CN107120193B - Engine air inlet device for helicopter and helicopter - Google Patents
Engine air inlet device for helicopter and helicopter Download PDFInfo
- Publication number
- CN107120193B CN107120193B CN201710504473.9A CN201710504473A CN107120193B CN 107120193 B CN107120193 B CN 107120193B CN 201710504473 A CN201710504473 A CN 201710504473A CN 107120193 B CN107120193 B CN 107120193B
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- sand
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- air inlet
- air
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- 239000000428 dust Substances 0.000 claims abstract description 101
- 238000000926 separation method Methods 0.000 claims abstract description 53
- 239000004576 sand Substances 0.000 claims abstract description 43
- 238000007789 sealing Methods 0.000 claims description 14
- 238000010438 heat treatment Methods 0.000 description 12
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000008014 freezing Effects 0.000 description 2
- 238000007710 freezing Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002452 interceptive effect 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
- 238000006467 substitution reaction Methods 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
- F02C7/055—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention discloses an engine air inlet device for a helicopter and the helicopter. The engine air intake device for a helicopter comprises: an engine air inlet channel, one end of which is connected with the engine; the sand-dust separation device is connected with the engine mounting platform and comprises a sand-dust separation body, wherein the sand-dust separation body is provided with an inner cavity and a first air port, and the space in the inner cavity is a first air inlet space; the first air port is arranged at a distance from an air inlet of an engine air inlet channel, and a space between the first air port and the air inlet channel is a second air inlet space; the telescopic communication device is connected with the sand-dust separation device and comprises a telescopic air duct, and the telescopic air duct can move, so that the telescopic air duct has a closed communication position and an open position. When the air conditioner flies in the sand and dust environment, external air enters from the first air inlet space through the telescopic air duct, and the air in the first air inlet space is separated from the sand and dust through the sand and dust separating device, so that the problem of flying in the sand and dust environment in the landing and the dust environment is solved.
Description
Technical Field
The invention relates to the technical field of helicopter engine air intake, in particular to an engine air intake device for a helicopter and the helicopter.
Background
In the prior art, an engine air inlet device of a helicopter is mainly provided with an air inlet channel before an engine compressor is used for air inlet, and a sand and dust separation device is additionally arranged in front of the air inlet channel.
The core of the sand-dust separation device is that a large number of vortex tube particle separators are arranged, when air passes through the vortex tubes, sand dust is separated, and clean air enters an engine air compressor.
The prior art has the following defects:
After the sand-dust separation device is added in front of the engine air inlet channel, the air inlet pressure loss of the engine is increased, so that the power loss is increased, and the available power is reduced;
when the sand-dust separation device is used in an icing environment, the sand-dust separation device can only meet 30-minute working capacity of partial navigability standards. Over time, the vortex tube can gradually freeze, the air inlet pressure loss of the engine is continuously increased, the power loss is larger and larger, and finally, the vortex tube can be blocked by the icing, so that the engine is flameout;
the heating anti-icing passage is long, a large amount of bleed air or power supply is needed, and the power loss of the engine is large.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide an engine air intake for a helicopter that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
In order to achieve the above object, the present invention provides an engine intake apparatus for a helicopter, comprising:
The engine air inlet is connected with the engine at one end;
The sand-dust separation device is connected with the engine mounting platform and comprises a sand-dust separation body, the sand-dust separation body is provided with an inner cavity and a first air port, and the space in the inner cavity is a first air inlet space;
the first air port is opposite to and spaced from an air inlet of the engine air inlet channel, and a space between the first air port and the air inlet is a second air inlet space;
The telescopic communication device is connected with the sand-dust separation device or the sand-dust separation device and the engine air inlet channel and comprises a telescopic air duct which can move so as to have a closed communication position and an open position; wherein,
In the closed communication position, the first air port is communicated with the air inlet through the telescopic air duct, so that external air only enters the engine air inlet channel from the first air inlet space;
in the open position, external air provides air for the engine air inlet through the second air inlet space or the external air provides air for the engine air inlet through the first air inlet space and the second air inlet space together.
Preferably, the telescopic communication device is arranged in the inner cavity of the sand-dust separation device and is connected with the sand-dust separation device.
Preferably, the telescopic communication device further comprises:
the driving device is arranged in the inner cavity of the sand-dust separation device and is provided with an output end;
One end of the telescopic mechanism is connected with the output end, and the other end of the telescopic mechanism is communicated with the telescopic air duct; wherein,
The telescopic mechanism can be driven by the driving device to perform telescopic movement, so that the telescopic air duct is driven to be switched between the closed communication position and the open position.
Preferably, the driving device is a motor;
The telescopic mechanism comprises a worm and a driving bracket, and one end of the worm is connected with the output end of the motor;
The driving bracket is arranged on the worm;
the telescopic air duct is arranged on the driving bracket; wherein,
The motor is capable of powering the worm;
the worm rotates through the power, so that the driving support is driven to perform linear motion.
Preferably, the telescopic communication device further comprises: an elastic sealing lip arranged on one end face of the annular air duct; the elastic sealing ring is arranged on the other end face of the annular air duct; and in the closed communication position, the end face of the annular air duct, which is provided with the elastic sealing lip, abuts against the air inlet, and the other end face of the annular air duct contacts with the wall surface of the inner cavity of the sand-dust separation device.
Preferably, one end face of the sand-dust separation body is the first air port;
the sand-dust separation body is provided with a sand-dust separation pipe and a sand discharge channel;
the sand-dust separation pipe is communicated with the wall surface of the sand-dust separation body;
The sand discharge channel is communicated with the sand-dust separation pipe.
Preferably, the sand-dust separation device further comprises a sand discharge pipe, and the sand discharge pipe is communicated with the sand discharge channel.
Preferably, the sand-dust separating device further includes a heating anti-icing lip disposed on the first tuyere.
Preferably, the air inlet of the engine air inlet channel is of a flaring type.
The application also provides a helicopter, which comprises an engine and an engine air inlet device for the helicopter, wherein the engine air inlet device for the helicopter is connected with the engine, and the engine air inlet device for the helicopter is the engine air inlet device for the helicopter.
The engine air inlet device for the helicopter is controlled through the telescopic air duct, so that whether external air enters from the second air inlet space or the first air inlet space can be selected according to requirements.
When the air conditioner flies in the sand and dust environment, external air enters from the first air inlet space through the telescopic air duct, and the air in the first air inlet space is separated from the sand and dust through the sand and dust separating device, so that the problem of flying in the sand and dust environment in the landing and the dust environment is solved.
When the helicopter is not in a dust environment, the telescopic air duct is adjusted to an open position, and most or all of external air enters the engine air inlet channel through the second air inlet space, so that power loss is reduced.
In addition, with this structure, even if the air conditioner freezes the dust separating pipe in the dust separating device, the engine can be normally charged without impeding the charging of the engine due to the freezing of the dust separating device, since the position adjustment can be performed by the telescopic communication device, and the telescopic duct is adjusted to the open position.
Drawings
Fig. 1 is a schematic structural view of an engine intake apparatus for a helicopter according to a first embodiment of the invention, in which a telescopic duct is located at a closed communication position.
Fig. 2 is another schematic structural view of the engine intake apparatus for a helicopter of the embodiment of fig. 1, wherein the telescopic air duct is located in an open position.
Fig. 3 is a schematic cross-sectional view of the engine intake apparatus for a helicopter of the embodiment of fig. 1, wherein the telescopic air duct is located in a closed communication position.
Fig. 4 is a schematic cross-sectional view of the engine intake for a helicopter of the embodiment of fig. 1 wherein the telescoping tunnel is in an open position.
Fig. 5 is a schematic view of the structure of an engine intake passage in the engine intake apparatus for a helicopter of the embodiment shown in fig. 1.
Fig. 6 is a schematic structural view of the telescopic communication device in the engine intake apparatus for a helicopter of the embodiment shown in fig. 1.
Fig. 7 is a schematic view of the structure of the dust separating apparatus in the engine air intake apparatus for a helicopter of the embodiment shown in fig. 1.
Reference numerals:
1. engine intake duct 11 air inlet
2. Sand and dust separating device 52 driving device
21. Telescopic mechanism of sand-dust separating body 53
211. Inner cavity 54 elastic sealing lip
212. Elastic sealing ring of first air port 55
3. First air inlet space 221 sand-dust separating pipe
4. Second air inlet space 222 sand discharge channel
5. Sand discharging pipe of telescopic communication device 223
51. Expansion air duct 224 heating anti-icing lip
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention become more apparent, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present invention.
Fig. 1 is a schematic structural view of an engine intake apparatus for a helicopter according to a first embodiment of the invention, in which a telescopic duct is located at a closed communication position. Fig. 2 is another schematic structural view of the engine intake apparatus for a helicopter of the embodiment of fig. 1, wherein the telescopic air duct is located in an open position. Fig. 3 is a schematic cross-sectional view of the engine intake apparatus for a helicopter of the embodiment of fig. 1, wherein the telescopic air duct is located in a closed communication position. Fig. 4 is a schematic cross-sectional view of the engine intake for a helicopter of the embodiment of fig. 1 wherein the telescoping tunnel is in an open position. Fig. 5 is a schematic view of the structure of an engine intake passage in the engine intake apparatus for a helicopter of the embodiment shown in fig. 1. Fig. 6 is a schematic structural view of the telescopic communication device in the engine intake apparatus for a helicopter of the embodiment shown in fig. 1. Fig. 7 is a schematic view of the structure of the dust separating apparatus in the engine air intake apparatus for a helicopter of the embodiment shown in fig. 1.
The engine intake device for a helicopter shown in fig. 1 to 4 includes an engine intake duct 1, a telescopic communication device 5, and a dust separating device 2.
One end of an engine air inlet channel 1 is connected with an engine; the sand-dust separation device 2 is connected with the engine mounting platform, the sand-dust separation device 2 comprises a sand-dust separation body 21, the sand-dust separation body 21 is provided with an inner cavity 211 and a first air port 212, and the space in the inner cavity 211 is a first air inlet space 3; the first air port 212 is opposite to and spaced from the air inlet 11 of the engine air inlet 1, and the space between the first air port 212 and the air inlet 11 is the second air inlet space 4; the telescopic communication device 5 is connected with the sand-dust separation device 2, the telescopic communication device 5 comprises a telescopic air duct 51, and the telescopic air duct 51 can move so as to have a closed communication position and an open position; in the closed communication position (the position shown in fig. 1 and 3), the first air port 212 communicates with the air inlet 11 through the telescopic air duct 51, so that the external air enters the engine air intake passage only from the first air intake space.
In the open position (the position shown in fig. 2 and 4), the external air is supplied from the first intake space 3 together with the second intake space 4 to the engine intake.
The engine air inlet device for the helicopter is controlled through the telescopic air duct, so that whether external air enters from the second air inlet space or the first air inlet space can be selected according to requirements.
When the air conditioner flies in the sand and dust environment, external air enters from the first air inlet space through the telescopic air duct, and the air in the first air inlet space is separated from the sand and dust through the sand and dust separating device, so that the problem of flying in the sand and dust environment in the landing and the dust environment is solved.
When the helicopter is not in a dust environment, the telescopic air duct is adjusted to an open position, and most or all of external air enters the engine air inlet channel through the second air inlet space, so that power loss is reduced.
In addition, with this structure, even if the air conditioner freezes the dust separating pipe in the dust separating device, the engine can be normally charged without impeding the charging of the engine due to the freezing of the dust separating device, since the position adjustment can be performed by the telescopic communication device, and the telescopic duct is adjusted to the open position.
It will be appreciated that in an alternative embodiment, the telescopic means is connected to the dust separating means and the engine inlet.
It will be appreciated that in an alternative embodiment, in the open position, external air is supplied from the second intake space 4 to the engine intake. In this alternative embodiment, this may be achieved by the sand-dust separation device closing off its own first air inlet space.
Referring to fig. 5, in the present embodiment, an intake port heating device is provided on an engine intake port 1, by which the intake port can be heated, thereby preventing icing of the intake port. It will be appreciated that the inlet heating means may be heated by engine induced heating or by electrical heating.
Referring to fig. 1 to 4, in the present embodiment, the telescopic communication means 5 is provided in the inner cavity 211 of the dust separating apparatus 2 and is connected to the dust separating apparatus 2. The telescopic communication device 5 is arranged in the inner cavity of the sand-dust separation device 2, so that the layout space can be saved, the layout is convenient, and the telescopic communication device can be prevented from interfering the engine to enter air.
Referring to fig. 3, 4 and 6, in the present embodiment, the telescopic communication device 5 further includes a driving device 52 and a telescopic mechanism 53, the driving device 52 is installed in the inner cavity of the sand-dust separating device 2, and the driving device 52 has an output end; one end of the telescopic mechanism 53 is connected with the output end, and the other end of the telescopic mechanism 53 is communicated with the telescopic air duct 51; the telescopic mechanism 53 can be driven by the driving device 52 to perform telescopic movement, so as to drive the telescopic air duct 51 to switch between a closed communication position and an open position.
Specifically, in the present embodiment, the driving device is a motor. The telescopic mechanism 53 comprises a worm and a driving bracket, and one end of the worm is connected with the output end of the motor; the driving bracket is arranged on the worm; the telescopic air duct is arranged on the driving bracket; wherein the motor is capable of powering the worm; the worm rotates through power, so that the driving support is driven to perform linear motion. The worm driving mode is adopted, so that the problems of connection difficulty and reliability caused by air supply, power supply, pressure supply and the like for the telescopic communication device are avoided.
It will be appreciated that the telescopic communication means may also take other forms. For example, the telescopic mechanism adopts a movement mode of a gear rack and the like.
Referring to fig. 6, in the present embodiment, the telescopic communication device 5 further includes an elastic sealing lip 54 and an elastic sealing ring 55, the elastic sealing lip 54 being provided on one end face of the telescopic duct 51; the elastic sealing ring 55 is arranged on the other end face of the telescopic air duct 51; in the closed communication position, the end face of the telescopic air duct 51, on which the elastic sealing lip 54 is arranged, abuts against the air inlet 11, and the other end face contacts with the wall surface of the inner cavity of the sand-dust separating device 2. In this way, it is ensured that in the closed communication position, outside air enters the engine intake duct only from the first intake space. I.e. all the external air is passed through the sand-dust separation device to make sand-dust separation.
Referring to fig. 7, in the present embodiment, one end surface of the sand-dust separating body 21 is a first tuyere; the sand-dust separation body 21 is provided with a sand-dust separation pipe 221, a sand discharge passage 222, and a sand discharge pipe 223; the sand-dust separation pipe 221 communicates with the wall surface of the sand-dust separation body 21; the sand discharge passage 222 communicates with the sand and dust separating pipe 221. The sand discharge pipe 223 communicates with the sand discharge passage 222.
When the sand-dust separating device works, external air enters from the sand-dust separating pipe and is separated through the sand-dust separating pipe, so that sand dust is discharged into the sand discharge channel and enters the sand discharge pipe through the sand discharge channel, and is discharged.
Advantageously, in an alternative embodiment, a dust collection device is added to prevent the exhausted dust from entering other parts of the helicopter.
In this embodiment, the sand and dust separating apparatus further includes a heating anti-icing lip 224, and the heating anti-icing lip 224 is disposed on the first tuyere. By providing the heating ice-preventing lip 224, it is possible to prevent the sand-dust separating apparatus from losing performance due to ice formation when the helicopter flies in the ice formation region.
In this embodiment, when the telescopic air duct 51 in the telescopic communication device 5 is in the closed communication position (the position shown in fig. 1 and 3), the first air port 212 is communicated with the air inlet 11 through the telescopic air duct 51, that is, an integrated space of the engine air inlet, the telescopic air duct and the sand-dust separation device is formed, in this space, the heating anti-icing device (prior art) is disposed on the engine air inlet, and the heating anti-icing lip is disposed on the sand-dust separation device, so that in use, this integrated space can be heated in real time, and the space is prevented from icing, thereby affecting the engine operation.
Advantageously, in an alternative embodiment, the intake of the engine intake is of the flared type. By adopting the structure, the second air inlet space can have a stamping effect when the helicopter flies forward, so that the power loss of the engine is further reduced.
The application also provides a helicopter, which comprises an engine and an engine air inlet device for the helicopter, wherein the engine air inlet device for the helicopter is connected with the engine.
Finally, it should be pointed out that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting. Although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. An engine air intake device for a helicopter, characterized in that the engine air intake device for a helicopter comprises:
The engine air inlet channel (1), one end of the engine air inlet channel (1) is connected with the engine;
The sand-dust separation device (2), the sand-dust separation device (2) is connected with an engine mounting platform, the sand-dust separation device (2) comprises a sand-dust separation body (21), the sand-dust separation body (21) is provided with an inner cavity (211) and a first air port (212), and a space in the inner cavity (211) is a first air inlet space (3);
The first air port (212) is opposite to and spaced from the air inlet (11) of the engine air inlet channel (1), and a space between the first air port (212) and the air inlet (11) is a second air inlet space (4);
The telescopic communication device (5) is connected with the sand-dust separation device (2) and the engine air inlet passage at a closed communication position, the telescopic communication device (5) comprises a telescopic air duct (51), and the telescopic air duct (51) can move so as to have the closed communication position and an open position; wherein,
In the closed communication position, the first air port (212) is communicated with the air inlet (11) through the telescopic air duct (51), so that external air only enters the engine air inlet channel from the first air inlet space;
In the open position, external air is supplied from the second intake space (4) to the engine intake.
2. Engine intake device for helicopters according to claim 1, wherein the telescopic communication means (5) are arranged in the inner chamber (211) of the dust-sand separating device (2) and are connected to the dust-sand separating device (2).
3. Engine intake device for helicopters according to claim 2, wherein the telescopic communication means (5) further comprise:
the driving device (52) is arranged in the inner cavity of the sand-dust separation device (2), and the driving device (52) is provided with an output end;
The telescopic mechanism (53), one end of the telescopic mechanism (53) is connected with the output end, and the other end of the telescopic mechanism (53) is communicated with the telescopic air duct (51); wherein,
The telescopic mechanism (53) can be driven by the driving device (52) to perform telescopic movement, so that the telescopic air duct (51) is driven to switch between the closed communication position and the open position.
4. An engine intake for a helicopter according to claim 3 wherein said drive means is an electric motor;
The telescopic mechanism (53) comprises a worm and a driving bracket, and one end of the worm is connected with the output end of the motor;
The driving bracket is arranged on the worm;
the telescopic air duct is arranged on the driving bracket; wherein,
The motor is capable of powering the worm;
the worm rotates through the power, so that the driving support is driven to perform linear motion.
5. An engine intake device for a helicopter according to claim 4 characterized in that said telescopic communication means (5) further comprise:
An elastic sealing lip (54), wherein the elastic sealing lip (54) is arranged on one end face of the telescopic air duct (51);
The elastic sealing ring (55) is arranged on the other end face of the telescopic air duct (51);
In the closed communication position, the end face of the telescopic air duct (51) provided with the elastic sealing lip (54) abuts against the air inlet (11), and the other end face is in contact with the wall surface of the inner cavity of the sand-dust separation device (2).
6. Engine intake for a helicopter according to any one of claims 1 to 5, characterized in that one end face of said dust-sand separating body (21) is said first tuyere;
the sand-dust separation body (21) is provided with a sand-dust separation pipe (221) and a sand discharge channel (222);
the sand-dust separation pipe (221) is communicated with the wall surface of the sand-dust separation body (21);
the sand discharge channel (222) is communicated with the sand-dust separation pipe (221).
7. The engine intake apparatus for a helicopter of claim 6 wherein said dust and sand separating apparatus further comprises a sand discharge pipe (223), said sand discharge pipe (223) communicating with said sand discharge passage (222).
8. The engine intake apparatus for a helicopter of claim 6 wherein said dust and sand separating apparatus further comprises a heated anti-icing lip (224), said heated anti-icing lip (224) being disposed over said first tuyere.
9. The engine intake apparatus for a helicopter according to claim 1, wherein an intake port of the engine intake duct is of a flaring type.
10. A helicopter, characterized in that the helicopter comprises an engine and an engine intake for a helicopter connected to the engine, the engine intake for a helicopter being as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710504473.9A CN107120193B (en) | 2017-06-28 | 2017-06-28 | Engine air inlet device for helicopter and helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710504473.9A CN107120193B (en) | 2017-06-28 | 2017-06-28 | Engine air inlet device for helicopter and helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107120193A CN107120193A (en) | 2017-09-01 |
| CN107120193B true CN107120193B (en) | 2024-05-03 |
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| CN201710504473.9A Active CN107120193B (en) | 2017-06-28 | 2017-06-28 | Engine air inlet device for helicopter and helicopter |
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Families Citing this family (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 |
| 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 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1401187A (en) * | 1971-11-25 | 1975-07-16 | Secr Defence | Helicopter engine intakes |
| US3998048A (en) * | 1973-11-09 | 1976-12-21 | Societe Nationale Industrielle Aerospatiale | Ram air intakes of rotary-wing aircraft turbine engines |
| CN101131123A (en) * | 2006-07-19 | 2008-02-27 | 尤洛考普特公司 | Multifunctional air inlet of turbine engine |
| CN103821615A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Engine gas inlet protection device |
| CN104507810A (en) * | 2012-07-30 | 2015-04-08 | 涡轮梅坎公司 | Helicopter engine air intake with improved bypass flow |
| CN106523158A (en) * | 2016-11-09 | 2017-03-22 | 南京航空航天大学 | Turboshaft engine intake device and operation method |
| 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/CN107120193B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1401187A (en) * | 1971-11-25 | 1975-07-16 | Secr Defence | Helicopter engine intakes |
| US3998048A (en) * | 1973-11-09 | 1976-12-21 | Societe Nationale Industrielle Aerospatiale | Ram air intakes of rotary-wing aircraft turbine engines |
| CN101131123A (en) * | 2006-07-19 | 2008-02-27 | 尤洛考普特公司 | Multifunctional air inlet of turbine engine |
| CN104507810A (en) * | 2012-07-30 | 2015-04-08 | 涡轮梅坎公司 | Helicopter engine air intake with improved bypass flow |
| CN103821615A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Engine gas inlet protection device |
| CN106523158A (en) * | 2016-11-09 | 2017-03-22 | 南京航空航天大学 | Turboshaft engine intake device and operation method |
| CN207195037U (en) * | 2017-06-28 | 2018-04-06 | 李兵长 | A kind of helicopter engine intake duct and helicopter |
Non-Patent Citations (1)
| Title |
|---|
| 直升机发动机进气防护装置探讨;吕品;信息化建设(第05期);第338页 * |
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