CN106523158A - Turboshaft engine intake device and operation method - Google Patents
Turboshaft engine intake device and operation method Download PDFInfo
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- CN106523158A CN106523158A CN201610985841.1A CN201610985841A CN106523158A CN 106523158 A CN106523158 A CN 106523158A CN 201610985841 A CN201610985841 A CN 201610985841A CN 106523158 A CN106523158 A CN 106523158A
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- splitter
- ring
- air chamber
- shaped air
- centerbody
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a turboshaft engine intake device and an operation method thereof. The turboshaft engine intake device comprises a central body component, a wedge component and a casing component, and is characterized in that a flexible deformable annular air chamber is embedded into the central body component, meanwhile, a wedge capable of moving in the axial direction is designed, and the profiles of the air chamber and the axial position of the wedge can be adjusted according to the working environment and the working state of an engine. When a helicopter works in unclean air environments such as the environment with dust sand, the intake system is enabled to work in a mode with high dust sand separation efficiency through increasing the height of the air chamber and moving the wedge forwards; and when the helicopter is in a cruising state, the intake system is enabled to work in a mode with high aerodynamic efficiency by reducing the height of the air chamber and moving the wedge backwards. The invention effectively solves the problem that a traditional fixed-geometry intake system cannot give consideration to both low-altitude efficient sand draining and high cruising aerodynamic performance.
Description
Technical field
The present invention relates to Aeroengine Design field, especially turboshaft engine gas handling system.
Background technology
China is one of maximum country of desert area in the world, desert stretch in a connected line in an arcuate zone in northwest, North China and
On the soil in northeast, this arc desert belt north and south width 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.As helicopter landing is convenient, airport environment is required
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 clashes into the engine working-blade of rotation at a high speed, and oarse-grained sandstone 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 tiny cooling duct in moving turbine blade, make turbo blade overtemperature or even burn.A part of dirt sand can also
Deposit in the inner surface of turbine wheel shaft, make engine luggine value uprush.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 lift 800h by original 80h.For this purpose, improve starting
Machine gas handling system excludes the ability of foreign matter extremely significant actively impact to the life-span of turboshaft engine, it is necessary in China
Adopt on turboshaft engine of new generation.
In the engineering practice of early stage, widely used obstruction formula screen pack as the dust-proof means of sand control in gas handling system, but
It is that As time goes on, the dirt sand and exotic sticked on screen pack is cumulative, and motor inlet is easy to by these
Exotic is blocked so that air-flow is difficult to be inhaled into engine, and flow resistance is also dramatically increased, therefore filter needs Jing often to carry out
Cleaning and maintenance, the manpower and materials of consumption are very big.Later, Boeing Co. in its T700 for developing engine innovatively
A kind of new inlet duct is devised, by runner is bent, sand grains runner is thrown away into using sand grains inertia big principle.This
The method pressure loss for planting desanding is less, can continuously exclude dirt sand, and maintenance cost is also very low.But as its geometry is fixed, mesh
Front still can only seeking between several functions (air inlet, sediment outflow), different operating modes (take off, cruise) takes compromise, it is difficult to realize full work
The Performance optimization of envelope curve.If adopting 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 realize 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, by remembering conjunction at the bulge of centerbody
Gold and worm screw realizing the deformation of bulge, so as to adapt 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 there is the even property of circumferential asymmetry and close
Envelope problem, and the research of memorial alloy at present is still not reaching to the level of requirement, therefore, the engineer applied that this is envisioned is difficult
Degree is very big.
Accordingly, it would be desirable to a kind of new technical scheme is solving 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, make the gas handling system be in efficient operation all the time.
To reach above-mentioned purpose, the present invention can be adopted the following technical scheme that：
A kind of turboshaft engine inlet duct, including centerbody component, splitter component and casing component；The centerbody
After component includes ring-shaped air chamber, extend from ring-shaped air chamber forward centerbody leading portion, the centerbody extended back from ring-shaped air chamber
Section；The casing component includes the outer tube around centerbody component and the lip section positioned at outer tube forward position；The splitter component bag
Include around centerbody back segment arrange splitter inner core, the splitter outer tube around splitter inner core, positioned at splitter inner core and splitter outer tube
Between splitter, drive splitter to ring-shaped air chamber direction advance or retreat away from ring-shaped air chamber driving means；The annular
Air chamber with diameter greater than centerbody leading portion and the diameter of centerbody back segment；Form first-class between the centerbody component and outer tube
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 of soft shell is adjusted by inflation/deflation is carried out to air chamber, adjusts removable by actuation mechanism
The axial location of ligulate splitter, so that the local working environment of runner matching of this gas handling system.Work as aircraft, such as helicopter work
When making in the environment of unholiness dust-laden sand, by the height for increasing ring-shaped air chamber, and drive ligulate splitter to move forward, make first-class
Degree of crook in road, second flow channel becomes part that is big and bending and increases, and sand grains is thrown away stream using sand grains inertia big principle
Road；When helicopter is when runway landing and high-performance cruise is cleaned, reduce soft shell height, and after driving ligulate splitter position
Move, make the degree of crook in first flow, second flow channel diminish, sweep 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 method for operating of above-mentioned turboshaft engine inlet duct, 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 inflation 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 is retreated and 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, the turboshaft engine inlet duct that the present invention is provided can also be employed the following technical solutions：
A kind of turboshaft engine inlet duct, including centerbody component, splitter component and casing component；
The centerbody component includes ring-shaped air chamber, extend from ring-shaped air chamber forward centerbody leading portion, from ring-shaped air chamber
The centerbody back segment for extending back；The casing component includes the outer tube around centerbody component；The splitter component includes splitting
Point, driving splitter advance to ring-shaped air chamber direction or retreat the driving means 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 tube, this
One runner be included in formed between centerbody leading portion and outer tube first flow forward part, formed between ring-shaped air chamber and outer tube
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 first flow in the middle part of point between formed part in bending section, and first flow be equally bending simultaneously
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.
Technical problem that the turboshaft engine inlet duct of second technical scheme is solved and the beneficial effect of realization with
In first, technical scheme is identical, again by the height for increasing ring-shaped air chamber, and drives ligulate splitter to move forward, makes first-class
Degree of crook in road, second flow channel becomes part that is big and bending and increases, and sand grains is thrown away stream using sand grains inertia big principle
Road；When helicopter is when runway landing and high-performance cruise is cleaned, reduce soft shell height, and after driving ligulate splitter position
Move, make the degree of crook in first flow, second flow channel diminish, sweep tails off and forms unobstructed runner environment, to carry
The pneumatic efficiency of the high inlet duct.
Description of the drawings
Fig. 1 is the cross-sectional schematic 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 cross-sectional schematic.
Specific 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 the outer tube 13 around centerbody component and
Positioned at the lemniscate lip section 12 in 13 forward position of outer tube.The centerbody component includes front fairing 1, ring-shaped air chamber 3, certainly annular gas
Centerbody leading portion 4 that room extends forward, centerbody back segment 5, connection the fixed outer cylinder 13 extended back from ring-shaped air chamber are with
The front support section 2 of heart body leading portion 4, rear support section 6, the pressure monitor 7 of connection fixed outer cylinder 13 and centerbody back segment 5.Its
In, ring-shaped air chamber 3 adopts monoblock type framework, with 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 core 8, splitter outer tube 9, can move forward and backward splitter 10, drive
Dynamic splitter 10 advances to 3 direction of ring-shaped air chamber or retreats the driving means 11 away from ring-shaped air chamber 3.The driving means 11 can
Using hydraulic transmission or linear stepping motor etc..The driving means 11 include position feedback device, stop etc..
The position feedback device can be with the axial location of Real-time Feedback splitter 10, and the stop is to limit 10 axial dominant bit of splitter
The stopping means of shifting, causes engine flow too small or excessive in case 10 axial displacement of splitter is excessive.Wherein, institute in Fig. 1 for another example
Show, the ring-shaped air chamber 3 with diameter greater than centerbody leading portion 4 and the diameter of centerbody back segment 5.The centerbody component and outer tube
Between formed first flow 31, before the first flow 31 is included in the first flow formed between centerbody leading portion 4 and outer tube 13
Partly, part in the first flow formed between ring-shaped air chamber 3 and outer tube 13.Between the splitter component and centerbody back segment 5
The second flow channel 32 that formation is connected with first flow 31.It is as the ring-shaped air chamber 3 is with diameter greater than centerbody leading portion 4, described
First flow forward part with first flow in the middle part of point between form bending section, and again as ring-shaped air chamber 3 is with diameter greater than in
The diameter of heart body back segment 5, in first flow, part is equally bending and is communicated to second flow channel 32；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 core 8 all the time, and back and forth transports between first position and the second place
Dynamic, when splitter 10 is located at first position, splitter is located at original position, that is, be housed between splitter inner core 8 and splitter outer tube 9 and cannot
The position being moved rearwards by again；When splitter 10 is located at the second place, splitter 10 is moved forward under the promotion forward of driving means 11
To near 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 core 8 is also cambered surface, and when splitter 10 is located at first position, the lower surface of splitter is interior with splitter inner core
Surface forms coherent cambered surface；Such design causes to need the pneumatic efficiency for improving the inlet duct and be located at splitter 10
During first position, the lower surface of splitter forms the type face during coherent cambered surface makes whole second flow channel with the inner surface of splitter inner core
It is coherent simply to hinder little, it is advantageously implemented more smooth runner type face and improves pneumatic efficiency.The movement of the splitter 10 and ring
It is that splitter 10 advances to 3 direction of ring-shaped air chamber makes splitter that the expansion or shrinkage of shape air chamber changes the impact for producing to overall runner
Second flow channel part between 10 and ring-shaped air chamber 3 narrows；And the inflation of ring-shaped air chamber 3 simultaneously outwards expands, make ring-shaped air chamber 3 and
First flow part between outer tube 13 narrows；Splitter 10 is retreated 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, makes first-class between ring-shaped air chamber 3 and outer tube 13
Road part broadens.
Please in conjunction with shown in Fig. 2, the ring-shaped air chamber includes endless metal framework 14, is wrapped on the outside of metal framework 14
Deformable soft shell 15 and the deformable soft shell 15 of connection the aerating and exhaust device to 15 inflation/deflation of deformable soft shell
18.The deformable soft shell 15 is internally embedded aramid fiber or Metal wire material using specific rubber as matrix, by adjusting
Solar term pressure, can change the deflection of deformable soft shell 15.Wherein, during unaerated, deformable soft shell 15 is tightly wrapped up
On endless metal framework 14.Part outwardly convex of the outer tube on the outside of deformable soft shell 15, outer tube can with outer tube
First flow part between yielding flexibility shell 15 is bending, so at this after 15 inflation of deformable soft shell
The part of bending can substantially change flow channel shape.A passage 16 is provided with per 90 ° of directions on the endless metal framework 14,
On corresponding position, deformable soft shell 15 is all provided with a charging connector, by five-way conduit 17 and 18 phase of air-charging and air-discharging system
Even, a valve 19 is set on five-way conduit 17 aeration quantity is controlled.When filling (put) gas system 18 and being operated, valve is opened
Door 19, four valves are filled (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 with pressure respectively using threeway conduit 20
Mechanism of qi, is respectively provided with compressor valve 21 and air exhauster valve 22 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, open 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, the air chamber for being adopted in runner
Inflation pressure is higher, 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 the different deformable soft shell of correspondence.In engine air during real work, by measuring pressure monitoring point 7
Pressure, and the data of above-mentioned demarcation compare, and can obtain the practical distortion amount of deformable soft shell 15.
Refer to shown in Fig. 3, be the cross-sectional schematic 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 core 8 and splitter outer tube 9, sealing air ring 23 is inlayed in groove, air ring 23 is sealed
It is connected with aerating and exhaust device 26 by conduit 24,26 structure of aerating and exhaust device 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 driving means drive splitter 10 to move, valve 25 is opened,
Deflated using 26 pairs of sealing air rings 23 of air-charging and air-discharging system；After splitter 10 moves to specified location, using air-charging and air-discharging system 26
Inflate to sealing air ring 23, make sealing air ring be expanded into largest deformation state, so as to play sealing effectiveness, now, close 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 method of operating 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 using dirt sand separation efficiency mode；When helicopter is needed using high pneumatic effect when runway landing and high-performance cruise is cleaned
Rate pattern.
When the turboshaft engine inlet duct is in dirt sand separation efficiency mode, splitter 10 is to before 3 direction of ring-shaped air chamber
Enter to make 32 part of second flow channel between splitter 10 and ring-shaped air chamber 3 to narrow；And ring-shaped air chamber 3 is inflated and is outwards expanded, and is made
31 part of first flow between ring-shaped air chamber 3 and outer tube 13 narrows.Can so make in first flow 31, second flow channel 32
Degree of crook becomes part that is big and bending and increases, and sand grains is thrown away runner using sand grains inertia big principle.
When the turboshaft engine inlet duct is in high pneumatic efficiency pattern, splitter 10 is retreated to be made away from ring-shaped air chamber 3
32 part of second flow channel between splitter 10 and ring-shaped air chamber 3 broadens；And ring-shaped air chamber 3 is deflated and to contract, makes annular
31 part of first flow between air chamber 3 and outer tube 13 broadens.The bending in first flow 31, second flow channel 32 can so be made
Degree diminishes, sweep tails off and forms unobstructed runner environment, to improve the pneumatic efficiency of the inlet duct.
The method and approach that the present invention implements the technical scheme is a lot, and the 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
True each part can use prior art to be realized.
Claims (10)
1. a kind of 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), extend from ring-shaped air chamber (3) forward centerbody leading portion (4), from annular
The centerbody back segment (5) that air chamber (3) extends back；
The casing component includes the outer tube (13) around centerbody component and the lip section (12) positioned at outer tube forward position；
The splitter component includes the splitter inner core (8) arranged around centerbody back segment (5), around the splitter of splitter inner core (8)
Outer tube (9), the splitter (10) between splitter inner core (8) and splitter outer tube (9), driving splitter (10) to ring-shaped air chamber (3)
Advance or retreat the driving means (11) away from ring-shaped air chamber (3) in direction；
The ring-shaped air chamber (3) with diameter greater than centerbody leading portion (4) and the diameter of centerbody back segment (5)；The centerbody group
First flow (31) is formed between part and outer tube；Form what is connected with first flow between the splitter component and centerbody back segment
Second flow channel (32).
2. turboshaft engine inlet duct according to claim 1, it is characterised in that：The front end of the splitter (10) is all the time
Splitter inner core (8) is stretched out in, and is moved back and forth between first position and the second place, when splitter (10) is positioned at first position
When, splitter (10) is positioned at original position；Splitter (10) positioned at the second place when, splitter (10) is under driving means (11) promotion forward
Move forward near the position of ring-shaped air chamber (3)；The lower surface of splitter (10) is outwardly cambered surface, and splitter inner core
(8) inner surface is also cambered surface, and works as splitter position (10) when first position, lower surface and the splitter inner core (8) of splitter (10)
Inner surface form coherent cambered surface.
3. turboshaft engine inlet duct according to claim 1 and 2, it is characterised in that：The splitter component also includes
It is centered around sealing air ring (23), the conduit (24) of connection sealing air ring (23) and the connecting conduit (24) of splitter (10) periphery
Aerating and exhaust device (26)；The upper end of sealing air ring (23) seals the lower end of air ring (23) against splitting against splitter outer tube (9)
Sharp inner core (8)；Sealing is formed with splitter inner core (8), splitter outer tube (9) simultaneously after sealing air ring (23) inflation.
4. turboshaft engine inlet duct according to claim 1, it is characterised in that：The ring-shaped air chamber includes annular gold
Category framework (14), the deformable soft shell (15) being wrapped on the outside of metal framework (14) and the deformable soft shell (15) of connection
And the aerating and exhaust device (18) to deformable soft shell inflation/deflation.
5. turboshaft engine inlet duct according to claim 4, it is characterised in that：On the endless metal framework (14)
A passage (16) is provided with per 90 ° of directions, deformable soft shell (15) correspondence is provided with one and fills on the position of each pore
Valve, is connected with aerating and exhaust device (18) by five-way conduit (17).
6. turboshaft engine inlet duct according to claim 4, it is characterised in that：The outer tube (13) is deformable soft
Part outwardly convex on the outside of property shell (15), the first flow part between outer tube (13) and deformable soft shell (15) is
Bending.
7. the turboshaft engine inlet duct according to claim 4 or 5 or 6, it is characterised in that：It is described deformable flexible outer
Shell (15) is provided with demarcation corresponding with air pressure, and different demarcates the atmospheric pressure value for corresponding to different deformable soft shells respectively.
8. a kind of method of operating to turboshaft engine inlet duct any one of claim 1 to 7, it is characterised in that：
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) is to before ring-shaped air chamber (3) direction
Enter to make the second flow channel part between splitter (10) and ring-shaped air chamber (3) to narrow；And ring-shaped air chamber (3) inflation is simultaneously outwards swollen
It is swollen, make the first flow part between ring-shaped air chamber (3) and outer tube (13) narrow；
When the turboshaft engine inlet duct is in high pneumatic efficiency pattern, splitter (10) is retreated and makes splitter away from ring-shaped air chamber
(10) the second flow channel part and between ring-shaped air chamber (3) broadens；And ring-shaped air chamber (3) is deflated and to contract, makes annular
First flow part between air chamber (3) and outer tube (13) broadens.
9. a kind of 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), extend from ring-shaped air chamber (3) forward centerbody leading portion (4), from annular
The centerbody back segment (5) that air chamber (3) extends back；
The casing component includes the outer tube (13) around centerbody component；
The splitter component includes splitter (10), drives splitter (10) to advance to ring-shaped air chamber (3) direction or retreat away from ring
The driving means (11) of shape air chamber；
The ring-shaped air chamber (3) with diameter greater than centerbody leading portion (4) and the diameter of centerbody back segment (5)；The centerbody group
First flow (31) is formed between part and outer tube (13), the first flow (31) is included in centerbody leading portion (4) and outer tube (13)
Between the first flow forward part for being formed, part in the first flow that formed between ring-shaped air chamber (3) and outer tube (13)；It is described to split
The second flow channel (32) connected with first flow is formed between sharp component and centerbody back segment (5)；The first flow forward part
With first flow in the middle part of point between form part in bending section, and first flow and be equally bending and be communicated to second flow channel
(32)；The forward part of the second flow channel partly forms tubular after forming toroidal and second flow channel.
10. turboshaft engine inlet duct according to claim 9, it is characterised in that：Splitter (10) is to ring-shaped air chamber (3)
Direction is advanced makes the second flow channel part between splitter (10) and ring-shaped air chamber (3) narrow；And ring-shaped air chamber (3) inflate and to
Outer expansion, makes the first flow part between ring-shaped air chamber (3) and outer tube (13) narrow；Splitter (10) is retreated away from ring-shaped air chamber
(3) the second flow channel part between splitter (10) and ring-shaped air chamber (3) is made to broaden；And ring-shaped air chamber (3) is deflated and is inwardly received
Contracting, makes the first flow part between ring-shaped air chamber (3) and outer tube (13) broaden.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Application Number | Priority Date | Filing Date | Title |
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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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| CN201610985841.1A Active CN106523158B (en) | 2016-11-09 | 2016-11-09 | A kind of turboshaft engine inlet duct and operating method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107120193A (en) * | 2017-06-28 | 2017-09-01 | 李兵长 | A kind of helicopter engine intake duct and helicopter |
| CN109519282A (en) * | 2018-11-07 | 2019-03-26 | 中国航发湖南动力机械研究所 | Monoblock type Inertia particle separator and aero-engine based on bounce-back characteristic |
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
| CN111648864A (en) * | 2020-04-30 | 2020-09-11 | 南京航空航天大学 | Flexible bulge structure for variable particle separator center body and design method thereof |
| 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 |
| 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 |
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Cited By (8)
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| CN107120193A (en) * | 2017-06-28 | 2017-09-01 | 李兵长 | A kind of helicopter engine intake duct and helicopter |
| CN107120193B (en) * | 2017-06-28 | 2024-05-03 | 李兵长 | Engine air inlet device for helicopter and helicopter |
| CN109519282A (en) * | 2018-11-07 | 2019-03-26 | 中国航发湖南动力机械研究所 | Monoblock type Inertia particle separator and aero-engine based on bounce-back characteristic |
| 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 |
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
| CN111648864A (en) * | 2020-04-30 | 2020-09-11 | 南京航空航天大学 | Flexible bulge structure for variable particle separator center body and design method thereof |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107605602A (en) | 2018-01-19 |
| CN107605602B (en) | 2018-08-31 |
| CN106523158B (en) | 2018-01-19 |
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