CN106523158B - A kind of turboshaft engine inlet duct and operating method - Google Patents
A kind of turboshaft engine inlet duct and operating method Download PDFInfo
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- CN106523158B CN106523158B CN201610985841.1A CN201610985841A CN106523158B CN 106523158 B CN106523158 B CN 106523158B CN 201610985841 A CN201610985841 A CN 201610985841A CN 106523158 B CN106523158 B CN 106523158B
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- splitter
- ring
- air chamber
- shaped air
- centerbody
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Classifications
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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
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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
Abstract
The invention discloses a kind of turboshaft engine inlet duct and its operating method.This is that inlet duct includes centerbody component, splitter component and casing component.By the ring-shaped air chamber of an embedded flexible deformable in centerbody component, while a splitter being axially movable is designed, the type face of air chamber and the axial location of splitter are adjusted according to engine operating environments and working condition.When helicopter works in the unholiness air ambients such as dirt sand, by increasing air room height, the reach of splitter position, the gas handling system is set to be in high dirt sand separation efficiency mode；When helicopter is in cruising condition, air room height is reduced, and will be moved behind splitter position, the gas handling system is worked in high pneumatic efficiency pattern.Solve the problems, such as that tradition determines geometry gas handling system and can not take into account the efficient sediment outflow in low latitude and the high aeroperformance of cruise by the present invention.
Description
Technical field
The present invention relates to Aeroengine Design field, especially turboshaft engine gas handling system.
Background technology
China is one of country that desert area is maximum in the world, desert in an arcuate zone stretch in a connected line in northwest, North China and
On the soil in northeast, this arc desert belt north and south wide 600km, the long 4000km of thing, along with the Desert Area of Northern Tibet Plateau,
Desert area accounts for the 15.5% of area up to 1,490,000 square kilometres.Because helicopter landing is convenient, to airport environment requirement
It is relatively low, and the work such as military-civil rescue, supply, fire extinguishing in above-mentioned environment can be particularly suitable for hovering, however it is husky
The dirt sand ring border in desertization area is brought by the operating efficiency and service life of helicopter and its dynamical system (turboshaft engine)
Great harm.The dirt sand of suction hits the engine working-blade of rotation at a high speed, and the sandstone of bulky grain even can be direct
Blade is broken, short grained dirt sand then can form abrasion to the type face of blade, reduce compressor efficiency.More seriously,
Dirt sand can block cooling duct tiny in moving turbine blade, make turbo blade overtemperature or even burn.A part of dirt sand can also
Deposited in the inner surface of turbine wheel shaft, engine luggine value is uprushed.During the Vietnam War, U.S.'s CH-54 helicopters are in motor inlet
After installing easy screen pack additional, the average time between overhauls of its engine are by original 80h liftings to 800h.Start therefore, improving
The ability that machine gas handling system excludes foreign matter has extremely significant actively impact to the life-span of turboshaft engine, it is necessary in China
Used on turboshaft engine of new generation.
In the engineering practice of early stage, the widely used obstruction formula screen pack means dust-proof as sand control in gas handling system, but
It is that over time, the dirt sand and exotic being adhered on screen pack are cumulative, and motor inlet is easy to by these
Exotic blocks so that air-flow is difficult to be inhaled into engine, and flow resistance also dramatically increases, therefore filter needs often to carry out
Cleaning and maintenance, the manpower and materials of consumption are very big.Later, Boeing Co. in its T700 developed engine innovatively
A kind of new inlet duct is devised, by the way that runner is bent, sand grains is thrown away into runner using sand grains inertia big principle.This
The method pressure loss of kind desanding is smaller, can continuously exclude dirt sand, maintenance cost is also very low.But because its geometry is fixed, mesh
Preceding can only still be sought between multiple functions (air inlet, sediment outflow), different operating modes (take off, cruise) takes compromise, it is difficult to realizes full work
The Performance optimization of envelope curve.If using structure changes inlet duct, according to working environment and engine operating condition to gas handling system
Runner type face is adjusted, and switches to corresponding mode of operation, you can realizes that the performance of engine is in more excellent state all the time.Ripple
Sound company proposes a kind of design concept of structure changes turboshaft engine gas handling system, is closed at the bulge of centerbody by remembering
Gold and worm screw realize the deformation of bulge, so as to adapting to different working environments.This idea is skillfully constructed, but the difficulty realized
Degree is but very big, and the installation of endless screw apparatus adds very big complexity to system architecture, while the even property of circumferential asymmetry and close be present
Envelope problem, and the research of memorial alloy is still not reaching to the level of requirement at present, and therefore, this engineer applied contemplated is difficult
Degree is very big.
Therefore, it is necessary to which a kind of new technical scheme is to solve the above problems.
The content of the invention
To solve the above problems, the present invention provides a kind of turboshaft engine inlet duct.Discharge dirt sand ability can be taken into account
And air inlet performance, the gas handling system is in efficient operation all the time.
To reach above-mentioned purpose, the present invention can adopt the following technical scheme that：
A kind of turboshaft engine inlet duct, including centerbody component, splitter component and casing component；The centerbody
Component includes ring-shaped air chamber, after the centerbody leading portion extended forward from ring-shaped air chamber, the centerbody that is extended back from ring-shaped air chamber
Section；The casing component includes the outer barrel around centerbody component and the lip section positioned at outer barrel forward position；The splitter component bag
Include the splitter inner cylinder set around centerbody back segment, the splitter outer barrel around splitter inner cylinder, positioned at splitter inner cylinder and splitter outer barrel
Between splitter, driving splitter to ring-shaped air chamber direction advance or retreat away from ring-shaped air chamber drive device；The annular
The diameter of air chamber is more than the diameter of centerbody leading portion and centerbody back segment；Formed between the centerbody component and outer barrel first-class
Road；The second flow channel connected with first flow is formed between the splitter component and centerbody back segment.
Beneficial effect：
Relative to prior art, turboshaft engine inlet duct of the present invention adds deformable ring-shaped air chamber and can be axial
Mobile splitter component.The height for adjusting soft shell by carrying out inflation/deflation to air chamber, is adjusted removable by actuation mechanism
The axial location of ligulate splitter, so that the runner of this gas handling system matches local working environment.Work as aircraft, such as helicopter work
When making in the environment of unholiness dust-laden sand, by increasing the height of ring-shaped air chamber, and drive ligulate splitter to move forward, make first-class
Degree of crook in road, second flow channel becomes big and bending part and increased, and sand grains is thrown away into stream using sand grains inertia big principle
Road；When helicopter is cleaning runway landing and during high-performance cruise, is reducing soft shell height, and after driving ligulate splitter position
Move, make first flow, the degree of crook in second flow channel diminishes, bent portion tails off and forms unobstructed runner environment, to carry
The pneumatic efficiency of the high inlet duct.
Present invention also offers the technical scheme of the operating method of above-mentioned turboshaft engine inlet duct, is specially：
Including dirt sand separation efficiency mode and high pneumatic efficiency pattern；
When the turboshaft engine inlet duct is in dirt sand separation efficiency mode, splitter advances to ring-shaped air chamber direction to be made
Second flow channel part between splitter and ring-shaped air chamber narrows；And ring-shaped air chamber inflate and outwards expand, make ring-shaped air chamber and
First flow part between shell narrows；
When the turboshaft engine inlet duct is in high pneumatic efficiency pattern, splitter retreats makes splitter away from ring-shaped air chamber
Second flow channel part between ring-shaped air chamber broadens；And ring-shaped air chamber is deflated and to contract, makes ring-shaped air chamber and shell
Between first flow part broaden.
And it is further, turboshaft engine inlet duct provided by the invention can also use following technical scheme：
A kind of turboshaft engine inlet duct, including centerbody component, splitter component and casing component；
The centerbody component includes ring-shaped air chamber, extends forward from ring-shaped air chamber centerbody leading portion, from ring-shaped air chamber
The centerbody back segment to extend back；The casing component includes the outer barrel around centerbody component；The splitter component includes splitting
Point, driving splitter advance to ring-shaped air chamber direction or drive device of the retrogressing away from ring-shaped air chamber；The ring-shaped air chamber it is straight
Footpath is more than the diameter of centerbody leading portion and centerbody back segment；First flow is formed between the centerbody component and outer barrel, this
One runner is included in what is formed between first flow forward part, ring-shaped air chamber and the outer barrel formed between centerbody leading portion and outer barrel
Part in first flow；The second flow channel connected with first flow is formed between the splitter component and centerbody back segment；It is described
First flow forward part with the middle part of first flow point between form bending section, and in first flow part be equally bending and
It is communicated to second flow channel；The forward part of the second flow channel partly forms tubular after forming toroidal and second flow channel.
The technical problem and the beneficial effect of realization that the turboshaft engine inlet duct of second of technical scheme solves with
Technical scheme is identical in first, again by the height of increase ring-shaped air chamber, and drives ligulate splitter to move forward, makes first-class
Degree of crook in road, second flow channel becomes big and bending part and increased, and sand grains is thrown away into stream using sand grains inertia big principle
Road；When helicopter is cleaning runway landing and during high-performance cruise, is reducing soft shell height, and after driving ligulate splitter position
Move, make first flow, the degree of crook in second flow channel diminishes, bent portion tails off and forms unobstructed runner environment, to carry
The pneumatic efficiency of the high inlet duct.
Brief description of the drawings
Fig. 1 is the schematic cross-sectional view of turboshaft engine inlet duct in the present invention.
Fig. 2 is ring-shaped air chamber section view and aerating and exhaust device schematic diagram.
Fig. 3 is splitter component densification device and operation principle schematic cross-sectional view.
Embodiment
Refer to shown in Fig. 1, the invention discloses a kind of turboshaft engine inlet duct, including centerbody component, splitter
Component and casing component.Shell of the casing component as overall inlet duct, including outer barrel 13 around centerbody component and
Lemniscate lip section 12 positioned at the forward position of outer barrel 13.The centerbody component includes front fairing 1, ring-shaped air chamber 3, from annular gas
Centerbody leading portion 4 that room extends forward, the centerbody back segment 5 to be extended back from ring-shaped air chamber, connection and fixed outer cylinder 13 are with
The front support section 2 of heart body leading portion 4, rear support section 6, the pressure monitor 7 of connection and fixed outer cylinder 13 and centerbody back segment 5.Its
In, ring-shaped air chamber 3 uses monoblock type framework, using metal structure as framework, using centerbody leading portion 4 and centerbody back segment 5 to ring
Shape air chamber 3 carries out centering positioning.The splitter component includes splitter inner cylinder 8, splitter outer barrel 9, the splitter 10 that can be moved forward and backward, drive
Dynamic splitter 10 advances to the direction of ring-shaped air chamber 3 or drive device 11 of the retrogressing away from ring-shaped air chamber 3.The drive device 11 can
Using hydraulic transmission or linear stepping motor etc..The drive device 11 includes position feedback device, limiter etc..
The position feedback device can be with the axial location of Real-time Feedback splitter 10, and the limiter is limitation 10 axial dominant bit of splitter
The stopping means of shifting, cause engine flow too small or excessive to prevent the axial displacement of splitter 10 is excessive.Wherein, institute in Fig. 1 for another example
Show, the diameter of the ring-shaped air chamber 3 is more than the diameter of centerbody leading portion 4 and centerbody back segment 5.The centerbody component and outer barrel
Between formed first flow 31, before the first flow 31 is included in the first flow formed between centerbody leading portion 4 and outer barrel 13
Partly, part in the first flow formed between ring-shaped air chamber 3 and outer barrel 13.Between the splitter component and centerbody back segment 5
Form the second flow channel 32 connected with first flow 31.It is described because the diameter of the ring-shaped air chamber 3 is more than centerbody leading portion 4
First flow forward part with the middle part of first flow point between form bending section, and be more than again due to the diameter of ring-shaped air chamber 3
The diameter of heart body back segment 5, part is equally to bend and be communicated to second flow channel 32 in first flow；The second flow channel 32
Forward part partly forms tubular after forming toroidal and second flow channel 32.
The front end of the splitter 10 stretches out in splitter inner cylinder 8 all the time, and is back and forth transported between first position and the second place
Dynamic, when splitter 10 be located at first position, splitter is housed between splitter inner cylinder 8 and splitter outer barrel 9 and can not positioned in situ
The position being moved rearwards again；When splitter 10 is located at the second place, splitter 10 moves forward under the promotion forward of drive device 11
To close to the position of ring-shaped air chamber 3.And further CONSTRUCTED SPECIFICATION is that the lower surface of splitter 10 is outwardly cambered surface, and
The inner surface of splitter inner cylinder 8 is also cambered surface, and when splitter 10 is located at first position, and the lower surface of splitter is interior with splitter inner cylinder
Surface forms coherent cambered surface；Such design, which to work as, to be needed to improve the pneumatic efficiency of the inlet duct and be located at splitter 10
During first position, the lower surface of splitter and the inner surface of splitter inner cylinder, which form coherent cambered surface, makes type face in whole second flow channel
Linking up, it is small simply to hinder, and is advantageously implemented more smooth runner type face and improves pneumatic efficiency.The movement of the splitter 10 and ring
The expansion or shrinkage of shape air chamber influences to be that splitter 10 advances to the direction of ring-shaped air chamber 3 makes splitter caused by changing overall runner
Second flow channel part between 10 and ring-shaped air chamber 3 narrows；And ring-shaped air chamber 3 inflate and outwards expand, make ring-shaped air chamber 3 and
First flow part between outer barrel 13 narrows；Splitter 10 retreats to be made between splitter 10 and ring-shaped air chamber 3 away from ring-shaped air chamber 3
Second flow channel part broadens；And ring-shaped air chamber 3 is deflated and to contract, made first-class between ring-shaped air chamber 3 and outer barrel 13
Road part broadens.
Please in conjunction with shown in Fig. 2, the ring-shaped air chamber includes endless metal framework 14, is wrapped in the outside of metal framework 14
Deformable soft shell 15 and the deformable soft shell 15 of connection and to the aerating and exhaust device of the deformable inflation/deflation of soft shell 15
18.The deformable soft shell 15 is internally embedded aramid fiber or Metal wire material using specific rubber as matrix, passes through tune
Solar term pressure, the deflection of deformable soft shell 15 can be changed.Wherein, during unaerated, deformable soft shell 15 tightly wraps up
On endless metal framework 14.Part outwardly convex of the outer barrel on the outside of deformable soft shell 15, outer barrel can with outer barrel
First flow part between yielding flexibility shell 15 is bending, so at this after the deformable inflation of soft shell 15
The part of bending can substantially change flow channel shape.Every 90 ° of directions are provided with a passage 16 on the endless metal framework 14,
On corresponding position, deformable soft shell 15 is all provided with a charging connector, passes through five-way conduit 17 and the phase of air-charging and air-discharging system 18
Even, a valve 19 is set to be controlled aeration quantity on five-way conduit 17.When filling and (putting) gas system 18 and be operated, valve is opened
Door 19, four valves are filled and (put) gas to deformable soft shell 15 simultaneously, inflation/deflation process is fast and effeciently carried out, and
Circumferential homogeneous deformation can be ensured to greatest extent.The air-charging and air-discharging system 18 connects air exhauster and pressure respectively using threeway conduit 20
Mechanism of qi, compressor valve 21 and air exhauster valve 22 are set respectively on threeway conduit.During inflation, air exhauster valve 22 is closed,
Open compressor valve 21 and five-way conduit valve 19；During deflation, compressor valve 21 is closed, opens air exhauster valve 22 and five
Admittance tube valve 19.In order to avoid interference of the aerodynamic loading change to soft shell deformation characteristic, used air chamber in runner
It is higher to inflate pressure, typically should be more than 3 atmospheric pressure.
And it is further, the deformable soft shell 15 is provided with demarcation corresponding with air pressure, different demarcation difference
The atmospheric pressure value of corresponding different deformable soft shell.In the aerial real work of engine, by measuring pressure monitoring point 7
Pressure, and the data of above-mentioned demarcation are compared, and can obtain the practical distortion amount of deformable soft shell 15.
Refer to shown in Fig. 3, be the schematic cross-sectional view of splitter component densification device and operation principle.The splitter 10 with
A ring-shaped groove is provided with the contact surface of splitter inner cylinder 8 and splitter outer barrel 9, sealing air ring 23 is inlayed in groove, seals air ring 23
It is connected by conduit 24 with aerating and exhaust device 26, the structure of aerating and exhaust device 26 is identical with aerating and exhaust device 18.In order to in air ring
Pressure be controlled, a valve 25 is set on conduit 24.When drive device driving splitter 10 moves, valve 25 is opened,
Sealing air ring 23 is deflated using air-charging and air-discharging system 26；After splitter 10 moves to specified location, air-charging and air-discharging system 26 is utilized
Sealing air ring 23 is inflated, sealing air ring is expanded into largest deformation state, so as to play sealing effectiveness, now, closes valve
25, you can complete sealing.
The turboshaft engine inlet duct of present embodiment is applied in aircraft, especially helicopter.When specifically used
When in aircraft, a kind of operating method that can be provided is：
Including dirt sand separation efficiency mode and high pneumatic efficiency pattern；When helicopter works in the environment of unholiness dust-laden sand
When need to use dirt sand separation efficiency mode；Needed when helicopter is cleaning runway landing and high-performance cruise using high pneumatic effect
Rate pattern.
When the turboshaft engine inlet duct is in dirt sand separation efficiency mode, splitter 10 is to before the direction of ring-shaped air chamber 3
Enter to make the part of second flow channel 32 between splitter 10 and ring-shaped air chamber 3 to narrow；And ring-shaped air chamber 3 is inflated and outwards expanded, and is made
The part of first flow 31 between ring-shaped air chamber 3 and outer barrel 13 narrows.First flow 31 can so be made, in second flow channel 32
Degree of crook becomes big and bending part and increased, and sand grains is thrown away into runner using sand grains inertia big principle.
When the turboshaft engine inlet duct is in high pneumatic efficiency pattern, splitter 10 retreats to be made away from ring-shaped air chamber 3
The part of second flow channel 32 between splitter 10 and ring-shaped air chamber 3 broadens；And ring-shaped air chamber 3 is deflated and to contract, makes annular
The part of first flow 31 between air chamber 3 and outer barrel 13 broadens.First flow 31, the bending in second flow channel 32 can so be made
Degree diminishes, bent portion tails off and forms unobstructed runner environment, to improve the pneumatic efficiency of the inlet duct.
The method and approach of the present invention specific implementation technical scheme are a lot, and described above is only being preferable to carry out for the present invention
Mode.It should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention, also
Some improvements and modifications can be made, these improvements and modifications also should be regarded as protection scope of the present invention.It is unknown in the present embodiment
The available prior art of true each part is realized.
Claims (7)
- A kind of 1. turboshaft engine inlet duct, it is characterised in that：Including centerbody component, splitter component and casing component；The centerbody component includes ring-shaped air chamber（3）, from ring-shaped air chamber（3）The centerbody leading portion extended forward（4）, from annular Air chamber（3）The centerbody back segment to extend back（5）；The casing component includes the outer barrel around centerbody component（13）And the lip section positioned at outer barrel forward position（12）；The splitter component includes surrounding centerbody back segment（5）The splitter inner cylinder of setting（8）, around splitter inner cylinder（8）Splitter Outer barrel（9）, positioned at splitter inner cylinder（8）And splitter outer barrel（9）Between splitter（10）, driving splitter（10）To ring-shaped air chamber（3） Advance or retreat away from ring-shaped air chamber in direction（3）Drive device（11）；The ring-shaped air chamber（3）Diameter be more than centerbody leading portion（4）And centerbody back segment（5）Diameter；The centerbody group First flow is formed between part and outer barrel（31）；Form what is connected with first flow between the splitter component and centerbody back segment Second flow channel（32）；The splitter（10）Front end stretch out in splitter inner cylinder all the time（8）, and back and forth transported between first position and the second place It is dynamic, work as splitter（10）During positioned at first position, splitter（10）Positioned at original position；Splitter（10）During positioned at the second place, splitter（10） In drive device（11）Moved forward under promotion forward close to ring-shaped air chamber（3）Position；Splitter（10）Lower surface be Outwardly cambered surface, and splitter inner cylinder（8）Inner surface be also cambered surface, and work as splitter（10）During positioned at first position, splitter （10）Lower surface and splitter inner cylinder（8）Inner surface form coherent cambered surface.
- 2. the turboshaft engine inlet duct according to claim 1, it is characterised in that：The splitter component also includes enclosing It is wound on splitter（10）The sealing air ring of periphery（23）, connection sealing air ring（23）Conduit（24）And connecting conduit（24）Aerating and exhaust device（26）；The sealing air ring（23）Upper end against splitter outer barrel （9）, seal air ring（23）Lower end against splitter inner cylinder（8）；Seal air ring（23）After inflation simultaneously with splitter inner cylinder（8）, split Sharp outer barrel（9）Form sealing.
- 3. the turboshaft engine inlet duct according to claim 1, it is characterised in that：The ring-shaped air chamber includes annular Metal framework（14）, be wrapped in metal framework（14）The deformable soft shell in outside（15）And the deformable soft shell of connection （15）And to the aerating and exhaust device of deformable soft shell inflation/deflation（18）.
- 4. the turboshaft engine inlet duct according to claim 3, it is characterised in that：The endless metal framework（14） Upper every 90 ° of directions are provided with a passage（16）, the deformable soft shell on the position of each passage（15）It is corresponding to be provided with One charging connector, passes through five-way conduit（17）With aerating and exhaust device（18）It is connected.
- 5. the turboshaft engine inlet duct according to claim 3, it is characterised in that：The outer barrel（13）In deformable soft shell（15）The part outwardly convex in outside, outer barrel（13）With deformable soft shell（15）Between First flow part is bending.
- 6. according to the turboshaft engine inlet duct described in claim 3 or 4 or 5, it is characterised in that：It is described deformable soft Property shell（15）Demarcation corresponding with air pressure is provided with, different demarcation corresponds to the air pressure of different deformable soft shells respectively Value.
- 7. a kind of operating method to turboshaft engine inlet duct any one of claim 1 to 6, its feature exists In：Including dirt sand separation efficiency mode and high pneumatic efficiency pattern；When the turboshaft engine inlet duct is in dirt sand separation efficiency mode, splitter（10）To ring-shaped air chamber（3）Before direction Enter to make splitter（10）With ring-shaped air chamber（3）Between second flow channel part narrow；And ring-shaped air chamber（3）Inflate and outwards swollen It is swollen, make ring-shaped air chamber（3）With outer barrel（13）Between first flow part narrow；When the turboshaft engine inlet duct is in high pneumatic efficiency pattern, splitter（10）Retreat makes splitter away from ring-shaped air chamber （10）With ring-shaped air chamber（3）Between second flow channel part broaden；And ring-shaped air chamber（3）Deflate and to contract, make annular Air chamber（3）With outer barrel（13）Between first flow part broaden.
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| CN201610985841.1A CN106523158B (en) | 2016-11-09 | 2016-11-09 | A kind of turboshaft engine inlet duct and operating method |
| CN201710959321.8A CN107605602B (en) | 2016-11-09 | 2016-11-09 | A kind of structure changes turboshaft engine gas handling system |
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| CN201610985841.1A CN106523158B (en) | 2016-11-09 | 2016-11-09 | A kind of turboshaft engine inlet duct and operating method |
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| CN107120193B (en) * | 2017-06-28 | 2024-05-03 | 李兵长 | Engine air inlet device for helicopter and helicopter |
| CN109519282B (en) * | 2018-11-07 | 2019-12-20 | 中国航发湖南动力机械研究所 | Integral inertia particle separator based on wall surface rebound characteristic and aero-engine |
| CN111024402B (en) * | 2019-12-13 | 2021-05-07 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
| CN111648864B (en) * | 2020-04-30 | 2021-07-23 | 南京航空航天大学 | Flexible bulge structure for variable particle separator center body and design method thereof |
| CN111648862A (en) * | 2020-04-30 | 2020-09-11 | 南京航空航天大学 | Flexible bulge central body structure of variable particle separator and design method thereof |
| CN111648865B (en) * | 2020-04-30 | 2022-02-08 | 南京航空航天大学 | Multi-air-chamber bulge central body structure of variable particle separator and design method thereof |
| CN113090390B (en) * | 2021-04-07 | 2022-02-08 | 南京航空航天大学 | Precooling type engine air inlet channel with bypass flow path and design method |
| CN113624504A (en) * | 2021-06-29 | 2021-11-09 | 北京精密机电控制设备研究所 | Swimming engine load simulation device and method |
| CN113530857A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Electric driving type sand discharging device for particle separator of aircraft engine |
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| CN102434285A (en) * | 2011-11-21 | 2012-05-02 | 南京航空航天大学 | Special air bag-based axially-symmetrical deformable air inlet channel |
| CN102698510A (en) * | 2012-04-13 | 2012-10-03 | 上海交通大学 | Airflow channel entry inertia particle separator |
| US10184399B2 (en) * | 2012-09-17 | 2019-01-22 | Honeywell International Inc. | Inlet particle separator systems and methods |
| DE102012022259A1 (en) * | 2012-11-13 | 2014-05-28 | Rolls-Royce Deutschland Ltd & Co Kg | Combustor shingle of a gas turbine and process for its production |
| US20160177823A1 (en) * | 2014-12-22 | 2016-06-23 | General Electric Company | System and method with inlet particle separator |
| CN105781746B (en) * | 2016-05-09 | 2017-11-10 | 兰州大学 | A kind of adaptive Inertia particle separator |
-
2016
- 2016-11-09 CN CN201610985841.1A patent/CN106523158B/en active Active
- 2016-11-09 CN CN201710959321.8A patent/CN107605602B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106523158A (en) | 2017-03-22 |
| CN107605602B (en) | 2018-08-31 |
| CN107605602A (en) | 2018-01-19 |
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