CN106043714A - Cooling gas inflow self-adjusting engine core engine room based on one-way memory alloy - Google Patents
Cooling gas inflow self-adjusting engine core engine room based on one-way memory alloy Download PDFInfo
- Publication number
- CN106043714A CN106043714A CN201610398245.3A CN201610398245A CN106043714A CN 106043714 A CN106043714 A CN 106043714A CN 201610398245 A CN201610398245 A CN 201610398245A CN 106043714 A CN106043714 A CN 106043714A
- Authority
- CN
- China
- Prior art keywords
- engine core
- engine room
- core cabin
- cabin
- 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.)
- Granted
Links
- 229910001285 shape-memory alloy Inorganic materials 0.000 title abstract description 17
- 239000000112 cooling gas Substances 0.000 title abstract 4
- 238000001816 cooling Methods 0.000 claims abstract description 34
- 229910045601 alloy Inorganic materials 0.000 claims description 24
- 239000000956 alloy Substances 0.000 claims description 24
- 230000008450 motivation Effects 0.000 claims description 4
- 206010022000 influenza Diseases 0.000 claims description 3
- 229910004337 Ti-Ni Inorganic materials 0.000 claims description 2
- 229910011209 Ti—Ni Inorganic materials 0.000 claims description 2
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 claims description 2
- 239000010931 gold Substances 0.000 claims description 2
- 229910052737 gold Inorganic materials 0.000 claims description 2
- KHYBPSFKEHXSLX-UHFFFAOYSA-N iminotitanium Chemical compound [Ti]=N KHYBPSFKEHXSLX-UHFFFAOYSA-N 0.000 claims description 2
- 238000005452 bending Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 abstract description 2
- 239000007789 gas Substances 0.000 abstract 1
- 238000000034 method Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013401 experimental design Methods 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 invention discloses a cooling gas inflow self-adjusting engine core engine room based on a one-way memory alloy. The cooling gas inflow self-adjusting engine core engine room is characterized in that multiple openings are formed in the wall faces of the engine room. Each opening is covered with a flaky memory alloy piece. One edge of each flaky memory alloy piece is welded to the corresponding inner wall face of the engine core engine room, and the other edges of each flaky memory alloy piece are suspended. At the normal temperature, the flaky memory alloy pieces are flat and straight and are attached to the corresponding inner wall face of the engine room. After the temperature is increased, the flaky memory alloy pieces are bent towards the inner portion of the engine room, and the higher the temperature is, the larger the bending angles are and the larger the openings in the wall faces of the engine room are. The openings distributed in the upper wall face of the engine core engine room are used for inflow of helicopter rotor underwashing gas flow; and the openings distributed in the side wall faces of the engine room are used for inflow of cooling gas in the helicopter forward flight process. By the adoption of the engine room, the requirements for cooling the engine core engine room in the helicopter forward flight state and the helicopter hovering state can be met at the same time, the structure is simple, the weight of a helicopter is not increased, and negative effects on the performance of the helicopter are small.
Description
Technical field
The present invention relates to a kind of air inlet self-regulation helicopter engine core cabin based on unidirectional memorial alloy, belong to straight
Rise machine engine core cabin design technical field.
Background technology
In Helicopter System, the piggyback pod of electromotor is the part that in overall helicopter, temperature is higher.In piggyback pod,
Do not only have electromotor and casing, the most also include electromotor control, lubricating oil, bleed and other driven accessaries.Engine core
The height of cabin temperature is by directly affecting the security and stability of these adnexaes work, if engine core cabin temperature is too high,
On the one hand the various adnexaes in engine core cabin are likely to cisco unity malfunction, on the other hand it is also possible to cause electromotor
Core cabin is on fire, breaking out of fire, thus the flight safety of serious threat helicopter.Therefore, it is necessary to engine core cabin
Use effective cooling technology, in order to make the temperature of room, engine core cabin maintain reduced levels, meet flight safety
Requirement.
Current helicopter engine core cabin cooling technology is core engine of starting the engine in one end, engine power cabin
Cabin cooling air inlet, and the piggyback pod other end start the engine core cabin cooling air outlet slit.Enter into piggyback pod
In cooling air by forced-convection heat transfer, the heat produced in taking away engine core cabin, so that it is guaranteed that in cabin electronics with
Control element in the operating temperature allowed.But this engine core cabin cooling structure needs to drive gas on helicopter into
Mouthful, the intake resistance flown before on the one hand adding helicopter, on the other hand add the Radar Cross Section of helicopter.This
Outward, when helicopter hovers, because flying the effect of punching press before not having, in engine core cabin, air inflow significantly reduces, it is impossible to
Meet engine core cabin cooling requirement.In order to overcome air inflow under floating state to reduce this shortcoming, sending out of appropriate design
In motivation exhaust ejector system compensate for the engine core cabin under floating state to a certain extent, cooling air volume is not enough
Defect.The ejection system utilizing engine exhaust kinetic energy to aspirate is connected with engine core cabin end, and ejection system is not only
Aspirate a large amount of surrounding air to reduce delivery temperature, and aspirate the air in engine core cabin, make engine core machine
In cabin, air flows, and increases cooling air volume in engine core cabin, but to increase electromotor whole for this ejection system
The weight of individual system and complexity.
Summary of the invention
It is an object of the invention to provide a kind of cooling air inlet self-regulation engine core machine based on unidirectional memorial alloy
Cabin, on the basis of the basic structure of existing engine core cabin, can fly before meeting helicopter to send out with floating state simultaneously
Motivation core cabin cooling requirement, and don't increase the complexity of available engine core cabin cooling structure system, do not increase
Electromotor overall weight.
For achieving the above object, the present invention is by the following technical solutions:
A kind of cooling air inlet self-regulation engine core cabin based on unidirectional memorial alloy, including front fire wall, rear defence
Wall with flues, side fire wall, lower fire wall, engine core cabin upper wall surface, engine core cabin side wall, and after being arranged at
Engine core cabin cooling air outlet slit on fire wall.Described engine core cabin upper wall surface and engine core cabin
Some openings it are respectively equipped with on side wall surface.One piece of unidirectional memorial alloy of lamellar it is coated with on each opening.The unidirectional memory of lamellar is closed
One limit of gold is welded on engine core nacelle interior wall face, and other limit is unsettled.
The unidirectional memorial alloy of described lamellar is Ti-Ni base memorial alloy, Cu base memorial alloy or Fe base memorial alloy.
Described opening be shaped as square, rectangle or rhombus, the shape of the unidirectional memorial alloy of lamellar and opening one
Cause.
The gross area of the opening on described engine core cabin upper wall surface and engine core cabin side wall accounts for whole
The 10% to 60% of engine core cabin wall surface area.
It is an advantage of the current invention that: the cooling air volume entering engine core engine room inside is as engine core machine
The height of cabin internal temperature and automatically increase and reduce；Either fly before helicopter, or floating state, this invention can
Normal work；This invention eliminates the engine core cabin cooling air inlet that general helicopter is offered on helicopter,
Thus reduce flight resistance, and reduce Radar Cross Section.
Accompanying drawing explanation
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；
Label and title thereof in figure: 1, front fire wall, 2, engine core cabin upper wall surface, 3, sheet shape memory alloys, 4,
Side fire wall, 5, lower fire wall, 6, engine core cabin side wall, 7, rear fire wall, 8, engine core cabin cooling sky
Gas outlet, 9, opening, 10, engine intake, 11, compressor casing, 12, combustion box, 13, turbine casing, 14, turbine
Outlet.
Detailed description of the invention
A kind of cooling air inlet self-regulation engine core cabin based on unidirectional memorial alloy, including front fire wall, rear defence
Wall with flues, side fire wall, lower fire wall, engine core cabin upper wall surface, engine core cabin side wall, and after being arranged at
Engine core cabin cooling air outlet slit on fire wall.Front fire wall 1 is provided with engine intake 10.Turbine outlet 14
And there is an annulus between rear fire wall 7, it is simply that engine core cabin cooling air outlet slit 8.In engine core cabin,
Compressor casing 11, combustion box 12 and turbine casing 13 are the main heating source in engine core cabin, transport at electromotor
During row, give out substantial amounts of heat in engine core cabin by its surface.Engine core cabin upper wall surface 2 and starting
Machine core cabin side wall surface 6 is provided with some openings 9, and each opening 9 is coated with one piece of unidirectional memorial alloy of lamellar 3.Lamellar
Unidirectional memorial alloy 3 while being welded on the inner side of engine core cabin wall, other limit is unsettled.
When helicopter engine is just started working, the temperature in engine core cabin is the highest, engine core machine
Cabin is without cooling, and sheet shape memory alloys 3 now is straight, fits with engine core cabin wall.Now, the most directly
Flying before the machine of liter or hover, engine core cabin wall is smooth.This not only reduces the air drag of helicopter flight,
Also reduce the Radar Cross Section on helicopter surface.Along with the accumulation of heat, engine core in engine core cabin
Machinery space bulkhead surface temperature raise, namely sheet shape memory alloys 3 surface temperature raise, thus sheet shape memory alloys 3 surface start to
Engine core engine room inside bends.In cabin, temperature is the highest, and sheet shape memory alloys 3 surface bends to engine core engine room inside
The most, the opening 9 on the wall of engine core cabin is the biggest.
If flying state before now helicopter is in, outside air is lamellar memory from engine core cabin side wall 6
Enter core engine room inside at the opening 9 produced after alloy 3 bending, the heat in engine core cabin is taken away, from starting
Machine core cabin cooling air outlet slit 8 flows out.Once in engine core cabin, temperature has declined, sheet shape memory alloys 3
Degree of crook has slowed down, and the opening 9 on the wall of engine core cabin is reduced by, and enters the extraneous empty of engine core cabin
Tolerance reduces, and vice versa, thus the air capacity playing entrance engine core engine room inside is automatically adjusted.
If now helicopter is in floating state, the downwash flow of lifting airscrew can be from engine core cabin
Entering core engine room inside at the opening 9 produced after sheet shape memory alloys 3 bending of wall 2, outside air is by engine core
Heat in cabin is taken away, and from engine core cabin, cooling air outlet slit 8 flows out.Once in engine core cabin, temperature has
Being declined, the degree of crook of sheet shape memory alloys 3 has slowed down, and the opening 9 on the wall of engine core cabin is reduced by, and enters
The outside air amount in engine core cabin reduces, and vice versa, thus plays the air entering engine core engine room inside
Amount is automatically adjusted.
The number of sheet shape memory alloys 3, size and the distribution on the wall of engine core cabin thereof depend entirely on to be sent out
Thermic load in motivation core cabin and the distribution situation of heat.The structure that this patent proposes has universality and representativeness, root
According to the distribution situation of the thermic load in engine core cabin and heat need to the number of sheet shape memory alloys, size and
Distribution on the wall of engine core cabin carries out specific Design Theory, numeric simulation design or experimental design, but its work
Make principle or its technological essence is constant.
Claims (4)
1. a cooling air inlet self-regulation engine core cabin based on unidirectional memorial alloy, including front fire wall (1), rear defence
Wall with flues (7), side fire wall (4), lower fire wall (5), engine core cabin upper wall surface (2), engine core cabin side wall
(6), and be arranged on rear fire wall (7) engine core cabin cooling air outlet slit (8)；It is characterized in that, described
It is respectively equipped with some openings (9) on motivation core cabin upper wall surface (2) and engine core cabin side wall (6)；Each opening
(9) the one piece of unidirectional memorial alloy of lamellar (3) it is coated with on；One limit of the unidirectional memorial alloy of lamellar (3) is welded on electromotor core
On the internal face of scheming cabin, other limit is unsettled.
A kind of cooling air inlet self-regulation engine core cabin based on unidirectional memorial alloy the most according to claim 1,
It is characterized in that, the unidirectional memorial alloy of described lamellar (3) is that Ti-Ni base memorial alloy, Cu base memorial alloy or the memory of Fe base are closed
Gold.
A kind of cooling air inlet self-regulation engine core cabin based on unidirectional memorial alloy the most according to claim 1,
It is characterized in that, described opening (9) be shaped as square, rectangle or rhombus, the shape of the unidirectional memorial alloy of lamellar (3) with
Opening (9) is consistent.
A kind of cooling air inlet self-regulation engine core cabin based on unidirectional memorial alloy the most according to claim 1,
It is characterized in that, the opening (9) on described engine core cabin upper wall surface (2) and engine core cabin side wall (6)
The gross area accounts for the 10% to 60% of whole 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 true CN106043714A (en) | 2016-10-26 |
| CN106043714B CN106043714B (en) | 2018-07-17 |
Family
ID=57169801
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 (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060101807A1 (en) * | 2004-11-12 | 2006-05-18 | Wood Jeffrey H | Morphing structure |
| US20100294476A1 (en) * | 2006-10-16 | 2010-11-25 | David Gorni | Temperature controlled valve for regulating cooling gas flow |
| US20110120075A1 (en) * | 2009-11-24 | 2011-05-26 | Carlos Enrique Diaz | Thermally actuated passive gas turbine engine compartment venting |
| 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 |
-
2016
- 2016-06-07 CN CN201610398245.3A patent/CN106043714B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060101807A1 (en) * | 2004-11-12 | 2006-05-18 | Wood Jeffrey H | Morphing structure |
| US20100294476A1 (en) * | 2006-10-16 | 2010-11-25 | David Gorni | Temperature controlled valve for regulating cooling gas flow |
| US20110120075A1 (en) * | 2009-11-24 | 2011-05-26 | Carlos Enrique Diaz | Thermally actuated passive gas turbine engine compartment venting |
| 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 |
|---|---|
| CN106043714B (en) | 2018-07-17 |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180717 |
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