CN101131123B - Multifunctional air inlet of turbine engine - Google Patents
Multifunctional air inlet of turbine engine Download PDFInfo
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- CN101131123B CN101131123B CN2007101526669A CN200710152666A CN101131123B CN 101131123 B CN101131123 B CN 101131123B CN 2007101526669 A CN2007101526669 A CN 2007101526669A CN 200710152666 A CN200710152666 A CN 200710152666A CN 101131123 B CN101131123 B CN 101131123B
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- Prior art keywords
- suction port
- air
- turbogenerator
- power
- district
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
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- 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
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- 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
-
- 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
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
-
- 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
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
- F02C7/052—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
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- 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
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
- F02C7/055—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
- F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64D2033/0246—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising particle separators
Abstract
The present invention relates to a multifunctional air inlet (2) of the aircraft turbine engine (1), which includes a power air inlet (3) that can be closed by the closing device (6) arranged at the upstream side of the filtering air inlet (4), and a multi-path of a particle filter (9) is arranged at the top part of the periphery of the filtering air inlet (4). The distinctive feature of the multifunctional air inlet (2) is that the entering air is provided by a grille (7) which lies at the top side of the power air inlet (3).
Description
Technical field
The present invention relates to the multifunctional air inlet of aircraft turbogenerator, for example, be used for rotorcraft.
Background technique
When particularly rotorcraft moved under various environment and extreme case, one or more turbogenerators of rotorcraft just should be protected, and enabled to stand so abominable situation.
At first be when taking off, rotorcraft advances and the air-flow of lifting rotor can be kicked up ground dust and gravel.Therefore protect the suction port of one or more turbogenerators of rotorcraft, make motor not suck those sand dusts and just seem very important.Must eliminate the rotorcraft turbogenerator in addition and suck the sand dust that suspends in the air.If when especially rotorcraft is full of regional use of dust storm of sand dust in air, just more will eliminate.
Secondly, rotorcraft may fly under the so-called situation that frost occurs.In such flight course, frost can part even is stopped up the air intlet of rotorcraft turbogenerator fully, this means that the turbogenerator output power reduces greatly even do not had fully.Equally, ice crystal possibly sucked by turbogenerator, and these ice crystals can seriously disturb the operation of turbogenerator or with its damage.
Therefore; In order in particular cases to fly at these, for example in the atmosphere that is full of particulate or frost, fly, will protect one or more turbogenerators of aircraft; Particularly protect their suction port, to guarantee the high subthreshold of each item performance of turbogenerator.
The Flight Vehicle Design personnel have designed the device that is used to protect the turbogenerator suction port, suck particulate to prevent turbogenerator.
We have known to be respectively applied for and have prevented that turbogenerator suction port ice crystal from piling up and preventing to suck first and second kinds of devices of particulate that second kind of device is called sand control by the Professional visitors and filters.
Yet, normally inconsistent between existing first and second kinds of devices.An aircraft can not only be prevented frost but also prevent sand grains simultaneously, and this can cause tangible use difficulty.
We have recognized through patent document FR2250671 a kind ofly can both prevent simultaneously that turbogenerator from sucking particulate, can under frost occurs condition, fly again, and not reduce the multifunctional air inlet of turbogenerator main performance.
This multifunctional air inlet comprises a radiation-like annular power suction port, and this power suction port can be closed through an axially movable tip body of ability.In addition, multifunctional air inlet also has a cylindric filtration suction port, is positioned at the downstream of power suction port, and downstream are filtered suction port a multichannel part that leans on the acting particulate filter of air-flow excircle inertia is housed for air-flow direction.
When frost prevention or sand control function are in when activating, tip body is closed the power suction port, and whole air that turbogenerator sucked all pass through filtering air inlet, particularly the particulate filter suction port.
Equipped spiral ramp on the particulate filter, it becomes vorticla motion with air disturbance before getting into pipeline, and separator is equipped with in the outlet of pipeline, and separator is concentric with pipeline, but diameter is littler than pipe diameter.
By the vorticla motion that causes by spiral ramp, cyclone whirlpool phenomenon appears in the ingress of each particulate filter.So ice crystal is just rolled up to the periphery of vortex and finally filtering the ingress deposition, more precisely deposits at the outer lug boss place of each particulate filter, and can not block filter.Like this, filter inlet and just stopped that ice crystal enters in the turbogenerator.
In the sand control operating mode, along with the motion of vortex air, sand grains is thrown on the inner-walls of duct, therefore can not enter in the separator into the final air feed of turbogenerator.Other has a blower to extract those out from the outside can not pass separator and the particulate of being thrown inner-walls of duct.
This device can meet the demands basically, but also is not best on the whole.
Because for aircraft with double engines, when one of them turbogenerator breaks down, for guaranteeing flight safety, the pilot will activate the state of emergency of turbogenerator operation, obtain interim surplus power from the turbogenerator of proper functioning.
Yet if sand control or frost prevention pattern are in when activating, the power suction port tip body of the turbogenerator of proper functioning remains on closed condition.Therefore, the power suction port is to be in unactivatedly, it is contemplated that, the turbogenerator of proper functioning and can not fully provide required power because the air quantity that single filtering air inlet provides reduces.
Can infer, the pilot can determine to open the power suction port simply, so that turbogenerator provides required power.Yet if still be in the situation that frost is arranged this moment, another has occurred with regard to problem so.In fact, open the power suction port through moving of tip body and will produce serious consequence, because turbogenerator begins to suck ice crystal.Moreover nowadays this operation is forbidden by aircraft flight license issuance department at present.
Therefore; Under the situation that a turbogenerator of aircraft with double engines breaks down; Send required power in order to ensure another turbogenerator at emergency condition; The artificer improves turbogenerator, has used an air inlet that restriction is arranged at the filtration suction port place of multifunctional air inlet, so that turbogenerator provides required power.
We understand fully, and with regard to the cost of aircraft, volume or also have such as with regard to the weight, so improving not is what have no effect.
Summary of the invention
The objective of the invention is to propose a kind of multifunctional air inlet that can break away from aforementioned limitations, particularly it can allow aircraft with double engines to fly having under the condition of ice crystal, and need not carry out bigger remodeling to its turbogenerator.
According to the present invention, the multifunctional air inlet of aircraft turbogenerator comprises a power suction port, and it points to the dynamic axis of flow that almost is parallel to the turbogenerator main axis, and by closing along the shutoff device that at least one direction moves.Shutoff device is arranged in before the air intake filter, and the multichannel part of a particulate filter is equipped with in the excircle top of air intake filter.The distinguishing feature of multifunctional air inlet is that a grid that is positioned at power suction port top is arranged.This grid allows not close when needed the power suction port.
Filter suction port and be preferably loop configuration, each particulate filter all passes annular table abutment.
Under normal circumstances, turbogenerator for the direction of air-flow, filters the downstream that suction port is positioned at the power suction port by power suction port and filtration suction port air feed.
First distortion according to embodiment; The power suction port is the suction port that points to the turbogenerator main axis; And filter suction port is the suction port that the certain size circular arc is arranged, and the pedestal along filtering suction port annular excircle of all particulate filters is arranged in the circular arc place.
Second distortion according to embodiment; Turbogenerator has a horizontal gas tube orifice perpendicular to main axis; Multifunctional air inlet has a conduit, and conduit is connected to the horizontal gas tube orifice of turbogenerator through a bend pipe, and conduit is with to filter suction port air fed by the power suction port.
Laterally gas tube orifice is pointed to almost the suction axis perpendicular to main axis, and the folded angle of the suction axis of the dynamic axis of flow of power suction port and gas tube orifice is between the angle of X and Y.
Thereby embodiment's first distortion is very suitable for having the turbogenerator of arranging the power gas tube orifice along main axis, and embodiment's second distortion is especially more effective for the turbogenerator that has horizontal gas tube orifice.
Under extreme flying condition, frosting just or be full of under the air ambient of particulate, shutoff device has for example cut out the radiation-like suction port of ring with the power inlet close, is to suck disadvantageous particle for fear of turbogenerator, ice crystal or particulate.Turbogenerator can only be supplied with by passing the air that filters suction port.
Yet; If aircraft comprises at least two turbogenerators, and if one of them turbogenerator break down, so; The program that will explain according to hereinafter; Shutoff device (just for example a tip body or a venetian blind move along at least one direction) with the power air inlet open, makes turbogenerator still remain on the running state of correct air feed, thereby required power is provided.The realization of this operation is that grid stops that ice crystal enters into turbogenerator because the existence of a grid is arranged fully.
We notice the bend pipe of multifunctional air inlet, are used by second embodiment of the invention, and it has unexpectedly participated in the frost prevention protection of turbogenerator.In fact, if there is the part ice crystal to pass the obstacle that grid forms, these ice crystals will be deposited on bend pipe and do not sucked by turbogenerator.
In order to make sand grains deposition effect maximization, when the power suction port contains an air and gets in it the air of process through the district, grid is located in the upstream position of this air through the district, so that protect air to pass through the district well, has also just protected turbogenerator.
Likewise, according to first distortion of first and second embodiments, grid is a concave surface, and its concave surface passes through the district towards air.
According to second distortion of first and second embodiments, comprise that with the compatible grid of previous distortion air first passes through section through section and air second.First shape through section can be ball cover shape, and through the district, on the contrary, second passes through section passes through the district round air to its concave surface towards air.
It is because the progradation of aircraft through section that air passes first, and passes second through the section result of turbogenerator getter action just.
Best, there is one to be divided into two the first largest interval section through section with first, it is positioned at the top of the second largest interval section, and the second largest interval section is divided into two with air through zoning.
In addition, air preferably is arranged in the inside of grid through the district.
Like this, grid has just stopped that ice crystal enters in the turbogenerator.Because ice crystal is deposited on the grid, and can't pass grid.Otherwise, consider the characteristics of grid, first perhaps might be deposited ice crystal through section partly stops up, but second be this situation through Duan Buhui, it bears the minimum air feed to turbogenerator.
At last, in order to optimize antifrost effect, grid is made a wire netting, its mesh is square, and the length of side preferably 4.75 millimeters, comes heater grid to guarantee defrosting and anti-freezing through turn-on current between 3 millimeters to 7 millimeters.
The present invention also is useful on the program of aircraft with double engines, is used under the state of emergency that a turbogenerator breaks down, and makes another turbogenerator operation of aircraft.Each turbogenerator all has a multifunctional air inlet; Multifunctional air inlet comprises a power suction port; The power suction port is closed by shutoff device, when aircraft in that frost occurs or atmosphere when being full of extreme environment under the particulate situation and using, shutoff device is with the power inlet close.
The effect of this program shows in the implementation process in order of following phases:
A) activate the state of emergency,
B) the affirmation shutoff device does not cut out the power suction port, and
C) as b) stage judges that the power suction port when closing, operates shutoff device, makes shutoff device no longer close the power suction port.
Therefore, when aircraft with double engines, rotorcraft for example, when under foregoing extreme condition, flying, the shutoff device of each multifunctional air inlet all cuts out power suction port separately.
Yet if one of them turbogenerator breaks down, the driver just activates the state of emergency, so that keep the turbogenerator of normal operation that sufficient power is provided.Subsequently, because the power suction port contains an air through the district, air gets into the power suction port thus, shutoff device be activated and the air that discharges the power suction port through the district, so that turbogenerator is in correct air feed state.
In order under frost occurs situation, to open the power suction port, be preferably in air and protect the power suction port through a grid of disposed in district, make the compelled grid that passes earlier of the air that gets into the power suction port.
In addition, multifunctional air inlet has been equipped an inlet air filtration, is located in the downstream of power suction port; And inlet air filtration comprises the multichannel part of a particulate filter; Be used for the suction air of particulate from turbogenerator separated, and then these particulates be discharged to outside the filter element, after stage c) by blower; Preferably set a stage d) again, blower is broken off in this stage.
In fact, should limit the extraction of turbogenerator being used energy,, guarantee the Driving force and the lifting force of aircraft so that guarantee to provide essential power.The sediment outflow if good flight suits is closed the blower wisdom.
Likewise, at least one air extracts mouth and is set in the height of turbogenerator compressor, so that the circuit like heater is provided, after stage c), has set a stage e), in this stage air is extracted a mouthful disconnection.Ditto, preferably guarantee Driving force and lifting force rather than heater.Usually, break off all unnecessary turbogenerator energy extraction.
In a word, constantly in order not increase the weight of work load for aircraft flight person, in case a) implemented state of emergency activation in the stage, a) all afterwards stage is set just to have started the stage automatically urgent.Therefore, this process is that the pilot can be absorbed in other work automatically.
Description of drawings
The present invention and advantage thereof have some unlimited preferably qualitative embodiment's explanations also with showing in greater detail out in the diagram below among the figure, referring to accompanying drawing, be illustrated as:
-Fig. 1, according to the multifunctional air inlet sectional view of first embodiment of the invention,
-Fig. 2 filters suction port particulate filter sectional view, and
-Fig. 3, the explanation sectional view of multifunctional air inlet grid effect, and
-Fig. 4 is according to second embodiment's multifunctional air inlet schematic sectional view.
The a plurality of different elements that occur among each figure are only for reference and suppose.
Embodiment
Usually, Fig. 1 and Fig. 4 demonstrate azimuth axis, just length axes X and highly axis Z, and length axes X directed towards air stream direction, the saying at " upper reaches " and " downstream " is as reference.
Fig. 1 representes the sectional view according to first embodiment's multifunctional air inlet 2, and multifunctional air inlet is equipped with power suction port 3 and filtration suction port 4 of an annular radiation-like, and multifunctional air inlet is equipped on the turbogenerator 1.Therefore, along the length axes AX of turbogenerator, next can see power suction port 3 successively, filter suction port 4 is turbogenerator 1, and with regard to the direction of air flow, power suction port 3 is at the upper reaches of filtering suction port 4.
Therefore, power suction port 3 points to dynamic axis of flow AX2, overlaps and therefore be parallel to the length axes AX of turbogenerator 1 with it.
Fig. 2 expresses more accurately and passes the particulate filter 9 that filters suction port ring portion pedestal E.Particulate filter 9 has a pipe 92, and first end of pipe is enclosed within on the spiral ramp 91, and second end is enclosed within on the separator 93, and separator points to and filters suction port 4 so that to turbogenerator 1 air supply.The lower diameter of separator 93 is identical with the pipe diameter; And it is concentric with it; Particulate filter 9 contains the different first outlet S1 and the second outlet S2, and the pedestal that filters suction port is led in first outlet, and second export S2 and expressed by separator 93 and lead to the inside of filtering suction port 3.
Air-flow leaves spiral ramp 91 and passes particulate filter 9 and generated a vortex V.
Subsequently, when being full of particulate in the air, in the outlet of spiral ramp 91; Particulate is thrown to the inwall of pipe 92; And be discharged at this first outlet S1 by filter 9 and filter the suction port pedestal, if necessary, just emit particulate into the outside by blower shown in Figure 1 14.Therefore, the air that enters into separator 93 is pure, does not damage the risk of turbogenerator.
Likewise, under the situation that frost occurs, vortex V is deposited in pipe 92 convex platform 92 ' go up with the ice crystal particulate and can live pipe plug.Subsequently, the air that passes particulate filter 9 comprises the ice crystal of trace, does not disturb the risk of the operation of turbogenerator.
On the other hand, multifunctional air inlet 2 comprises the shutoff device 6 of power suction port 3, especially also comprises air through district 31, and air gets into multifunctional air inlet 2 thus.
Have, shutoff device 6 and its Effector 5 all are arranged in the inside of multifunctional air inlet 2 again, and be fixing by blade 15, for example, is fixed on power suction port 3 and/or is fixed on and filter suction port 4 places.
In addition, power suction port 3 is equipped with a grid 7, is located in the upper reaches of air through district 31, sucks ice crystal to stop turbogenerator 1.
Especially, grid 7 demonstrate first through section 71 concave surface towards the air of power suction port 3 through district 31, also demonstrate second and surround air through district 31 through section 72.Air is arranged in the grid 7 through distinguishing 31.
In addition, second shape through section 72 is that thickness is 3 to 4 centimetres annular, is fixed on power suction port 3, the first and is preferably ball cover shape through section 71.
In addition, first of grid 7 is divided into two the first largest interval L1 through section 71, be positioned at air through distinguish 31 be divided into two the second largest interval L2 the upper reaches.
Air passes first and is mainly caused by the aircraft propelling force through section 71, just sucks the result who forms negative pressure by turbogenerator and pass second through section 72.
When the aircraft situation that is used for that frost occurs or atmosphere were full of solid particle such as sand dust situation, Effector 5 just worked to shutoff device 6, makes its air of closing the power suction port through district 31.Turbogenerator 1 just can only obtain the air supply via filtering suction port 4.
Yet; With reference to program of the present invention, when aircraft comprises the turbogenerator 1 that multifunctional air inlet 2 all is housed more than two, and one of them turbogenerator is when breaking down; The pilot a) activates the state of emergency in the stage, at the turbogenerator that moves suitable power is provided so that make still.
Subsequently, affirmation shutoff device 6 does not cut out air through district 31.This stage is to be set by known method, for example, is sent the different electrical signals of operation aspect, shutoff device position by sensor.
At last,, closed air through district 31, so, just operated this shutoff device, made it no longer close air through district 31 through Effector 5 if can during stage b), confirm shutoff device 6 at stage c).
In fact, according to automatic Implementation Modes of the present invention, the activation of the state of emergency is to realize by the operating case on the instrument panel that is positioned at aircraft.This activates control gear is activated, and then confirms the position such as shutoff device 6 by sensor.Therefore, with regard to the operation of this position, control gear will sort according to the movement directive of shutoff device, so that discharging air is through the district.
Certainly other Implementation Modes also is admissible, for example, and the composite control apparatus that is undertaken by order.
Air makes turbogenerator be in the running state that can suck the greater amount air through opening of district, so that power demand to be provided.
This program can be set under extreme case, and especially the situation of frosting appears in grid 7.
Fig. 3 representes that grid 7 is when especially severe frost occurs situation is used.
The air-flow 10 that is full of frost contacts with grid 7, particularly contacts through section 71 with first of grid 7.Part ice crystal 11 can pass through to pile up on the section 71 first, and under the serious situation about accumulating of airborne frost, stops up probably.
But, second 72 directly contact with air-flow 10 through section, and this has benefited from the geometrical shape of grid 7, and first is arranged in through section 71 and contains white air-flow 10 and second through between sections 72.
Therefore, arrive second and only contain the frost of very small amount through the air of section 72, can regard dead section to second as through section, these air can be second through the section 72 a large amount of ice crystals of deposition and it is not blocked.
Because just under extreme case, second also can't be blocked by ice crystal through section 72 under worst case, just guaranteed that the air that will not contain frost supplies with turbogenerator, these air are along the path flows shown in the arrow 12.
Finally; Can also set stage d) and/or stage e), in this two stages, cut off the blower 14 that filters suction port 4 respectively and extract at the air that the turbine engine compressor height carries out; So that make turbogenerator send peak output, the lift and the propelling force of aircraft is provided.
Fig. 4 has shown the schematic sectional view of second embodiment of the invention.
Among this figure, turbogenerator 1 has been equipped a horizontal gas tube orifice 1, and it points to air-breathing axis AX1, perpendicular to the length axes AX of turbogenerator 1.
For can be to horizontal gas tube orifice 1 air inlet, multifunctional air inlet have comprised a conduit 20 and a bend pipe 21, and bend pipe 21 is connected to conduit 20 the horizontal gas tube orifice 1 of turbogenerator.
Although have above-mentioned angle, and bend pipe 21 can be connected to horizontal gas tube orifice 1 with conduit 20.
At last, identical with embodiment's first distortion, multifunctional air inlet has also been equipped grid 7, is arranged in the upper reaches of the air of power suction port 3 through district 31.
Especially, grid 7 have one towards air through the district 31 first through the section 71 and one surround first through the section 71 second through the section 72.
Therefore, embodiment's second distortion can be according to the present invention setting program.
To turbogenerator frost prevention protection to greatest extent, give the credit to the existence of bend pipe 21.In fact, if ice crystal has passed grid 7, especially passed its second and passed through section 72, these ice crystals just will be deposited on bend pipe 21 so, and can not enter in the turbogenerator 1.
Certainly, the present invention can receive the restriction of a large amount of distortion when it is set.Although the distortion to a plurality of embodiments is described, we know that it is impossible that detailed identification is all carried out in all distortion.In the scope of the invention, exist certainly to substitute certain equivalent way of describing method.
Claims (20)
1. the suction port (2) of an aircraft turbogenerator (1); It comprises a power suction port (3), and it points to dynamic axis of flow (AX2), is parallel to the length axes (AX) of this turbogenerator; Can close the power suction port by shutoff device (6); Shutoff device just is arranged in the upper reaches of filtering suction port (4), is equipping the multichannel part of a particulate filter (9) in the top of filtering suction port (4) excircle
It is characterized in that, have a grid (7), be positioned on the power suction port (3), and
Turbogenerator (1) has a horizontal gas tube orifice (1); Perpendicular to length axes (AX); Suction port comprises a conduit (20), and conduit is connected to by bend pipe (21) on the horizontal gas tube orifice (1 ') of turbogenerator (1), and conduit (20) is by power suction port (3) and filter suction port (4) air feed.
2. suction port as claimed in claim 1,
It is characterized in that power suction port (3) points to turbogenerator length axes (AX)
3. suction port as claimed in claim 1,
It is characterized in that laterally gas tube orifice (1 ') is pointed to and sucked axis (AX1), perpendicular to length axes (AX), there is an angle in dynamic axis of flow (AX2) with suction axis (AX1).
4. like claim 1 or 3 described suction ports,
It is characterized in that shutoff device is an alternate type venetian blind.
5. like the described suction port of any one claim among the claim 1-3,
It is characterized in that shutoff device (6) is a tip body that can move at least one direction.
6. suction port as claimed in claim 1,
It is characterized in that filtering suction port (4) is annular, each particulate filter (9) all passes the pedestal of annular.
7. suction port as claimed in claim 1,
It is characterized in that power suction port (3) is annular radiation-like.
8. suction port as claimed in claim 1,
It is characterized in that power suction port (3) comprises an air through district (31), air enters into power suction port (3) thus, and grid (7) is positioned at the upper reaches of air through district (31), so that protect this air through district (31).
9. suction port as claimed in claim 1,
It is characterized in that power suction port (3) comprises an air through district (31), air enters into power suction port (3) thus, and grid (7) is recessed into, and its concave surface passes through district (31) towards air.
10. suction port as claimed in claim 1,
It is characterized in that; Power suction port (3) comprises an air through district (31); Air enters into power suction port (3) thus; Grid (7) comprises first (71) and second (72) air through section, and first passes through section (71) passes through district (31) towards air, and second then surrounds air through section (72) passes through district (31).
11. suction port as claimed in claim 1,
It is characterized in that; Power suction port (3) comprises an air through district (31); Air enters into power suction port (3) thus; Grid (7) comprises first (71) and second (72) air through section, air pass first through section (71) lean on is the propelling of aircraft, and air to pass second be the air-breathing result of turbogenerator (1) through section (72).
12. like claim 10 or 11 described suction ports,
It is characterized in that, first through the section (71) be ball cover shape.
13. like claim 10 or 11 described suction ports,
It is characterized in that, said first through the section (71) two ends between the first largest interval section (L1) greater than said air through the district (31) two ends between the second largest interval section (L2).
14. suction port as claimed in claim 1,
It is characterized in that power suction port (3) comprises an air through district (31), air enters into power suction port (3) thus, and air is arranged in the inside of grid (7) through district (31).
15. suction port as claimed in claim 1,
It is characterized in that grid (7) is a wire netting, its mesh is square, and the length of side is between 3 millimeters to 7 millimeters.
16. suction port as claimed in claim 1,
It is characterized in that the heater grid through turn-on current (7).
17. method that is used for aircraft with double engines; Be used under the state of emergency that another turbogenerator (1) breaks down; Make one of them turbogenerator (1) operation of aircraft, each turbogenerator (1) all is equipped with the described suction port of any one claim (2) in the claim 1 to 17, and it comprises a power suction port (3); The power suction port is closed by shutoff device (6); When aircraft in that frost occurs or atmosphere when being full of extreme environment under the particulate situation and using, shutoff device is with the power inlet close
It is characterized in that implementing in order following phases:
A) activate the state of emergency,
B) affirmation shutoff device (6) does not cut out power suction port (3),
C) as b) stage judges that power suction port (3) when closing, operates shutoff device (6), makes shutoff device (6) no longer close power suction port (3),
Wherein turbogenerator (1) has a horizontal gas tube orifice (1); Perpendicular to length axes (AX); Suction port comprises a conduit (20); Conduit is connected to by bend pipe (21) on the horizontal gas tube orifice (1 ') of turbogenerator (1), and conduit (20) is by power suction port (3) and filter suction port (4) air feed.
18. method as claimed in claim 17,
It is characterized in that; Suction port (2) has been equipped a filtration suction port (4), is located in the downstream of power suction port (3), and filters the multichannel part that suction port (4) comprises a particulate filter (9); Be used for the suction air of particulate from turbogenerator separated; By blower (14) these particulates are discharged to outside the filter element (4) then, after stage c), have set a stage d), blower (14) is broken off in this stage.
19. like claim 17 or 18 described methods,
It is characterized in that it is the height at turbogenerator (1) compressor that at least one air extracts mouth, after stage c), has set a stage e), will extract a mouthful disconnection in this stage.
20. like claim 17 or 18 described methods,
It is characterized in that after a) implementing the state of emergency and activate in the stage, a) afterwards all stages are set just to have started the stage automatically.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0606598A FR2904046B1 (en) | 2006-07-19 | 2006-07-19 | VERSATILE AIR INTAKE OF A TURBOMOTOR. |
| FR06/06598 | 2006-07-19 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101131123A CN101131123A (en) | 2008-02-27 |
| CN101131123B true CN101131123B (en) | 2012-02-22 |
Family
ID=37781901
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2007101526669A Expired - Fee Related CN101131123B (en) | 2006-07-19 | 2007-07-05 | Multifunctional air inlet of turbine engine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN101131123B (en) |
| FR (1) | FR2904046B1 (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8133309B2 (en) * | 2008-07-16 | 2012-03-13 | General Electric Company | Turbomachine filter system having a drain with one-way valve |
| FR2951226B1 (en) * | 2009-10-14 | 2013-01-04 | Turbomeca | AIR FILTERING DEVICE INTO INTERNAL COMBUSTION ENGINE INPUT WITH VENTILATION MEANS |
| CN102705081B (en) * | 2012-05-23 | 2014-02-19 | 南京航空航天大学 | Binary hypersonic variable geometrical inlet channel, design method and work mode |
| US10265707B2 (en) | 2016-12-21 | 2019-04-23 | Hamilton Sundstrand Corporation | Motor cooling circuit with integrated FOD particle separator |
| CN107120193A (en) * | 2017-06-28 | 2017-09-01 | 李兵长 | A kind of helicopter engine intake duct and helicopter |
| CN110552787B (en) * | 2018-06-04 | 2023-09-15 | Bmc有限公司 | Air intake unit for an aircraft engine, provided with a filter and a bypass duct for the filter |
| FR3111947B1 (en) | 2020-06-30 | 2022-05-27 | Airbus Helicopters | self-cleaning media air filtration system and method for an aircraft engine |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3998048A (en) * | 1973-11-09 | 1976-12-21 | Societe Nationale Industrielle Aerospatiale | Ram air intakes of rotary-wing aircraft turbine engines |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB853646A (en) * | 1958-04-29 | 1960-11-09 | Westinghouse Electric Corp | Improvements in or relating to screens for the air intakes of aircraft engines |
| US3449891A (en) * | 1966-11-15 | 1969-06-17 | United Aircraft Corp | Engine inlet air particle separator |
| US3534548A (en) * | 1969-06-30 | 1970-10-20 | Avco Corp | Separator apparatus for engine air inlets |
| DE2213352A1 (en) * | 1972-03-20 | 1973-09-27 | Wilhelm Dr Ing Lepper | BIRD STRIKE PROTECTION ON PLANES |
| US6595742B2 (en) * | 2000-10-02 | 2003-07-22 | Westar Corporation | Aircraft engine air filter and method |
| FR2829529A3 (en) * | 2001-09-11 | 2003-03-14 | Mikaele Heafala | Protective intake grid for aircraft gas turbine has vertical and horizontal blades to prevent intake of foreign objects |
-
2006
- 2006-07-19 FR FR0606598A patent/FR2904046B1/en not_active Expired - Fee Related
-
2007
- 2007-07-05 CN CN2007101526669A patent/CN101131123B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3998048A (en) * | 1973-11-09 | 1976-12-21 | Societe Nationale Industrielle Aerospatiale | Ram air intakes of rotary-wing aircraft turbine engines |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2904046A1 (en) | 2008-01-25 |
| FR2904046B1 (en) | 2012-11-23 |
| CN101131123A (en) | 2008-02-27 |
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