium that flow velocity increases can improve the temperature of air intake duct support plate, further increase heat transfer effect.
Description
Technical field
The present invention relates to a kind of anti-icing system of aero-engine, especially a kind of aero-engine air intake duct support plate is prevented
Ice system and anti-icing method.
Background technology
Aircraft ice formation issues are to jeopardize the serious problems of flight safety, and the aircraft accident relevant with icing has hair every year
It is raw.Aero gas turbine engine is part most sensitive in aircraft icing part, because high engine speeds rotate, makes air inlet
Road air is in aspiration phases, and air-flow accelerates, and static temperature declines so that aero-engine gas handling system is easier by icing weather
Influence, it is easier to freeze.Once engine aspirating system freezes, the aerodynamic characteristics of gas handling system, increase stream can be changed
Dynamic resistance, make inlet flow field skewness, flow distortion occurs when light, so as to influence the job stability of engine, when serious
It may cause flame-out parking, cause lethal effect.If engine aspirating system freezes, anti-icing system opens hysteresis, can also
The ice cube for causing thawing to come off is sucked by engine, produces engine by the serious problems of Foreign Object Damage.Transported according to American National
Defeated safety committee NTSB statistics is between 1998-2007, and aircraft accident is up to 264 caused by icing, wherein causing
Major accident 94 rises, dead 202 people.Russia finds to aero-engine icing accident investigation, can usually cause due to freezing
The accident of the serious threat flight safeties such as aero-engine aerodynamic stability is insufficient, aerial auto extinguishing.
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 studies it and paid much attention to.Aero-engine air inlet component is influenceed to freeze with anti-icing factor much, it is necessary to be directed to
The working condition and flight environment of vehicle of engine do specific analysis and design.Icing for aero-engine gas handling system and anti-
Ice performance, researcher have carried out substantial amounts of calculating analysis and experimental study.Some American-European aviation developed countries are for influenceing to navigate
Meteorological condition that empty engine freezes, flight parameter, modular construction parameter etc. there has been certain understanding, but due to freezing by very
More factors influences, such as content (LWC), the temperature of super-cooling waterdrop, the size of super-cooling waterdrop, aircraft of cloud layer aqueous water flight
Surface characteristic of speed and posture, engine charge modular construction form and material etc., aero-engine gas handling system freeze and
The problem of mechanism of anti-icing research is still one extremely complex.
In the last few years, domestic water impact characteristics in aircraft wing, ice increased calculating, anti-icing load Analysis etc. are all
Make some progress, as carried out full machine three-dimensional water impact characteristics for China first feeder liner ARJ21
Analysis is calculated, and the accumulated ice of critical component calculates analysis, has carried out influence wind tunnel experiment of the ice type to aircraft aerodynamic performance and has ground
Study carefully.For the ice formation issues research of aircraft wing, domestic icing/anti-icing research work phase in aircraft engine part
It is also fewer for.
Aero-engine imported equipments and parts (such as air intake duct support plate) it is anti-icing use hot gas anti-icing system, hot gas is from pressure
Mechanism of qi intergrade is drawn, and being imported by pipeline needs anti-icing components interior passage, and heater block keeps component surface temperature
On freezing point, so as to aggregation of the anti-stagnant ice on imported equipments and parts surface.Hot gas anti-icing system is due to needing calming the anger from engine
Power traction gas, the efficiency of engine can be caused to have declined.In addition, the cavity structure of available engine imported equipments and parts is relatively simple,
Hot gas is merely capable of carrying out heat exchange with imported equipments and parts, and heat exchanger effectiveness is not high.Therefore, it is necessary to provide a kind of heat transfer effect
More preferable anti-icing system.
The content of the invention
It is an object of the invention to provide a kind of anti-icing system of aero-engine air intake duct support plate and anti-icing method, with solution
The problem of certainly existing anti-icing system heat transfer effect is poor.
In order to achieve the above object, the invention provides a kind of anti-icing system of aero-engine air intake duct support plate, including
Isolated location and thermal medium supply unit, the air intake duct support plate have cavity, and the cavity has arrival end and the port of export, institute
State isolated location to be fixed in the cavity, for the cavity to be divided into multiple interconnected channel cavities, the heat is situated between
The thermal medium of matter supply unit conveying enters in the channel cavity through the arrival end, and is discharged from the port of export.
Further, spoiler is fixed with least one channel cavity, the spoiler is fixed on air intake duct branch
On plate or it is fixed on isolated location.
Further, the quantity of the spoiler is multiple to be respectively fixed with the air intake duct support plate and isolated location
The spoiler.
Further, the width positioned at a channel cavity of the air intake duct support plate edge is less than described in other
The width of channel cavity.
Further, spoiler is fixed with a channel cavity of the air intake duct support plate edge, institute
State spoiler to be fixed on air intake duct support plate or be fixed on isolated location, positioned at an institute of the air intake duct support plate edge
Channel cavity is stated to be connected with the arrival end, a channel cavity at the air intake duct support plate trailing edge with it is described go out
The connection of mouth end.
Further, the isolated location uses partition plate structure.
Further, the thermal medium is hot gas or deep fat.
Further, the thermal medium is deep fat, and the thermal medium supply unit carries for conveying engine lubrication system
The hot lubricating oil supplied.
Further, the air intake duct support plate includes support plate body, entrance pipe, entrance transition, export orientation section, gone out
Mouth transition and outlet pipe, the support plate body have the cavity, and the support plate body passes through entrance transition and entrance
Pipe connects, and the support plate body also passes sequentially through export orientation section, outlet transition is connected with outlet pipe, and thermal medium is successively
Enter through the entrance pipe and entrance transition in the cavity of support plate body, and successively through the export orientation section, outlet gradually
Become section and outlet pipe discharge, the export orientation section is used for the outflow direction for changing thermal medium.
Present invention also offers a kind of anti-icing method of aero-engine air intake duct support plate, apply in described anti-icing system
On, thermal medium is conveyed by the thermal medium supply unit, the thermal medium enters in the channel cavity from the arrival end,
And discharged from the port of export.
The invention provides a kind of anti-icing system of aero-engine air intake duct support plate and anti-icing method, in aero-engine
Into during easy freezing environment or aero-engine air intake duct support plate produce icing phenomenon when, by the way that high-temperature medium is pumped into support plate
Portion's air, to improve air intake duct support plate hull-skin temperature, so as to prevent support plate outer surface from producing icing phenomenon or eliminate air intake duct
The icing phenomenon of support plate outer surface.The anti-icing system includes multiple interconnected channel cavities, on the one hand, adds thermal medium
Flowing time in the cavities, accordingly add the heat transfer effect of thermal medium and air intake duct support plate；On the other hand, relative to entirety
The cavity structure of formula, the structure with multiple channel cavities of partition type can increase to thermal medium with the effect accelerated, flow velocity
Thermal medium can improve the temperature of air intake duct support plate, further increase heat transfer effect.
Brief description of the drawings
Fig. 1 is the stereogram of air intake duct support plate provided in an embodiment of the present invention；
Fig. 2 is the sectional view of air intake duct support plate provided in an 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：First internal channel, 10：Spoiler, 11：First partition,
12：Second internal channel, 13：Second partition, 14：3rd internal channel, 15：Export orientation section inner chamber, 16：Transition inner chamber is exported,
17：Export pipe inner chamber.
Embodiment
The embodiment of the present invention is described in more detail below in conjunction with schematic diagram.According to description below and
Claims, advantages and features of the invention will become apparent from.It should be noted that accompanying drawing is using very simplified form and
Using non-accurately ratio, only for the purpose of facilitating and clarifying the purpose of the embodiments of the invention.
As shown in Fig. 1~2, a kind of anti-icing system of aero-engine air intake duct support plate is present embodiments provided, including every
From unit and thermal medium supply unit (not shown), the air intake duct support plate has cavity, and the cavity has arrival end and gone out
Mouth end, the isolated location is fixed in the cavity, for the cavity to be divided into multiple interconnected channel cavities, institute
The thermal medium for stating the conveying of thermal medium supply unit enters in the channel cavity through the arrival end, and is arranged from the port of export
Go out.
The anti-icing system includes multiple interconnected channel cavities, on the one hand, adds the stream of thermal medium in the cavities
The dynamic time, accordingly add the heat transfer effect of thermal medium and air intake duct support plate；On the other hand, relative to the cavity knot of monoblock type
Structure, the structure with multiple channel cavities of partition type can be to thermal medium with the effect accelerated, the thermal medium meeting of flow velocity increasing
The temperature of air intake duct support plate is improved, further increases heat transfer effect.
Preferably, spoiler 10 is fixed with least one channel cavity, it is high to channel cavity inside for strengthening
The perturbation of warm medium (alternatively referred to as thermal medium), is imitated so as to further enhance the heat exchange of high-temperature medium and channel cavity inwall
Fruit.Specifically, similarly, set spoiler 10 to increase time of the thermal medium in channel cavity, improve heat transfer effect, also may be used
Because shortening the width of channel cavity at spoiler 10 and then adding the flow velocity of thermal medium, air intake duct support plate is accordingly improved
Temperature.The spoiler is fixed on air intake duct support plate or is fixed on isolated location.
In the present embodiment, the quantity of the spoiler 10 is multiple to distinguish on the air intake duct support plate and isolated location
It is fixed with the spoiler, but not limited to this.
The width for being preferably located at a channel cavity of the air intake duct support plate edge is described logical less than other
The width of road cavity.Because in a practical situation, air intake duct support plate leading edge is easier to freeze, therefore close to a passage sky of leading edge
When chamber width is less than other channel cavities, in the channel cavity of edge the flow velocity of thermal medium faster, edge air intake duct branch
The temperature of plate is relatively higher, it is easier to anti-icing.
In the present embodiment, a channel cavity positioned at the air intake duct support plate edge connects with the arrival end
Connect, the spoiler 10 is arranged in a channel cavity of the air intake duct support plate edge, positioned at the air intake duct
A channel cavity at support plate trailing edge is connected with the port of export.
Isolated location can be diversified forms, for example, the isolated location uses partition plate structure, but not limited to this.
In the present embodiment, isolated location includes first partition 11 and second partition 13, and cavity is divided into three channel cavities by isolated location,
Respectively the first internal channel 9, the second internal channel 12 and the 3rd internal channel 14, the first internal channel 9 is close to leading edge, and the first internal channel
Spoiler is provided with 9.
The thermal medium is hot gas or deep fat.In the present embodiment, the thermal medium is deep fat, and the thermal medium conveying is single
Member is used for the hot lubricating oil for conveying engine lubrication system offer.The hot lubricating oil that can be provided using engine lubrication system is added
Heat is anti-icing, can both reduce demand of the engine anti-icing system to hot gas, and improve the efficiency of compressor, while can also play
The effect of cooling lubricating oil.
In the present embodiment, the air intake duct support plate includes support plate body 3, entrance pipe 1, entrance transition 2, outlet guide
There is the cavity to section 4, outlet transition 5 and outlet pipe 6, the support plate body, the support plate body 3 by entrance gradually
Become section 2 to be connected with entrance pipe 1, the support plate body also passes sequentially through export orientation section 4, outlet transition 5 and outlet pipe 6
Connection, thermal medium enter in the cavity of support plate body 3 through the entrance pipe 1 and entrance transition 2 successively, and successively through described
Export orientation section 4, outlet transition 5 and outlet pipe 6 are discharged, and the export orientation section 4 is used for the outflow side for changing thermal medium
To.
Wherein, entrance pipe 1 has entrance pipe inner chamber 7, and entrance transition 2 has entrance transition inner chamber 8, outlet guide
There is export orientation section inner chamber 15 to section 4, outlet transition 5 has outlet transition inner chamber 16, and there is outlet pipe 6 outlet to justify
Tube cavity 17, entrance transition 2 and outlet transition 5 can reduce the resistance of high-temperature medium pump into and out air intake duct support plate,
Entrance pipe 1 and outlet pipe 6 are advantageous to connect 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 in described anti-icing system
On system, thermal medium is conveyed by the thermal medium supply unit, the thermal medium enters the channel cavity from the arrival end
In, and discharged from the port of export.
The anti-icing system and anti-icing method that the present embodiment provides, which can be used for preventing freezing, can be used for removing icing.Tool
Body, in order to prevent aero-engine air intake duct support plate outer surface from producing icing phenomenon, enter easy icing ring in aero-engine
During border, by the way that high-temperature medium is pumped into air intake duct support plate internal cavities, to improve air intake duct support plate hull-skin temperature, so as to prevent
Support plate outer surface produces icing phenomenon.(in general, the aeroplane engine when aero-engine air intake duct support plate produces icing phenomenon
When machine air inflow is reduced, can determine that and produce icing phenomenon for air intake duct support plate), by the way that high-temperature medium is pumped into air intake duct support plate
The interconnected channel cavity in three, portion, the temperature of support plate outer surface can be promptly improved, so as to eliminate outside air intake duct support plate
The icing phenomenon on surface, and then can prevent engine from producing the problem of high-altitude is stopped because inspiratory capacity die-offs.
The invention provides a kind of anti-icing system of aero-engine air intake duct support plate and anti-icing method, in aero-engine
Into during easy freezing environment or aero-engine air intake duct support plate produce icing phenomenon when, by the way that high-temperature medium is pumped into support plate
Portion's air, to improve air intake duct support plate hull-skin temperature, so as to prevent support plate outer surface from producing icing phenomenon or eliminate air intake duct
The icing phenomenon of support plate outer surface.The anti-icing system includes multiple interconnected channel cavities, on the one hand, adds thermal medium
Flowing time in the cavities, accordingly add the heat transfer effect of thermal medium and air intake duct support plate；On the other hand, relative to entirety
The cavity structure of formula, the structure with multiple channel cavities of partition type can increase to thermal medium with the effect accelerated, flow velocity
Thermal medium can improve the temperature of air intake duct support plate, further increase heat transfer effect.
The preferred embodiments of the present invention are above are only, any restrictions effect is not played to the present invention.Belonging to any
Those skilled in the art, in the range of technical scheme is not departed from, to the invention discloses technical scheme and
Technology contents make the variation such as any type of equivalent substitution or modification, belong to the content without departing from technical scheme, still
Belong within protection scope of the present invention.
Claims (9)
1. a kind of anti-icing system of aero-engine air intake duct support plate, it is characterised in that conveyed including isolated location and thermal medium
Unit, the air intake duct support plate have cavity, and the cavity has arrival end and the port of export, and the isolated location is fixed on described
In cavity, for the cavity to be divided into multiple interconnected channel cavities, heat Jie of the thermal medium supply unit conveying
Matter enters in the channel cavity through the arrival end, and is discharged from the port of export；The thermal medium is deep fat.
2. anti-icing system as claimed in claim 1, it is characterised in that be fixed with flow-disturbing at least one channel cavity
Piece, the spoiler are fixed on air intake duct support plate or are fixed on isolated location.
3. anti-icing system as claimed in claim 2, it is characterised in that the quantity of the spoiler is multiple, the air intake duct
The spoiler is respectively fixed with support plate and isolated location.
4. such as anti-icing system according to any one of claims 1 to 3, it is characterised in that positioned at the air intake duct support plate leading edge
The width of one channel cavity at place is less than the width of other channel cavities.
5. anti-icing system as claimed in claim 4, it is characterised in that positioned at described in one of the air intake duct support plate edge
Spoiler is fixed with channel cavity, the spoiler is fixed on air intake duct support plate or is fixed on isolated location, positioned at institute
A channel cavity for stating air intake duct support plate edge is connected with the arrival end, at the air intake duct support plate trailing edge
A channel cavity be connected with the port of export.
6. anti-icing system as claimed in claim 1, it is characterised in that the isolated location uses partition plate structure.
7. anti-icing system as claimed in claim 1, it is characterised in that the thermal medium supply unit is used to convey engine profit
The hot lubricating oil that sliding system provides.
8. anti-icing system as claimed in claim 1, it is characterised in that the air intake duct support plate includes support plate body, entrance is justified
Pipe, entrance transition, export orientation section, outlet transition and outlet pipe, the support plate body have the cavity, the branch
Plate body is connected by entrance transition with entrance pipe, and the support plate body also passes sequentially through export orientation section, outlet gradual change
Section is connected with outlet pipe, and thermal medium enters in the cavity of support plate body through the entrance pipe and entrance transition successively, and
It is used to change thermal medium through the export orientation section, outlet transition and outlet pipe discharge, the export orientation section successively
Flow out direction.
9. a kind of anti-icing method of aero-engine air intake duct support plate, apply such as according to any one of claims 1 to 8 anti-
In ice system, it is characterised in that convey thermal medium by the thermal medium supply unit, the thermal medium enters from the arrival end
Enter in the channel cavity, and discharged from the 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 CN105927389A (en) | 2016-09-07 |
| CN105927389B true CN105927389B (en) | 2017-11-24 |
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| 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 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106762147B (en) * | 2017-02-22 | 2019-04-23 | 中国航发沈阳发动机研究所 | A kind of engine anti-icing system |
| CN113047960B (en) * | 2021-03-22 | 2022-06-10 | 南京航空航天大学 | Aero-engine 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 |
| CN114922734B (en) * | 2022-06-10 | 2023-05-23 | 南京航空航天大学 | Uniform temperature rectification support plate hot gas anti-icing structure based on rib column partition turbulence |
Citations (4)
| 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 |
| 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 |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2817906B1 (en) * | 2000-12-12 | 2003-03-28 | Snecma Moteurs | TURBOMACHINE RECTIFIER COMPONENT AND ITS MANUFACTURING METHOD |
| US20100329836A1 (en) * | 2009-06-30 | 2010-12-30 | Wayne Garcia Edmondson | Method of operating a heated guide vane assembly |
-
2016
- 2016-04-20 CN CN201610248452.0A patent/CN105927389B/en not_active Expired - Fee Related
Patent Citations (4)
| 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 |
| 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 |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN105927389A (en) | 2016-09-07 |
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