CN110043369A - A kind of aero-engine anti-icing equipment using synthesizing jet-flow auxiliary continuity jet stream - Google Patents
A kind of aero-engine anti-icing equipment using synthesizing jet-flow auxiliary continuity jet stream Download PDFInfo
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- CN110043369A CN110043369A CN201910283212.8A CN201910283212A CN110043369A CN 110043369 A CN110043369 A CN 110043369A CN 201910283212 A CN201910283212 A CN 201910283212A CN 110043369 A CN110043369 A CN 110043369A
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- 239000012530 fluid Substances 0.000 abstract description 9
- 238000010586 diagram Methods 0.000 description 12
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- 230000000694 effects Effects 0.000 description 6
- 230000015572 biosynthetic process Effects 0.000 description 5
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- 238000003786 synthesis reaction Methods 0.000 description 4
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- 239000007921 spray Substances 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000005485 electric heating Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 230000008014 freezing Effects 0.000 description 2
- 238000007710 freezing Methods 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
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- 230000002159 abnormal effect Effects 0.000 description 1
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- 238000000605 extraction Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000013529 heat transfer fluid Substances 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 230000003434 inspiratory effect Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
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Classifications
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- 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
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
-
- 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- 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
-
- 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of aero-engine anti-icing equipments using synthesizing jet-flow auxiliary continuity jet stream, including engine charge lip, Jet stream array and synthesizing jet-flow exciter, engine charge lip is an arcwall face, arcwall face forms a cavity, several Jet stream arrays are successively set on cavity inside, synthesizing jet-flow exciter is set between two adjacent Jet stream arrays, synthesizing jet-flow exciter is a hollow cavity, and movement diaphragm and exciter aperture are provided on cavity, movement diaphragm connects with driver, Jet stream array and exciter aperture are directed to engine charge lip；The collar vortex that synthesizing jet-flow exciter is formed in the present invention, impacts target plate surface, enhances the heat convection of jet stream Yu engine charge lip surfaces；Synthesizing jet-flow improve between Jet stream array due to adjacent continuous jet stream liquidate boundary layer at position thicken and fluid and engine charge lip heat convection caused to weaken the problem of；It realizes aero-engine lip and prevents/deicing.
Description
Technical field
The invention belongs to aero-engine air inlet lip anti-icing technology fields, in particular to a kind of to be assisted using synthesizing jet-flow
The aero-engine anti-icing equipment of continuity jet stream.
Background technique
Under the conditions of icing meteorology when flight, icing phenomenon can occur aircraft for the windward side of the components such as wing and engine,
Freeze the flight safety that can seriously jeopardize to aircraft.As inspiratory component, when engine charge lip freezes, it is started
The stabilization of machine, the flight safety of effectively operation even aircraft bring very big harm, are mainly reflected in the following aspects: (1)
Aeroperformance deteriorates, and the icing of engine suction component will lead to the deterioration of these component aeroperformances, as velocity field generation is abnormal
Become, air-flow occurs local detachment, or even causes the vibration of compressor blade；(2) motor power reduces, engine suction component
It freezes and reduces the circulation area of air-flow, reduce the air mass flow into engine, and then the thrust of engine is caused to reduce.
(3) ice, which falls off, damages engine, and the ice to fall off can enter the inside of engine with air-flow, and hitting has very big revolving speed
Fan or compressor blade, cause the mechanical damage of engine.Therefore, it is very necessary for carrying out deicing to engine.
At present aircraft engine it is anti-/ equipment of deicing is divided into two major classes: anti-icing system and deicing system.The work of anti-icing system
With being to prevent from freezing on aircraft and engine components, it is using hot-air (compressor extraction), electric heating or low special of freezing point
The methods of liquid is anti-icing to realize.Deicing system is the system that ice is removed periodically when tying a small amount of ice on aircraft components,
Using modes such as expansion tube, electric pulse, electric heating come deicing.Deicing system can be used at the position for allowing to tie a small amount of ice.
But both anti-/ deicing modes have the shortcomings that it is respective.Firstly, for anti-icing system, in order to guarantee engine
Thrust under given rotating speed must just be automatically increased fuel oil specific discharge.On the one hand the consumption of fuel oil is increased, on the other hand
Fuel gas temperature before turbine can also be made increases, and turbine life reduces, in some instances it may even be possible to burn out turbine.Lead in engine anti-icing system
The bleed out of engine is often required, therefore engine performance may degenerate.Secondly, can disappear during deicing for deicing system
Consume a large amount of energy of engine, this makes deicing system that can only work in a short time, cannot continue to aero-engine into
Row prevents/de-icing work.
Forefathers expand a large amount of technology to the anti-icing work of aero-engine air inlet lip and attempt.
BJ University of Aeronautics & Astronautics etc. discloses a kind of with the aero-engine hot air anti-icing chamber conformal with anti-icing wall surface
Device (patent No.: CN201410298494.6).The anti-icing chamber device includes anti-icing chamber mouthpiece, sealing element, supporting element, prevents
Ice chamber end cap, Partition for realigning water flow and rectification nail.Partition for realigning water flow is placed between anti-icing cavity outer wall and anti-icing cavity wall, makes anti-icing chamber point
From for three chambers.The pin array being arranged on Partition for realigning water flow can disturb the flowing of anti-icing hot gas in third chamber, increase
The turbulivity of hot gas flowing, to strengthen the Convective Heat Transfer of hot gas and anti-icing wall surface.Liu Yong disclose a kind of engine into
Air flue anti-icing system (patent No.: CN201410100780.7).System includes heat exchanger channels, air entraining pipe, annular gas-distributing pipe and row
Tracheae.Annular gas-distributing pipe is arranged in heat exchanger channels, is equipped with aperture on annular gas-distributing pipe, the close air intake duct of air entraining pipe into
One end of mouth is connected with aperture.Wherein, annular gas-distributing pipe has throat and lip, and lip is along towards the import direction of air intake duct
Extending, adjustable guide-ring is installed on lip, the middle face of adjustable guide-ring and air intake duct is angled,
And the angle of guide-ring is adjusted by driving mechanism.Chen Jun discloses a kind of air intake duct anti-icing equipment and civilian turbofan starts
Machine (patent No.: CN201210496822.4).It passes through internal heat knot using the surrounding air outside the acquisition of bleed structure
For structure by the surrounding air of low temperature and exchanging in fan nacelle to heat exchanger components progress heat, the air after heating is then introduced into air-flow
Heating structure heats inlet lip, to meet the anti-icing demand of engine inlets.Air China's commercial engines
Company discloses a kind of hot-air anti-icer for engine inlet (patent No.: CN201110447988.2).Its purpose is
A kind of stream of hot air that can effectively control is provided to including: from calming the anger to improve the hot air anti-icing device of the heat exchange efficiency device
Before power traction goes out the bleed pipeline of hot-air, the circulating line being connected to bleed pipeline, circulating line is supported to air intake duct nacelle
Multiple brackets on wall surface are mounted on the multiple water conservancy diversion for being used to guide air-flow in the jet throat of circulating line on the lip formed
Leaf grating and the exhaust pipe that the air after the heat exchange in heat exchanger channels is discharged.The invention makes the hot-air sprayed as far as possible
Ground is bonded the anti-icing surface flow in air intake duct leading edge heat exchanger channels, and advances in the shape of a spiral in heat exchanger channels, to greatest extent
Improve heat exchange efficiency in ground.United Technologies Corporation discloses an aero-engine anti-icing system (patent No.: US2016/
0167792 A1).It includes a cavity, which there is one to pass through pipeline to cavity for the outer surface of icing and one
Inside provides the gas source of hot-air.The system installs multiple temperature sensors in engine surface, related to detecting for measuring
The temperature on surface judges its ice conditions in turn.System controller and each temperature sensor communication.The controller is according to temperature
Spend sensor output come judge each temperature sensor whether failure.
Rolls-Roy Si company discloses a kind of aircraft and the aircraft engine nacelle deicer (patent No.: US
8480032 B2).The device is mounted with deicer in aircraft and aircraft engine nacelle.It is set with engine nacelle in inlet
Circular passage is set, which introduces hot-air.At least one oil cooler is mounted on inside enging cabin.It is left with heating air-flow
Oil cooler is by passing through air duct.Nuria Llamas CastRo, which is disclosed, assembles air inlet for the aircraft propulsion of deicing
Lip circuit (patent No.: 2016/0114898 Al of US).It includes a circular cabin, annular air inlet lip, aviation hair
Motivation.Engine power component further includes the engine lubrication turbine and inlet lip deicing circuit of a circuit element,
It is characterized in that the ice-melt circuit includes a heat exchanger and circuit.Lubricating loop provides multiple deicing channels, it extends
To the secondary circuit of air inlet lip heat-transfer fluid.
Luo Zhenbing discloses a kind of for/frost/ice synthesis thermojet driver and the application of dehumidifying
(201510920386.2).Synthesis thermojet driver be made of synthesizing jet-flow excitor and heat source, synthesizing jet-flow excitor by
Cavity, vibrating membrane and outlet composition, cavity offer one or more outlets；Portion in the cavity is arranged in heat source.Luo Zhenbing is disclosed
A kind of broken de-icing method (201610841778.4) based on plasma attack jet stream.In the easy icing for having deicing demand object
In region, flushly mount with Plasma Actuator and icing detector with the easy ice field object plane, Plasma Actuator and
Icing detector is connect with a controller, when icing detector, which detects the easy ice field object plane, to freeze, control
Device control be located at the easy ice field at Plasma Actuator work, and control Plasma Actuator discharge power,
Frequency and working time, using the periodic high temperature high dynamic pressure jet impulse ice sheet fast vibration deformation fracture that it is generated, even
Ice sheet is directly smashed and melted, ice-breaking is carried out.Luo Zhenbing discloses the conjunction of the zero energy consumption zero mass based on hypersonic speed flow energy utilization
At fluidic device (201410324990.4).The zero energy consumption zero mass synthesizing jet-flow device include gas source unit, power supply unit and
Synthesizing jet-flow excitor, gas source unit include cavity, air collector and solenoid valve windward, power supply unit include thermo-electric conversion module,
Input circuit, high voltage power supply, hvdc circuit and high-voltage pulse circuit；Synthesizing jet-flow excitor includes driver shell, is swashed
It encourages and is equipped with main discharge electrode in device shell, light a fire positive and igniting cathode, driver shell are equipped with air source inlet and at least one
A jet exit, main discharge electrode, igniting anode and igniting cathode are connected with power supply unit respectively, air source inlet and solenoid valve it
Between pass through steam line be connected to.
Current aero-engine lip is anti-/ and deicing scheme is largely Jet stream array impact aero-engine lip inner cavity
Surface.The heat convection of stagnation center, aero-engine lip and jet stream reaches maximum.Hereafter, jet stream is along jet stream along hair
The flowing of motivation air inlet lip inner surface, jet stream liquidate with adjacent jets reaching center position, fluid forward movement by
It is moved upwards after to obstruction.The jet stream effect of liquidating is so that the boundary layer of the position jet stream thickens, fluid and engine charge lip
The heat exchange property on surface deteriorates.
Synthesizing jet-flow be caused by the cycle movement of inside cavity diaphragm intracavity gas alternately spray or sucking and outside
A kind of pattern that portion flow field is formed, realizes that the device of synthesizing jet-flow is exactly synthesizing jet-flow exciter.Synthesizing jet-flow is due to tool
There is the notable feature of zero-net-mass-flux jet, it possesses vast potential for future development in Active Flow Control and enhanced heat exchange technology.
Summary of the invention
In order to overcome the problems, such as existing aero-engine lip it is anti-/ deicing when adjacent jets middle position heat transfer deterioration,
The invention proposes a kind of devices that the aero-engine using synthesizing jet-flow auxiliary continuity jet stream is anti-icing, to improve the phase
The problem of adjacent jet stream middle position jet stream and aero-engine lip wall surface heat transfer deterioration, promotes its anti-/ deicing effect.This hair
It is bright periodic synthesizing jet-flow to be utilized adjacent jets middle position is impacted, the boundary layer of the jet stream position is weakened,
Enhance the heat convection of jet stream Yu aero-engine lip wall surface.
To achieve the above object, the technical solution adopted by the present invention are as follows:
A kind of aero-engine anti-icing equipment using synthesizing jet-flow auxiliary continuity jet stream, including engine charge lip 1, are penetrated
Array 2 and synthesizing jet-flow exciter 3 are flowed, the engine charge lip 1 is an arcwall face, and arcwall face forms a cavity,
Several Jet stream arrays 2 are successively set on cavity inside, are provided with synthesizing jet-flow exciter between two adjacent Jet stream arrays 2
3, the synthesizing jet-flow exciter 3 is a hollow cavity, and movement diaphragm 31 and exciter aperture 34 are provided on cavity,
Movement diaphragm 31 connects with driver 35, and the Jet stream array 2 and exciter aperture 34 are directed to engine charge lip 1；It drives
The dynamic driving of device 35 movement 31 reciprocal transformation of diaphragm, drives the periodical volume of cavity to change, gases cycle sexual intercourse alternately self-excitation
Device aperture 34 is into or out.
Further, several Jet stream arrays 2 are equally spaced, and several Jet stream arrays 2 and synthesizing jet-flow exciter 3
It is generally aligned in the same plane.
Further, the Jet stream array 2 and synthesizing jet-flow exciter 3 are located at 1 arcwall face both ends of engine charge lip
Connection plane middle vertical plane on, and the middle vertical plane and arcwall face both ends are non-intersecting.
Further, the synthesizing jet-flow exciter 3 includes movement diaphragm 31, exciter inner cavity 32, exciter cavity wall
Face 33, exciter aperture 34 and driver 35, one end of cavity are provided with exciter aperture 34, opposite with exciter aperture 34
One end is provided with movement diaphragm 31, and the side wall of the cavity is exciter cavity wall surface 33.
Further, distance of the exciter aperture 34 apart from 1 surface of engine charge lip is exciter aperture 34
8-12 times of diameter.
Further, the synthesizing jet-flow impact adjacent continuous jet stream that the synthesizing jet-flow exciter 3 generates liquidates position
11, adjacent continuous jet stream liquidates position 11 as the extended line of synthesizing jet-flow exciter 3 and crossing for engine charge lip 1
Place.
Further, the movement diaphragm 31 is that the metal film of changeability pastes piezoelectric ceramic piece.
Further, the driver 35 generates periodic voltage, and driving movement diaphragm 31 deforms, toward the fortune of renaturation
Dynamic, the movement diaphragm 31 of reciprocating motion changes the periodical volume of exciter inner cavity 32, the gas near exciter aperture 34
Body is alternatively entered or is discharged, and forms synthesizing jet-flow in 34 downstream of exciter aperture.
Further, the bore in the exciter aperture 34 is less than the internal diameter of cavity.
Further, the size of the movement diaphragm 31 is greater than the bore in exciter aperture 34, moves the size of diaphragm 31
Less than the internal diameter of cavity.
Compared with prior art, the invention has the following advantages:
The periodic synthesizing jet-flow that synthesizing jet-flow exciter is formed in the present invention is constantly sheared with surrounding air, is formed a series of
Collar vortex, impact target plate surface, enhance the heat convection of jet stream Yu engine charge lip surfaces；Periodically synthesis is penetrated
Stream improves between Jet stream array since the adjacent continuous jet stream boundary layer at position that liquidates thickens and causes fluid and engine
The problem of air inlet lip heat convection weakens；Therefore, so that using aero-engine lip it is anti-/ deicing effect is improved.
Detailed description of the invention
Fig. 1 is the principle of the present invention figure；
Fig. 2 is the rearview of device in the present invention；
Fig. 3 is the side view of device in the present invention；
Fig. 4 is the main view of device in the present invention；
Fig. 5 is 45 ° of views of device in the present invention；
Fig. 6 is the structural schematic diagram of synthesizing jet-flow exciter in the present invention；
Fig. 7 is the schematic diagram of device in the present invention；
Fig. 8 is that synthesizing jet-flow exciter existstThe working principle diagram at=0T moment；
Fig. 9 is that synthesizing jet-flow exciter existstThe working principle diagram at ∈ (0,1/4T) moment；
Figure 10 is that synthesizing jet-flow exciter existstThe working principle diagram at ∈ (1/4T, 1/2T) moment；
Figure 11 is that synthesizing jet-flow exciter existstThe working principle diagram at ∈ (1/2T, 3/4T) moment；
Figure 12 is that synthesizing jet-flow exciter existstThe working principle diagram at ∈ (3/4T, 1T) moment；
In figure: 1- engine charge lip, 2- Jet stream array, 3- synthesizing jet-flow exciter, 11- adjacent continuous jet stream liquidate position
It sets, 31- moves diaphragm, 32- exciter inner cavity, 33- exciter cavity wall surface, 34- exciter aperture, 35- driver.
Specific embodiment
Below with reference to embodiment, the present invention will be further explained.
As shown in figures 1 to 6, a kind of aero-engine anti-icing equipment using synthesizing jet-flow auxiliary continuity jet stream, including hair
Motivation air inlet lip 1, Jet stream array 2 and synthesizing jet-flow exciter 3, the engine charge lip 1 are an arcwall face, arc
Face forms a cavity, several Jet stream arrays 2 are successively set on cavity inside, are arranged between two adjacent Jet stream arrays 2
There is synthesizing jet-flow exciter 3, the synthesizing jet-flow exciter 3 is a hollow cavity, and movement diaphragm is provided on cavity
31 and exciter aperture 34, movement diaphragm 31 connects with driver 35, and the Jet stream array 2 and exciter aperture 34 are directed to send out
Motivation air inlet lip 1；Driving movement 31 reciprocal transformation of diaphragm of driver 35, drives the periodical volume of cavity to change, gas week
Alternately self-excitation device aperture 34 is into or out for phase sexual intercourse.
Several Jet stream arrays 2 are equally spaced, and several Jet stream arrays 2 and synthesizing jet-flow exciter 3 are positioned at same
Plane, the Jet stream array 2 and synthesizing jet-flow exciter 3 are located in the joint face at 1 arcwall face both ends of engine charge lip
On vertical plane, and the middle vertical plane and arcwall face both ends are non-intersecting.The synthesizing jet-flow that the synthesizing jet-flow exciter 3 generates impacts phase
Adjacent continuity jet stream liquidates position 11, and adjacent continuous jet stream liquidates the extended line and hair that position 11 is synthesizing jet-flow exciter 3
The intersection of motivation air inlet lip 1.
The synthesizing jet-flow exciter 3 includes movement diaphragm 31, exciter inner cavity 32, exciter cavity wall surface 33, excitation
Device aperture 34 and driver 35, one end of cavity are provided with exciter aperture 34, one end setting opposite with exciter aperture 34
There is movement diaphragm 31, the side wall of the cavity is exciter cavity wall surface 33.The exciter aperture 34 is apart from engine charge
The distance on 1 surface of lip is 8-12 times of 34 diameter of exciter aperture；In particular, the periodicity that synthesizing jet-flow exciter is formed
Synthesizing jet-flow constantly with surrounding air shear, form a series of collar vortex, impact target plate surface, enhance jet stream and start
The heat convection on machine air inlet lip surface, periodic synthesizing jet-flow improve between Jet stream array due to adjacent continuous jet stream
It liquidates the problem of thickeing and fluid and engine charge lip heat convection is caused to weaken of boundary layer at position；Therefore, make to get profit
With aero-engine lip it is anti-/ deicing effect is improved.
The movement diaphragm 31 is that the metal film of changeability pastes piezoelectric ceramic piece, and the driver 35 generates periodically
Voltage, driving movement diaphragm 31 deform, and toward the movement of renaturation, the movement diaphragm 31 of reciprocating motion makes the body of exciter inner cavity 32
Cyclically-varying is accumulated, the gas near exciter aperture 34 is alternatively entered or is discharged, and is formed and is closed in 34 downstream of exciter aperture
At jet stream.
The bore in the exciter aperture 34 is less than the internal diameter of cavity, and the size of the movement diaphragm 31 is greater than exciter hole
The size of the bore of mouth 34, movement diaphragm 31 is less than the internal diameter of cavity.
As illustrated in figures 1 and 7, the principle of the present invention is as follows, and engine charge lip 1 is presented arc and forms a cavity,
Jet stream array 2 and synthesizing jet-flow exciter 3 are all positioned in 1 cavity inside of engine charge lip, it is preferable that several jet stream battle arrays
Column 2 are equidistantly arranged to the cavity inside of the formation of engine charge lip 1, and perpendicular to 1 surface of engine charge lip, phase
Synthesizing jet-flow exciter 3 is set between adjacent Jet stream array 2；The gas that aero-engine high-pressure compressor end introduces passes through jet stream
The continuity jet stream formed after array 2, to 1 surface of engine charge lip, this to start the continuity jet impulse of high temperature
The temperature on 1 surface of machine air inlet lip increases and is maintained at 0 DEG C or more, and then achievees the effect that anti-icing.3 cloth of synthesizing jet-flow exciter
It sets between adjacent Jet stream array 2, distance of the exciter aperture 34 apart from 1 surface of engine charge lip is exciter aperture
8-12 times of 34 diameters, the synthesizing jet-flow impact adjacent continuous jet stream that synthesizing jet-flow exciter 3 generates liquidate position 11, the period
The synthesizing jet-flow of property destroys adjacent continuous jet stream and liquidates the boundary layer in 11 region of position, which increase fluid and engine into
The heat convection on 1 surface of gas lip, 1 surface of engine charge lip increases at the position；
In particular, from the continuity jet impulse that Jet stream array 2 flows out to 1 surface of engine charge lip, jet stream starts edge
1 surface flow of engine charge lip, jet stream liquidates after reaching center position with adjacent jets, and then transports upwards
Dynamic, adjacent continuous jet stream liquidates position 11 at the position, and jet stream is flowed up due to the effect of liquidating, and the boundary layer at this becomes
The heat exchange property on thickness, fluid and 1 surface of engine charge lip deteriorates, and the temperature on 1 surface of engine charge lip reduces.It is adjacent
Continuity jet stream, which liquidates, installs synthesizing jet-flow exciter 3 at 11 position of position, and synthesizing jet-flow exciter 3 generates periodic synthesis
Jet stream.The air that synthesizing jet-flow shears surrounding static on one side during flowing to engine charge 1 surface of lip forms a system
The collar vortex of column.Meanwhile after periodic synthesizing jet-flow reaches 1 surface of engine charge lip, the boundary layer of the position is weakened
Thickness.Therefore, jet stream and the heat convection on 1 surface of engine charge lip are enhanced.
As illustrated in figs. 8-12, synthesizing jet-flow swashs the working principle of 3 different moments of device, in particular, Fig. 8 swashs for synthesizing jet-flow
Hair device existstThe working principle diagram at=0T moment, Fig. 9 are that synthesizing jet-flow exciter existstThe working principle diagram at ∈ (0,1/4T) moment,
Figure 10 is that synthesizing jet-flow exciter existstThe working principle diagram at ∈ (1/4T, 1/2T) moment, Figure 11 are that synthesizing jet-flow exciter existstThe working principle diagram at ∈ (1/2T, 3/4T) moment, Figure 12 are that synthesizing jet-flow exciter existstThe work at ∈ (3/4T, 1T) moment
Make schematic diagram.Driver 5 gives the movement periodically variable voltage of diaphragm 31, makes to move diaphragm 31 along middle position dotted line periodicity
Movement,t=0T moment, driver 35 do not give movement 31 voltage of diaphragm, and movement diaphragm 31 is centrally located.At this point, excitation
32 volume of device inner cavity does not change, and the speed of jet stream is zero near exciter aperture 34；t∈ (0,1/4T) moment, driver
35 loads are positive in the voltage of movement diaphragm 31, and diaphragm is mobile to the position close to exciter aperture 34,32 body of exciter inner cavity
Product is reduced, and air pressure increases in exciter inner cavity 32.At this point, fluid sprays outward at exciter aperture 34, jet stream is formed；t∈ (1/
4T, 1/2T) moment, driver 35 is loaded to be negative in the voltage for moving diaphragm 31, position of the diaphragm to separate exciter aperture 34
Mobile, 32 volume of exciter inner cavity increases, and air pressure is reduced in exciter inner cavity 32.Gas near exciter aperture 34 is inhaled into
Inside exciter inner cavity 32；t∈ (1/2T, 3/4T) moment, the load of driver 35 are still negative in the voltage of movement diaphragm 31,
Movement diaphragm 31 continues the position movement to separate exciter aperture 34, and the gas near exciter aperture 34 is inhaled into exciter
Inside inner cavity 32, arrivet=3/4T moment, 32 volume of exciter inner cavity reach maximum；t∈ (3/4T, 1T) moment, driver 35 add
The voltage for being loaded in movement diaphragm 31 becomes just again, and diaphragm is mobile to the position close to exciter aperture 34, exciter inner cavity 32
Volume is reduced, and air pressure increases in exciter inner cavity 32, at this point, fluid sprays outward at exciter aperture 34, forms jet stream,t=T
Moment, movement diaphragm 31 are returned to middle position again；Diaphragm and so on moves, and 34 downstream of exciter aperture forms periodicity
Synthesizing jet-flow.Synthesizing jet-flow, constantly with the Air Entrainment of surrounding static, is formed a series of during downward downstream
Collar vortex.
Mechanism of the invention is as follows: the air introduced from aero-engine high-pressure compressor end is formed by Jet stream array 2
Continuity jet stream, continuity jet impulse to 1 surface of engine charge lip.Synthesizing jet-flow exciter 3 is alternately arranged at jet stream
Between array 2.The synthesizing jet-flow impact adjacent continuous jet stream generated using synthesizing jet-flow exciter 3 is liquidated position 11, the period
The synthesizing jet-flow of property weakens adjacent continuous jet stream and liquidates bound thickness at position 11.Jet stream and 1 table of engine charge lip
The heat convection in face is enhanced, and then the temperature on 1 surface of engine charge lip is improved.
The above is only a preferred embodiment of the present invention, it should be pointed out that: for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (10)
1. a kind of aero-engine anti-icing equipment using synthesizing jet-flow auxiliary continuity jet stream, which is characterized in that including starting
Machine air inlet lip (1), Jet stream array (2) and synthesizing jet-flow exciter (3), the engine charge lip (1) are an arc
Face, arcwall face form a cavity, several Jet stream arrays (2) are successively set on cavity inside, two adjacent Jet stream arrays
(2) it is provided between synthesizing jet-flow exciter (3), the synthesizing jet-flow exciter (3) is a hollow cavity, and on cavity
It is provided with movement diaphragm (31) and exciter aperture (34), movement diaphragm (31) connects with driver (35), the Jet stream array
(2) and exciter aperture (34) are directed to engine charge lip (1)；Driver (35) driving movement diaphragm (31) back and forth becomes
Shape drives the periodical volume of cavity to change, and gases cycle sexual intercourse is alternately self-excitation device aperture (34) into or out.
2. the aero-engine anti-icing equipment according to claim 1 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: several Jet stream arrays (2) are equally spaced, and several Jet stream arrays (2) and synthesizing jet-flow exciter (3) are located at
Same plane.
3. the aero-engine anti-icing equipment according to claim 2 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: the Jet stream array (2) and synthesizing jet-flow exciter (3) are located at the company at engine charge lip (1) arcwall face both ends
It connects on the middle vertical plane of plane, and the middle vertical plane and arcwall face both ends are non-intersecting.
4. the aero-engine anti-icing equipment according to claim 1 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: the synthesizing jet-flow exciter (3) includes movement diaphragm (31), exciter inner cavity (32), exciter cavity wall surface
(33), exciter aperture (34) and driver (35), one end of cavity are provided with exciter aperture (34), with exciter aperture
(34) opposite one end is provided with movement diaphragm (31), and the side wall of the cavity is exciter cavity wall surface (33).
5. the aero-engine anti-icing equipment according to claim 1 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: distance of the exciter aperture (34) apart from engine charge lip (1) surface is exciter aperture (34) diameter
8-12 times.
6. the aero-engine anti-icing equipment according to claim 1 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: the synthesizing jet-flow impact adjacent continuous jet stream that the synthesizing jet-flow exciter (3) generates liquidates position (11), adjacent
Continuity jet stream liquidates position (11) as the extended line of synthesizing jet-flow exciter (3) and the intersection of engine charge lip (1).
7. the aero-engine anti-icing equipment according to claim 1 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: movement diaphragm (31) is that the metal film of changeability pastes piezoelectric ceramic piece.
8. the aero-engine anti-icing equipment according to claim 1 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: the driver (35) generates periodic voltage, and driving movement diaphragm (31) deforms, toward the movement of renaturation, back and forth
The movement diaphragm (31) of movement changes the periodical volume of exciter inner cavity (32), the gas of exciter aperture (34) nearby
It alternatively enters or is discharged, form synthesizing jet-flow in exciter aperture (34) downstream.
9. the aero-engine anti-icing equipment according to claim 1 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: the bore of the exciter aperture (34) is less than the internal diameter of cavity.
10. the aero-engine anti-icing equipment according to claim 1 using synthesizing jet-flow auxiliary continuity jet stream, special
Sign is: the size of movement diaphragm (31) is greater than the bore of exciter aperture (34), and the size of movement diaphragm (31) is less than
The internal diameter of cavity.
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| CN201910283212.8A CN110043369A (en) | 2019-04-10 | 2019-04-10 | A kind of aero-engine anti-icing equipment using synthesizing jet-flow auxiliary continuity jet stream |
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| CN201910283212.8A CN110043369A (en) | 2019-04-10 | 2019-04-10 | A kind of aero-engine anti-icing equipment using synthesizing jet-flow auxiliary continuity jet stream |
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| CN110043369A true CN110043369A (en) | 2019-07-23 |
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| CN201910283212.8A Pending CN110043369A (en) | 2019-04-10 | 2019-04-10 | A kind of aero-engine anti-icing equipment using synthesizing jet-flow auxiliary continuity jet stream |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111412609A (en) * | 2020-03-31 | 2020-07-14 | 广东美的制冷设备有限公司 | Non-wind-sensing air supply method based on air conditioner, storage medium and device |
| CN117493744A (en) * | 2023-12-04 | 2024-02-02 | 北京航空航天大学 | Determination method for ice crystal particle convection heat exchange experiment association type |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060050482A1 (en) * | 2004-09-03 | 2006-03-09 | Ari Glezer | Apparatus and method for enhanced heat transfer |
| US20100076614A1 (en) * | 2009-11-05 | 2010-03-25 | Jacob Johannes Nies | Systems and method for operating a wind turbine having active flow control |
| CN105523186A (en) * | 2015-12-11 | 2016-04-27 | 中国人民解放军国防科学技术大学 | Synthetic thermal jet exciter for removing damp/frost/ice and application thereof |
| CN105691620A (en) * | 2016-01-20 | 2016-06-22 | 南京师范大学 | Heat pipe and ultrasonic wave combined ice preventing and removing device and method utilizing waste heat of aircraft engine |
| CN106150988A (en) * | 2015-05-14 | 2016-11-23 | 波音公司 | The piezo-activator optimized for synthetic jet actuator |
| CN209925093U (en) * | 2019-04-10 | 2020-01-10 | 南京航空航天大学 | Aero-engine anti-icing device utilizing synthetic jet flow to assist continuous jet flow |
-
2019
- 2019-04-10 CN CN201910283212.8A patent/CN110043369A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060050482A1 (en) * | 2004-09-03 | 2006-03-09 | Ari Glezer | Apparatus and method for enhanced heat transfer |
| US20100076614A1 (en) * | 2009-11-05 | 2010-03-25 | Jacob Johannes Nies | Systems and method for operating a wind turbine having active flow control |
| CN106150988A (en) * | 2015-05-14 | 2016-11-23 | 波音公司 | The piezo-activator optimized for synthetic jet actuator |
| CN105523186A (en) * | 2015-12-11 | 2016-04-27 | 中国人民解放军国防科学技术大学 | Synthetic thermal jet exciter for removing damp/frost/ice and application thereof |
| CN105691620A (en) * | 2016-01-20 | 2016-06-22 | 南京师范大学 | Heat pipe and ultrasonic wave combined ice preventing and removing device and method utilizing waste heat of aircraft engine |
| CN209925093U (en) * | 2019-04-10 | 2020-01-10 | 南京航空航天大学 | Aero-engine anti-icing device utilizing synthetic jet flow to assist continuous jet flow |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111412609A (en) * | 2020-03-31 | 2020-07-14 | 广东美的制冷设备有限公司 | Non-wind-sensing air supply method based on air conditioner, storage medium and device |
| CN117493744A (en) * | 2023-12-04 | 2024-02-02 | 北京航空航天大学 | Determination method for ice crystal particle convection heat exchange experiment association type |
| CN117493744B (en) * | 2023-12-04 | 2024-05-10 | 北京航空航天大学 | Determination method for ice crystal particle convection heat exchange experiment association type |
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