CN107120193A - A kind of helicopter engine intake duct and helicopter - Google Patents
A kind of helicopter engine intake duct and helicopter Download PDFInfo
- Publication number
- CN107120193A CN107120193A CN201710504473.9A CN201710504473A CN107120193A CN 107120193 A CN107120193 A CN 107120193A CN 201710504473 A CN201710504473 A CN 201710504473A CN 107120193 A CN107120193 A CN 107120193A
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- Prior art keywords
- sand dust
- engine
- helicopter
- intake duct
- sand
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000004576 sand Substances 0.000 claims abstract description 103
- 239000000428 dust Substances 0.000 claims abstract description 102
- 238000004891 communication Methods 0.000 claims abstract description 49
- 238000000926 separation method Methods 0.000 claims abstract description 25
- 239000013049 sediment Substances 0.000 claims description 20
- 238000010438 heat treatment Methods 0.000 claims description 10
- 238000012856 packing Methods 0.000 claims description 10
- 230000008014 freezing Effects 0.000 description 3
- 238000007710 freezing Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 241000237858 Gastropoda Species 0.000 description 1
- 206010068052 Mosaicism Diseases 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 210000003765 sex chromosome Anatomy 0.000 description 1
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
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- 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
-
- 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
- F02C7/057—Control or regulation
Abstract
The invention discloses a kind of helicopter engine intake duct and helicopter.The helicopter is included with engine intake duct：Engine inlets, its one end is connected with engine；Sand dust separator, it is connected with engine mounting platform, including a sand dust separation body, and sand dust separation body has inner chamber and the first air port, and interior cavity space is the first admission space；The air inlet of first air port and engine inlets is separated by setting, and the space between the first air port and air inlet is the second admission space；Flexible communication apparatus, it is connected with sand dust separator, and the communication apparatus that stretches includes a Telescopic air duct, and Telescopic air duct can be moved, so that with closed communication position and open position.When in sand dust environment landing flight, by Telescopic air duct so that extraneous gas enters from the first admission space, and the gas of the first admission space is to carry out sand dust separation by sand dust separator, so as to solve the problems, such as in sand dust environment landing flight.
Description
Technical field
The present invention relates to helicopter engine air induction field, more particularly to a kind of helicopter is filled with engine charge
Put and helicopter.
Background technology
In the prior art, the engine intake duct of helicopter is mainly equipped with air inlet before engine compressor air inlet
Increase sand dust separator before road and air intake duct.
Sand dust separator core is arranges substantial amounts of vortex tube particle separator, when air passes through vortex tube, sand dust
It is separated, clean air enters engine compressor.
Have as a drawback that in the prior art：
Increase before engine inlets after sand dust separator, the increase of engine charge crushing causes power loss to increase,
Available horsepower is reduced；
Sand dust separator is in freezing environment in use, being only capable of meeting 30 minutes abilities to work of part airworthiness standard.With
The increase of time, vortex tube can gradually be frozen, and engine charge crushing is continuously increased, and power loss is increasing, finally, tied
Ice may block vortex tube, cause engine misses；
Heat anti-icing passage long, need substantial amounts of bleed or power supply, engine power loss is very big.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
Overcome it is an object of the invention to provide a kind of helicopter with engine intake duct or at least mitigate existing skill
At least one drawbacks described above in art.
To achieve the above object, the present invention provides a kind of helicopter and included with engine intake duct：
Engine inlets, described engine inlets one end is connected with engine；
Sand dust separator, the sand dust separator is connected with engine mounting platform, the sand dust separator bag
A sand dust separation body is included, the sand dust separation body has inner chamber and the first air port, and the space of the interior intracavitary is first
Admission space；
First air port is relative with the air inlet of the engine inlets and is separated by setting, first air port and institute
It is the second admission space to state the space between air inlet；
Flexible communication apparatus, the flexible communication apparatus with the sand dust separator or with the sand dust separator with
And the engine inlets are connected, the flexible communication apparatus includes a Telescopic air duct, and the Telescopic air duct can be moved,
So as to closed communication position and open position；Wherein,
In the closed communication position, first air port is connected with the air inlet by the Telescopic air duct, so that
Extraneous gas is set only to enter the engine inlets from first admission space；
In the open position, extraneous gas from second admission space for the engine inlets provide gas or
Extraneous gas provides gas for the engine inlets jointly from first admission space and second admission space.
Preferably, the flexible communication apparatus is arranged on the interior intracavitary of the sand dust separator and separated with the sand dust
Device is connected.
Preferably, the flexible communication apparatus further comprises：
Drive device, the drive device is arranged on the inner chamber of the sand and dust separation device, and the drive device has one
Individual output end；
Telescoping mechanism, described telescoping mechanism one end is connected with the output end, the other end of the telescoping mechanism with it is described
Telescopic air duct is connected；Wherein,
The telescoping mechanism can under the driving of the drive device stretching motion, so as to drive the Telescopic air duct to exist
Changed between the closed communication position and open position.
Preferably, the drive device is motor；
The telescoping mechanism includes worm screw and driving arm, and one end of the worm screw and the output end of the motor connect
Connect；
The driving arm is arranged on the worm screw；
The Telescopic air duct is arranged on the driving arm；Wherein,
The motor can provide power for the worm screw；
The worm screw is rotated by the power, so as to drive the driving arm to be moved along a straight line.
Preferably, the flexible communication apparatus further comprises：Elastic packing lip, the elastic packing lip is arranged on
On one end face of the looped duct；Elastic seal ring, the elastic seal ring is arranged on another of the looped duct
On end face；In the closed communication position, the end face for being provided with elastic packing lip of the looped duct is against the air inlet
Mouthful, another end face is contacted with the wall of the inner chamber of the sand and dust separation device.
Preferably, an end face of the sand dust separation body is first air port；
Sand dust separating pipe and sediment outflow road are provided with the sand dust separation body；
The sand dust separating pipe connects the wall that the sand dust separates body；
The sediment outflow road is connected with the sand and dust separating pipe.
Preferably, the sand dust separator further comprises sediment outflow pipe, and the sediment outflow pipe is connected with the sediment outflow road.
Preferably, the sand dust separator further comprises heating anti-icing lip, and the anti-icing lip of heating is arranged on
On first air port.
Preferably, the air inlet of the engine inlets is flared.
Present invention also provides a kind of helicopter, the helicopter include engine and be connected with the engine it is straight
Machine engine intake duct is risen, the helicopter is helicopter engine charge as described above with engine intake duct
Device.
The helicopter of the application is controlled with engine intake duct by Telescopic air duct, so as to select as needed
It is to enter from the second admission space or the entrance of the first admission space to select extraneous gas.
When in sand dust environment landing flight, by Telescopic air duct so that extraneous gas enters from the first admission space,
And the gas of the first admission space is to carry out sand dust separation by sand dust separator, so as to solve in sand dust environment landing
Flight problem.
When helicopter is not under sand dust environment, Telescopic air duct is adjusted to open position, most of extraneous gas or complete
Portion's extraneous gas enters engine inlets by the second admission space, reduces power loss.
In addition, using this structure, even if making the sand dust separating pipe in sand dust separator freeze due to cold air, due to can
To carry out position adjustments by flexible communication apparatus, Telescopic air duct is adjusted to open position, can also engine is normally entered
Gas, will not hinder the air inlet of engine due to the icing of sand dust separator.
Brief description of the drawings
Fig. 1 is the structural representation of helicopter engine intake duct according to a first embodiment of the present invention, wherein, stretch
Contracting air channel is located at closed communication position.
Fig. 2 is another structural representation of the helicopter engine intake duct of embodiment illustrated in fig. 1, wherein, stretch
Air channel is located at open position.
Fig. 3 is the structure schematic cross-sectional view of the helicopter engine intake duct of embodiment illustrated in fig. 1, wherein, stretch
Air channel is located at closed communication position.
Fig. 4 is the structure schematic cross-sectional view of the helicopter engine intake duct of embodiment illustrated in fig. 1, wherein, stretch
Air channel is located at open position.
Fig. 5 is the structural representation of the engine inlets in the helicopter engine intake duct of embodiment illustrated in fig. 1
Figure.
Fig. 6 is the structural representation of the flexible communication apparatus in the helicopter engine intake duct of embodiment illustrated in fig. 1
Figure.
Fig. 7 is the structural representation of the sand dust separator in the helicopter engine intake duct of embodiment illustrated in fig. 1
Figure.
Reference：
| 1 | Engine inlets | 11 | Air inlet |
| 2 | Sand dust separator | 52 | Drive device |
| 21 | Sand dust separates body | 53 | Telescoping mechanism |
| 211 | Inner chamber | 54 | Elastic packing lip |
| 212 | First air port | 55 | Elastic seal ring |
| 3 | First admission space | 221 | Sand dust separating pipe |
| 4 | Second admission space | 222 | Sediment outflow road |
| 5 | Flexible communication apparatus | 223 | Sediment outflow pipe |
| 51 | Telescopic air duct | 224 | Heat anti-icing lip |
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
Fig. 1 is the structural representation of helicopter engine intake duct according to a first embodiment of the present invention, wherein, stretch
Contracting air channel is located at closed communication position.Fig. 2 is that another structure of the helicopter engine intake duct of embodiment illustrated in fig. 1 is shown
It is intended to, wherein, Telescopic air duct is located at open position.Fig. 3 is the knot of the helicopter engine intake duct of embodiment illustrated in fig. 1
Structure schematic cross-sectional view, wherein, Telescopic air duct is located at closed communication position.Fig. 4 is the helicopter engine of embodiment illustrated in fig. 1
The structure schematic cross-sectional view of inlet duct, wherein, Telescopic air duct is located at open position.Fig. 5 is the helicopter of embodiment illustrated in fig. 1
With the structural representation of the engine inlets in engine intake duct.Fig. 6 is the helicopter of embodiment illustrated in fig. 1 with starting
The structural representation of flexible communication apparatus in machine inlet duct.Fig. 7 is the helicopter engine charge of embodiment illustrated in fig. 1
The structural representation of sand dust separator in device.
The engine intake duct of helicopter as shown in Figures 1 to 4 includes engine inlets 1, flexible communication apparatus 5
And sand dust separator 2.
The one end of engine inlets 1 is connected with engine；Sand dust separator 2 is connected with engine mounting platform, sand dust
Separator 2 includes a sand dust separation body 21, and sand dust separation body 21 has the air port 212 of inner chamber 211 and first, inner chamber
Space in 211 is the first admission space 3；The air inlet 11 of first air port 212 and engine inlets 1 is relative and is separated by and sets
Put, the space between the first air port 212 and air inlet 11 is the second admission space 4；Flexible communication apparatus 5 and sand dust separator
2 connections, the communication apparatus 5 that stretches includes a Telescopic air duct 51, and Telescopic air duct 51 can be moved, so that with closed communication position
And open position；Wherein, at closed communication position (Fig. 1 and Fig. 3 shown in position), the first air port 212 passes through with air inlet 11
Telescopic air duct 51 is connected, so that extraneous gas only enters engine inlets from the first admission space.
At open position (Fig. 2 and Fig. 4 shown in position), extraneous gas is common from the first admission space 3 and the second admission space 4
It is all that engine inlets provide gas.
The helicopter of the application is controlled with engine intake duct by Telescopic air duct, so as to select as needed
It is to enter from the second admission space or the entrance of the first admission space to select extraneous gas.
When in sand dust environment landing flight, by Telescopic air duct so that extraneous gas enters from the first admission space,
And the gas of the first admission space is to carry out sand dust separation by sand dust separator, so as to solve in sand dust environment landing
Flight problem.
When helicopter is not under sand dust environment, Telescopic air duct is adjusted to open position, most of extraneous gas or complete
Portion's extraneous gas enters engine inlets by the second admission space, reduces power loss.
In addition, using this structure, even if making the sand dust separating pipe in sand dust separator freeze due to cold air, due to can
To carry out position adjustments by flexible communication apparatus, Telescopic air duct is adjusted to open position, can also engine is normally entered
Gas, will not hinder the air inlet of engine due to the icing of sand dust separator.
It is understood that in an alternative embodiment, stretch communication apparatus and sand dust separator and engine
Air intake duct is connected.
It is understood that in an alternative embodiment, in open position, extraneous gas is from the second admission space 4
Engine inlets provide gas.In this alternative embodiment, the first air inlet of itself can be closed by sand dust separator
Space is so as to realize.
Referring to Fig. 5, in the present embodiment, air intake duct heater is provided with engine inlets 1, by air intake duct plus
Thermal can be air intake duct heating, so as to prevent air intake duct from freezing.It is understood that the air intake duct heater can be adopted
Mode of heating or Electric heating is caused to be heated with engine.
Referring to Fig. 1 to Fig. 4, in the present embodiment, flexible communication apparatus 5 is arranged in the inner chamber 211 of sand dust separator 2
And be connected with sand dust separator 2.Flexible communication apparatus 5 is arranged on to the interior intracavitary of sand dust separator 2, layout can be saved
Space, convenient layout, and flexible communication apparatus interference engine charge can be prevented.
Referring to Fig. 3, Fig. 4 and Fig. 6, in the present embodiment, flexible communication apparatus 5 further comprises drive device 52 and stretched
Contracting mechanism 53, drive device 52 is arranged on the inner chamber of sand and dust separation device 2, and drive device 52 has an output end；Telescopic machine
The one end of structure 53 is connected with output end, and the other end of telescoping mechanism 53 is connected with Telescopic air duct 51；Wherein, telescoping mechanism 53 can be
Stretching motion under the driving of drive device 52, thus drive the Telescopic air duct 51 closed communication position and open position it
Between change.
Specifically, in the present embodiment, drive device is motor.Telescoping mechanism 53 includes worm screw and driving arm, snail
One end of bar and the output end of motor are connected；Driving arm is arranged on worm screw；Telescopic air duct is arranged on driving arm；Its
In, motor can provide power for worm screw；Worm screw is rotated by power, so as to drive driving arm to be moved along a straight line.
By the way of worm drive, it is to avoid the connection brought to flexible communication apparatus supply, power supply and voltage supply etc. is difficult and reliable
Sex chromosome mosaicism.
It is understood that flexible communication apparatus can also use other modes.For example, telescoping mechanism uses rack-and-pinion
Motion mode etc..
Referring to Fig. 6, in the present embodiment, flexible communication apparatus 5 further comprises that elastic packing lip 54 and elasticity are close
Seal 55, elastic packing lip 54 is arranged on an end face of Telescopic air duct 51；Elastic seal ring 55 is arranged on Telescopic air duct
On 51 another end face；In closed communication position, the end face for being provided with elastic packing lip 54 of Telescopic air duct 51 is against entering
Gas port 11, another end face is contacted with the wall of the inner chamber of sand and dust separation device 2.In this way, it ensure that in closing
Communicating position, extraneous gas only enters engine inlets from the first admission space.I.e. all extraneous gas pass through sand dust
Separator carries out sand dust separation.
Referring to Fig. 7, in the present embodiment, an end face of sand dust separation body 21 is the first air port；Sand dust separates body
Sand dust separating pipe 221, sediment outflow road 222 and sediment outflow pipe 223 are provided with 21；The connection sand dust separation body of sand dust separating pipe 221
21 wall；Sediment outflow road 222 is connected with sand and dust separating pipe 221.Sediment outflow pipe 223 is connected with sediment outflow road 222.
When sand dust separator works, extraneous air enters from sand dust separating pipe, is separated by sand dust separating pipe,
So as to which sand dust is discharged into sediment outflow road, and sediment outflow pipe is entered by sediment outflow road, so as to discharge.
Advantageously, in an alternative embodiment, increase has sand dust collection device, prevents the sand dust of discharge enters from going straight up to
Other positions of machine.
In the present embodiment, sand dust separator further comprises heating anti-icing lip 224, heats anti-icing lip 224 and sets
Put on the first air port.By being provided with the anti-icing lip 224 of the heating, helicopter can be prevented in icing area flight, sand dust
The situation of separator loss of performance due to icing occurs.
In the present embodiment, when the Telescopic air duct 51 in flexible communication apparatus 5 is in closed communication position (Fig. 1 and Fig. 3 institutes
Show position), the first air port 212 is connected with air inlet 11 by Telescopic air duct 51, that is, is formd an engine inlets, stretched
Air channel and the space of sand dust separator one, are provided with heating anti-icing equipment (existing within this space, on engine inlets
Have technology), the anti-icing lip of heating is provided with sand dust separator, being capable of the heated in real-time integral sky so that when in use
Between, prevent the space from freezing, so as to influence engine to work.
Advantageously, in an alternative embodiment, the air inlet of engine inlets is flared.Using this knot
Structure, the second admission space can be acted on punching press when flying before helicopter, further reduce engine power loss.
Present invention also provides a kind of helicopter, the helicopter includes engine and the helicopter being connected with engine
With engine intake duct, wherein, helicopter is that helicopter as described above is filled with engine charge with engine intake duct
Put.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (10)
1. a kind of helicopter engine intake duct, it is characterised in that the helicopter is included with engine intake duct：
Engine inlets (1), described engine inlets (1) one end is connected with engine；
Sand dust separator (2), the sand dust separator (2) is connected with engine mounting platform, the sand dust separator
(2) a sand dust separation body (21) is included, the sand dust separation body (21) has inner chamber (211) and the first air port (212),
Space in the inner chamber (211) is the first admission space (3)；
First air port (212) is relative with the air inlet (11) of the engine inlets (1) and is separated by setting, described first
Space between air port (212) and the air inlet (11) is the second admission space (4)；
Flexible communication apparatus (5), the flexible communication apparatus (5) separates with the sand dust separator (2) or with the sand dust
Device and engine inlets connection, the flexible communication apparatus (5) include a Telescopic air duct (51), described flexible
Air channel (51) can be moved, so that with closed communication position and open position；Wherein,
In the closed communication position, first air port (212) passes through the Telescopic air duct (51) with the air inlet (11)
Connection, so that extraneous gas only enters the engine inlets from first admission space；
In the open position, extraneous gas from second admission space (4) for the engine inlets provide gas or
Extraneous gas provides for the engine inlets jointly from first admission space (3) and second admission space (4)
Gas.
2. helicopter engine intake duct as claimed in claim 1, it is characterised in that the flexible communication apparatus (5)
It is arranged in the inner chamber (211) of the sand dust separator (2) and is connected with the sand dust separator (2).
3. helicopter engine intake duct as claimed in claim 2, it is characterised in that the flexible communication apparatus (5)
Further comprise：
Drive device (52), the drive device (52) is arranged on the inner chamber of the sand and dust separation device (2), the drive device
(52) there is an output end；
Telescoping mechanism (53), described telescoping mechanism (53) one end is connected with the output end, the telescoping mechanism (53) it is another
End is connected with the Telescopic air duct (51)；Wherein,
The telescoping mechanism (53) can under the driving of the drive device (52) stretching motion, so as to drive the Telescopic wind
Changed between the closed communication position and open position in road (51).
4. helicopter engine intake duct as claimed in claim 3, it is characterised in that the drive device is motor；
The telescoping mechanism (53) includes worm screw and driving arm, and one end of the worm screw and the output end of the motor connect
Connect；
The driving arm is arranged on the worm screw；
The Telescopic air duct is arranged on the driving arm；Wherein,
The motor can provide power for the worm screw；
The worm screw is rotated by the power, so as to drive the driving arm to be moved along a straight line.
5. helicopter engine intake duct as claimed in claim 4, it is characterised in that the flexible communication apparatus (5)
Further comprise：
Elastic packing lip (54), the elastic packing lip (54) is arranged on an end face of the Telescopic air duct (51)；
Elastic seal ring (55), the elastic seal ring (55) is arranged on another end face of the Telescopic air duct (51)；
In the closed communication position, the end face for being provided with elastic packing lip (54) of the Telescopic air duct (51) is against described
Air inlet (11), another end face is contacted with the wall of the inner chamber of the sand and dust separation device (2).
6. the helicopter engine intake duct as described in any one in claim 1 to 5, it is characterised in that the sand
One end face of dirt separation body (21) is first air port；
Sand dust separating pipe (221) and sediment outflow road (222) are provided with the sand dust separation body (21)；
The sand dust separating pipe (221) connects the wall of the sand dust separation body (21)；
The sediment outflow road (222) connects with the sand and dust separating pipe (221).
7. helicopter engine intake duct as claimed in claim 6, it is characterised in that the sand dust separator enters one
Step includes sediment outflow pipe (223), and the sediment outflow pipe (223) connects with the sediment outflow road (222).
8. helicopter engine intake duct as claimed in claim 6, it is characterised in that the sand dust separator enters one
Step includes the anti-icing lip (224) of heating, and the anti-icing lip (224) of heating is arranged on first air port.
9. helicopter engine intake duct as claimed in claim 1, it is characterised in that the engine inlets enter
Gas port is flared.
10. a kind of helicopter, it is characterised in that the helicopter includes engine and the helicopter being connected with the engine
With engine intake duct, the helicopter engine intake duct is straight as in one of claimed in any of claims 1 to 9
Rise machine engine intake duct.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710504473.9A CN107120193A (en) | 2017-06-28 | 2017-06-28 | A kind of helicopter engine intake duct and helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710504473.9A CN107120193A (en) | 2017-06-28 | 2017-06-28 | A kind of helicopter engine intake duct and helicopter |
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| Publication Number | Publication Date |
|---|---|
| CN107120193A true CN107120193A (en) | 2017-09-01 |
Family
ID=59720202
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| CN201710504473.9A Pending CN107120193A (en) | 2017-06-28 | 2017-06-28 | A kind of helicopter engine intake duct and helicopter |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111502828A (en) * | 2020-04-30 | 2020-08-07 | 中国直升机设计研究所 | Engine icing airworthiness air inlet structure and design method |
| CN112392601A (en) * | 2020-10-30 | 2021-02-23 | 中国直升机设计研究所 | Front output shaft engine coupling sand control device air inlet channel |
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| CN104507810A (en) * | 2012-07-30 | 2015-04-08 | 涡轮梅坎公司 | Helicopter engine air intake with improved bypass flow |
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| CN207195037U (en) * | 2017-06-28 | 2018-04-06 | 李兵长 | A kind of helicopter engine intake duct and helicopter |
-
2017
- 2017-06-28 CN CN201710504473.9A patent/CN107120193A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN111502828A (en) * | 2020-04-30 | 2020-08-07 | 中国直升机设计研究所 | Engine icing airworthiness air inlet structure and design method |
| CN112392601A (en) * | 2020-10-30 | 2021-02-23 | 中国直升机设计研究所 | Front output shaft engine coupling sand control device air inlet channel |
| CN112392601B (en) * | 2020-10-30 | 2022-05-17 | 中国直升机设计研究所 | Front output shaft engine coupling sand control device air inlet channel |
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