CN106043714B - A kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy - Google Patents

A kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy Download PDF

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Publication number
CN106043714B
CN106043714B CN201610398245.3A CN201610398245A CN106043714B CN 106043714 B CN106043714 B CN 106043714B CN 201610398245 A CN201610398245 A CN 201610398245A CN 106043714 B CN106043714 B CN 106043714B
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CN
China
Prior art keywords
engine core
cabin
wall surface
helicopter
memorial alloy
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CN201610398245.3A
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Chinese (zh)
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CN106043714A (en
Inventor
单勇
谭晓茗
张靖周
顾仁勇
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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Priority to CN201610398245.3A priority Critical patent/CN106043714B/en
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00Power-plant nacelles, fairings, or cowlings
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/40Weight reduction

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

The present invention discloses a kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy, which is characterized in that cabin wall surface is equipped with several openings.It is covered with a block piece shape memory alloys in each opening.One side of piece shape memory alloys is welded on engine core nacelle interior wall face, and other sides are hanging.Under room temperature, piece shape memory alloys are straight, are closed with nacelle interior wall face paste.After temperature increases, piece shape memory alloys are bent to engine room inside, and temperature is higher, and the angle of bending is bigger, and the opening on cabin wall surface is bigger.The opening for being distributed in engine core cabin upper wall surface is used for lifting airscrew downwash flow air inlet;Into cooling air when being distributed in the opening of cabin side wall surface for flying before helicopter.The present invention flies before can meeting helicopter simultaneously and floating state engine core cabin cooling requirement, simple in structure, does not increase helicopter weight, is negatively affected to helicopter performance small.

Description

A kind of cooling air inlet self-regulation helicopter engine core based on unidirectional memorial alloy Cabin
Technical field
The air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy that the present invention relates to a kind of, belongs to straight Rise machine engine core cabin design technical field.
Background technology
In Helicopter System, the piggyback pod of engine is the higher part of temperature in its whole helicopter.In piggyback pod In, not only there are engine and casing, while further including the attachmentes such as engine control, lubricating oil, bleed and other transmissions.Engine The height of core cabin temperature will directly affect the safe and stable operation of these attachmentes, if engine core cabin temperature mistake Height, the various attachmentes in one side engine core cabin are likely to cisco unity malfunction, on the other hand it is also possible to causing to send out Motivation core cabin is on fire, fire occurs, to seriously threaten the flight safety of helicopter.Therefore, it is necessary to engine core Cabin, to make the temperature of engine core cabin room maintain reduced levels, meets flight safety using effective cooling It is required that.
Current helicopter engine core cabin cooling technology is started the engine core engine in engine power cabin one end Cabin cooling air air inlet, and start the engine core cabin cooling air outlet in the piggyback pod other end.Enter piggyback pod Interior cooling air takes away the heat generated in engine core cabin by forced-convection heat transfer, so that it is guaranteed that in cabin electronics and Control element is in the operating temperature of permission.But this engine core cabin cooling structure needs drive gas on helicopter Mouthful, the intake resistance flown before helicopter is on the one hand increased, the Radar Cross Section of helicopter is on the other hand increased.This Outside, when helicopter hovers, because without the effect of preceding winged punching press, air inflow significantly reduces in engine core cabin, cannot Meet engine core cabin cooling requirement.In order to overcome air inflow under floating state to reduce this disadvantage, the hair appropriately designed Motivation exhaust ejector system just compensates in the engine core cabin under floating state cooling air volume not to a certain extent The defect of foot.The ejection system aspirated using engine exhaust kinetic energy is connected with engine core cabin end, and ejection system is not A large amount of surrounding airs are only aspirated to reduce delivery temperature, and aspirate the air in engine core cabin, make engine core Air flows in cabin, increases cooling air volume in engine core cabin, but the ejection system can increase engine The weight and complexity of whole system.
Invention content
The cooling air inlet that the purpose of the present invention is to provide a kind of based on unidirectional memorial alloy is self-regulated helicopter engine Core cabin flies and hovers before can meeting helicopter simultaneously on the basis of existing engine core cabin basic structure State engine core cabin cooling requirement, and do not increase available engine core cabin cooling structure system complexity, Engine overall weight is not increased.
To achieve the above object, the present invention uses following technical scheme:
A kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy, including preceding fire prevention Wall, rear fire wall, side fire wall, lower fire wall, engine core cabin upper wall surface, engine core cabin side wall surface, and The engine core cabin cooling air outlet being set on rear fire wall.The engine core cabin upper wall surface and engine It is respectively equipped with several openings in core cabin side wall surface.It is covered with a unidirectional memorial alloy of block piece shape in each opening.Sheet list It is welded on engine core nacelle interior wall face to a side of memorial alloy, other sides are hanging.
The unidirectional memorial alloy of sheet is Ti-Ni base memorial alloys, Cu base memorial alloys or Fe base memorial alloys.
The shape of the opening is square, rectangle or diamond shape, shape and the opening one of the unidirectional memorial alloy of sheet It causes.
The engine core cabin upper wall surface and the gross area of the opening in engine core cabin side wall surface account for entirely The 10% to 60% of engine core cabin wall surface area.
The advantage of the invention is that:Cooling air volume into engine core engine room inside is with engine core machine The height of cabin internal temperature and increase automatically and reduce;Winged or floating state either before helicopter, which can Normal work;The invention eliminates the engine core cabin cooling air air inlet that general helicopter opens up on helicopter, To reduce flight resistance, and reduce Radar Cross Section.
Description of the drawings
Fig. 1 is the helicopter engine core nacelle cooling system of an angle;
Fig. 2 is the helicopter engine core nacelle cooling system of another angle;
Fig. 3 is inside the helicopter engine core nacelle cooling system of an angle;
Fig. 4 is inside the helicopter engine core nacelle cooling system of another angle;
Figure label and its title:1, preceding fire wall, 2, engine core cabin upper wall surface, 3, piece shape memory alloys, 4, Side fire wall, 5, lower fire wall, 6, engine core cabin side wall surface, 7, rear fire wall, 8, the cooling of engine core cabin it is empty Gas outlet, 9, opening, 10, engine intake, 11, compressor casing, 12, combustion box, 13, turbine casing, 14, turbine Outlet.
Specific implementation mode
A kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy, including preceding fire prevention Wall, rear fire wall, side fire wall, lower fire wall, engine core cabin upper wall surface, engine core cabin side wall surface, and The engine core cabin cooling air outlet being set on rear fire wall.Preceding fire wall 1 is equipped with engine intake 10.Whirlpool There is an annulus between wheel outlet 14 and rear fire wall 7, is exactly engine core cabin cooling air outlet 8.In engine core In scheming cabin, compressor casing 11, combustion box 12 and turbine casing 13 are the main heating sources in engine core cabin, When engine is run, given out in a large amount of heat to engine core cabin by its surface.Engine core cabin upper wall Face 2 and engine core cabin side wall surface 6 are equipped with several openings 9, and being covered with a block piece shape in each opening 9 unidirectionally remembers conjunction Gold 3.The inside for being welded on engine core cabin wall surface on one side of the unidirectional memorial alloy of sheet 3, other sides are hanging.
When helicopter engine is just started to work, the temperature in engine core cabin is not high, engine core machine Without cooling, piece shape memory alloys 3 at this time are straight, are closed with engine core machinery space bulkhead face paste in cabin.At this point, either straight Fly before the machine of liter or hover, engine core cabin wall surface is smooth.This not only reduces the air drag of helicopter flight, Also reduce the Radar Cross Section on helicopter surface.With the accumulation of heat in engine core cabin, engine core Cabin wall surface temperature increase, that is, 3 surface temperature of piece shape memory alloys increase, to 3 surface of piece shape memory alloys start to Engine core engine room inside is bent.Temperature is higher in cabin, and 3 surface of piece shape memory alloys is bent to engine core engine room inside It is more, the opening 9 on engine core cabin wall surface is bigger.
If helicopter is in preceding winged state at this time, outside air is remembered from sheet in engine core cabin side wall surface 6 Enter core engine room inside at the opening 9 that generates after alloy 3 is bent, the heat in engine core cabin is taken away, from starting Machine core cabin cooling air outlet 8 flows out.Once temperature is declined in engine core cabin, piece shape memory alloys 3 Bending degree is slowed down, and the opening 9 on engine core cabin wall surface is reduced by, and the external world into engine core cabin is empty Tolerance is reduced, and vice versa, to play the air capacity automatic adjustment for entering engine core engine room inside.
If helicopter is in floating state at this time, the downwash flow of lifting airscrew can be from engine core cabin Enter core engine room inside at the opening 9 that the piece shape memory alloys 3 of wall surface 2 generate after being bent, outside air is by engine core Heat in cabin is taken away, and is flowed out from engine core cabin cooling air outlet 8.Once there is temperature in engine core cabin Declined, the bending degree of piece shape memory alloys 3 is slowed down, and the opening 9 on engine core cabin wall surface is reduced by, and is entered The outside air amount of engine core cabin is reduced, and vice versa, to play the air for entering engine core engine room inside Amount automatic adjustment.
Number, size and its distribution on engine core cabin wall surface of piece shape memory alloys 3 depend entirely on hair The distribution situation of thermic load and heat in motivation core cabin.The structure that this patent proposes has universality and representativeness, root According to thermic load and heat in engine core cabin distribution situation need to the number of piece shape memory alloys, size and its The specific Theoretical Design of distribution progress, numeric simulation design or experimental design on engine core cabin wall surface, but its work It is constant to make principle or its technological essence.

Claims (4)

  1. Helicopter engine core cabin, including preceding fire wall 1. a kind of cooling air inlet based on unidirectional memorial alloy is self-regulated (1), rear fire wall (7), side fire wall (4), lower fire wall (5), engine core cabin upper wall surface (2), engine core machine Cabin side wall surface (6), and the engine core cabin cooling air outlet (8) that is set on rear fire wall (7);Its feature exists In being respectively equipped with several openings (9) on the engine core cabin upper wall surface (2) and engine core cabin side wall surface (6); It is covered with a unidirectional memorial alloy of block piece shape (3) on each opening (9);One side of the unidirectional memorial alloy of sheet (3) is welded on On engine core nacelle interior wall face, other sides are hanging;The unidirectional memorial alloy of sheet (3) and engine core nacelle interior wall The side of face welding is close to engine intake (10) side.
  2. The helicopter engine core 2. a kind of cooling air inlet based on unidirectional memorial alloy according to claim 1 is self-regulated Cabin, which is characterized in that the unidirectional memorial alloy of sheet (3) is Ti-Ni base memorial alloys, Cu base memorial alloys or Fe bases note Recall alloy.
  3. The helicopter engine core 3. a kind of cooling air inlet based on unidirectional memorial alloy according to claim 1 is self-regulated Cabin, which is characterized in that the shape of the opening (9) is square, rectangle or diamond shape, the unidirectional memorial alloy of sheet (3) Shape is consistent with opening (9).
  4. The helicopter engine core 4. a kind of cooling air inlet based on unidirectional memorial alloy according to claim 1 is self-regulated Cabin, which is characterized in that the opening on the engine core cabin upper wall surface (2) and engine core cabin side wall surface (6) (9) the gross area accounts for the 10% to 60% of entire engine core cabin wall surface area.
CN201610398245.3A 2016-06-07 2016-06-07 A kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy Expired - Fee Related CN106043714B (en)

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CN201610398245.3A CN106043714B (en) 2016-06-07 2016-06-07 A kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy

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CN201610398245.3A CN106043714B (en) 2016-06-07 2016-06-07 A kind of cooling air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy

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Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104760703A (en) * 2015-03-09 2015-07-08 中国航空工业集团公司沈阳飞机设计研究所 Cooling mechanism for ramjet engine
CN104948286A (en) * 2014-03-27 2015-09-30 中航商用航空发动机有限责任公司 Cooling method and device for engine core module

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7340883B2 (en) * 2004-11-12 2008-03-11 The Boeing Company Morphing structure
IL178633A0 (en) * 2006-10-16 2007-09-20 Josef Flomenblit Temperature controlled valve for regulating cooling gas flow
US8991191B2 (en) * 2009-11-24 2015-03-31 General Electric Company Thermally actuated passive gas turbine engine compartment venting

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104948286A (en) * 2014-03-27 2015-09-30 中航商用航空发动机有限责任公司 Cooling method and device for engine core module
CN104760703A (en) * 2015-03-09 2015-07-08 中国航空工业集团公司沈阳飞机设计研究所 Cooling mechanism for ramjet engine

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