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 PDFInfo
- 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
- Authority
- CN
- China
- Prior art keywords
- engine core
- cabin
- wall surface
- helicopter
- memorial alloy
- 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.)
- Expired - Fee Related
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- 238000001816 cooling Methods 0.000 title claims abstract description 37
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 28
- 239000000956 alloy Substances 0.000 title claims abstract description 28
- 230000001105 regulatory effect Effects 0.000 claims description 5
- 229910004337 Ti-Ni Inorganic materials 0.000 claims description 2
- 229910011209 Ti—Ni Inorganic materials 0.000 claims description 2
- 229910003460 diamond Inorganic materials 0.000 claims description 2
- 239000010432 diamond Substances 0.000 claims description 2
- KHYBPSFKEHXSLX-UHFFFAOYSA-N iminotitanium Chemical compound [Ti]=N KHYBPSFKEHXSLX-UHFFFAOYSA-N 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims 1
- 229910001285 shape-memory alloy Inorganic materials 0.000 abstract description 14
- 238000005452 bending Methods 0.000 abstract description 3
- 230000008450 motivation Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000013401 experimental design Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- Y—GENERAL 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- 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
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)
- 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.
- 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.
- 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).
- 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106043714A CN106043714A (en) | 2016-10-26 |
| CN106043714B true CN106043714B (en) | 2018-07-17 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610398245.3A Expired - Fee Related 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106043714B (en) |
Citations (2)
| 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)
| 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 |
-
2016
- 2016-06-07 CN CN201610398245.3A patent/CN106043714B/en not_active Expired - Fee Related
Patent Citations (2)
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106043714A (en) | 2016-10-26 |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180717 |
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