CN105667765A - Tail gas guiding device for lateral gas inflow helicopter - Google Patents
Tail gas guiding device for lateral gas inflow helicopter Download PDFInfo
- Publication number
- CN105667765A CN105667765A CN201610151336.7A CN201610151336A CN105667765A CN 105667765 A CN105667765 A CN 105667765A CN 201610151336 A CN201610151336 A CN 201610151336A CN 105667765 A CN105667765 A CN 105667765A
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- China
- Prior art keywords
- helicopter
- guiding device
- gas
- air inlet
- tail gas
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- 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.)
- Pending
Links
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 40
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 6
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a tail gas guiding device for a lateral gas inflow helicopter and relates to the technical field of helicopters. The tail gas guiding device (3) for the lateral gas inflow helicopter is arranged between a gas inlet (1) and a gas outlet (2) of the helicopter and used for isolating gas entering the gas inlet (1) from gas exhausted from the gas outlet (2). The tail gas guiding device (3) is fixedly connected with the outer surface of a helicopter body. The tail gas guiding device has the beneficial effects that the tail gas guiding device for the lateral gas inflow helicopter is arranged between the gas inlet and the gas outlet of the helicopter and can isolate inflow gas flow at the position of the gas inlet of the helicopter from tail gas at the position of the gas outlet of the helicopter, and therefore the tail gas exhausted from the gas outlet is prevented from being sucked in an engine from the gas inlet.
Description
Technical field
The present invention relates to Helicopter Technology field, be specifically related to a kind of side air inlet helicopter tail gas guiding device.
Background technology
The air inlet of side air inlet helicopter is arranged in the side of fuselage roof piggyback pod, electromotor sucks air either directly through the air inlet of side, the type helicopter is when flying backward, under the purling effect of rotor, tail gas is to the slightly biased flowing underneath of fore-body, exhaustor is positioned at the front of air inlet, and the tail gas of electromotor can be inhaled into air inlet. Owing to the oxygen content of tail gas is low, temperature is high, sucking tail gas and can cause that the oxygen content of engine charge declines, the output directly resulting in electromotor declines; Also result in engine charge air-flow uneven simultaneously, make engine behavior that sudden change to occur so that engine blade generation chatter phenomenon, the situation that engine power declines occurs. The phenomenon that helicopter flight height can be caused on these present helicopter flights of phenomenon synthesis exactly to sink suddenly, affects riding comfort and aerial mission execution efficiency. In this case, if the flying height of helicopter is relatively low, serious situation also results in air crash accident.
The problem that during for flying after alleviating, tail gas sucks electromotor, existing a kind of solution is by arranging air inlet and exhaustor in short transverse dislocation, as air inlet is arranged in top, exhaustor is arranged in middle part, after fly time, the exhaust flow directly arriving air inlet can be reduced, but this design need to increase the diversing flow system supporting with air inlet in piggyback pod, simultaneously because hot-fluid is usually from top outflow in piggyback pod cabin, this solution also results in electromotor and sucks the steam in piggyback pod, can cause that the intake efficiency of electromotor reduces; Another kind of solution is by being moved forward by air inlet, increase the horizontal range of air inlet and exhaustor, make in the horizontal range lengthened, more tail gas flows out downwards air inlet port regions, to reduce the tail gas suction volume of electromotor, but this design needs to increase air intake duct between air inlet and electromotor, adds the piggyback pod volume shared by air intake duct simultaneously, increase fuselage front face area, affect flight speed.
Summary of the invention
It is an object of the invention to provide a kind of side air inlet helicopter tail gas guiding device, to solve or the problem at least existing in mitigation technique background at least one place.
The technical solution used in the present invention is: provide a kind of side air inlet helicopter tail gas guiding device, described guiding device is arranged between the air inlet of helicopter and gas outlet, for isolating the gas entering described air inlet with from described gas outlet expellant gas, described guiding device is fixing with fuselage outer surface to be connected.
Preferably, described guiding device is curved slab.
Preferably, the projection on fuselage of the described curved slab has forward terminal and an aft terminal, and the angle flying direction before the line of described forward terminal and described aft terminal and helicopter is 30 ° to 60 °.
Preferably, the cross section being perpendicular to forward terminal and aft terminal line direction of described curved slab is triangle.
Preferably, the angle flying direction with fuselage before the line on the midpoint, base that the cross section of described curved slab contacts and corresponding summit and helicopter is 20 ° to 60 °.
Preferably, described curved slab height on fuselage is 30 millimeters to 200 millimeters.
The beneficial effects of the present invention is:
The side air inlet helicopter guiding device of the present invention is arranged between the air inlet of helicopter and gas outlet, it is possible to the charge air flow at isolation helicopter air inlet place and the tail gas at gas outlet place, to avoid the tail gas that gas outlet is discharged to be sucked from air inlet by electromotor.
Guiding device is set to the advantage of curved slab and is in that: simple in construction, lighter in weight, is conducive to air-flow to flow through, and reduces the resistance that helicopter is caused.
The cross section of curved slab is set to the advantage of triangle and is in that: curved slab is big with helicopter fuselage contact area, stable connection, and can reduce the volume of curved slab, thus alleviating the weight of curved slab.
The projection on fuselage of the described curved slab has forward terminal and an aft terminal, and the angle flying direction before the line of described forward terminal and described aft terminal and helicopter is 30 ° to 60 °, is conducive to the water conservancy diversion of tail gas and alleviates the resistance that helicopter is caused by curved slab.
The angle flying direction with fuselage before the line on the midpoint, base that the cross section of curved slab contacts and corresponding summit and helicopter is 20 ° to 60 °, is conducive to the water conservancy diversion of tail gas and alleviates the resistance that helicopter is caused by curved slab.
Accompanying drawing explanation
Fig. 1 is the scheme of installation of the side air inlet helicopter tail gas guiding device of one embodiment of the invention;
Fig. 2 is the guiding device shown in Fig. 1 and the angle schematic diagram flying direction before helicopter;
Fig. 3 is the installation schematic cross-section of the guiding device shown in Fig. 1.
Wherein, 1-air inlet, 2-gas outlet, 3-guiding device, 31-forward terminal, 32-aft terminal;
The angle in direction is flown before the line of A-forward terminal and aft terminal and helicopter;
The angle in direction is flown with fuselage before the line on the midpoint, base that the cross section of B-the present embodiment mean camber plate contacts and corresponding summit and helicopter;
H-curved slab height on fuselage.
Detailed description of the invention
For making purpose of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail. In the accompanying drawings, same or similar label represents same or similar element or has the element of same or like function from start to finish. Described embodiment is a part of embodiment of the present invention, rather than whole embodiments. The embodiment described below with reference to accompanying drawing is illustrative of, it is intended to is used for explaining the present invention, and is not considered as limiting the invention. Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention. Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " orientation or the position relationship of the instruction such as " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " be based on orientation shown in the drawings or position relationship; be for only for ease of the description present invention and simplifying and describe; rather than instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that limiting the scope of the invention.
As shown in Figure 1 to Figure 3, a kind of side air inlet helicopter tail gas guiding device, described guiding device 3 is arranged between the air inlet 1 of helicopter and gas outlet 2, for isolating the gas entering described air inlet 1 with from described gas outlet 2 expellant gas, described guiding device 3 is fixing with fuselage outer surface to be connected.
Guiding device 3 is arranged between the air inlet 1 of helicopter and gas outlet 2, the charge air flow at helicopter air inlet 1 place and the tail gas at gas outlet 2 place can be isolated, to avoid the tail gas that gas outlet 2 is discharged to be sucked from air inlet 1 by electromotor, sucking tail gas and can cause that the oxygen content of engine charge declines, the output directly resulting in electromotor declines; Also result in engine charge air-flow uneven simultaneously, make engine behavior that sudden change to occur so that engine blade generation chatter phenomenon, the situation that engine power declines occurs.
It is understood that described guiding device 3 can according to the feature specific design of aircraft self. Such as, in the present embodiment, guiding device 3 is curved slab. Have an advantage in that: simple in construction, lighter in weight, be conducive to air-flow to flow through, reduce the resistance that helicopter is caused. Described curved slab is fixing with the outer surface of fuselage to be connected, and will not change interior of aircraft structure, install simple and convenient.
In the present embodiment, curved slab projection on fuselage has forward terminal 31 and aft terminal 32, and the included angle A flying direction (from right to left for front flying direction in Fig. 2) before the line of forward terminal 31 and described aft terminal 32 and helicopter is 45 °.
It is understood that the included angle A flying direction before the line of forward terminal 31 and described aft terminal 32 and helicopter can also set according to practical situation. Such as, in an alternative embodiment, the included angle A flying direction before the line of forward terminal 31 and described aft terminal 32 and helicopter is 30 °; In another alternative, the included angle A flying direction before the line of forward terminal 31 and described aft terminal 32 and helicopter is 60 °; And the included angle A flying direction before the line of forward terminal 31 and described aft terminal 32 and helicopter can arbitrarily set according to the actual requirements between 30 ° to 60 °.
In the present embodiment, the angle flying direction before the line of forward terminal and aft terminal and helicopter is 30 ° to 60 °, has an advantage in that: is conducive to the water conservancy diversion of tail gas and alleviates the resistance that helicopter is caused by curved slab.
In the present embodiment, the cross section being perpendicular to forward terminal and aft terminal line direction of curved slab is triangle. Have an advantage in that: curved slab is big with helicopter fuselage contact area, stable connection, and can reduce the volume of curved slab, thus alleviating the weight of curved slab.
In the present embodiment, the included angle B flying direction before the line being perpendicular to midpoint, base that forward terminal contacts with fuselage and corresponding summit with the cross section in aft terminal line direction of described curved slab and helicopter is 45 °.
It is understood that the included angle B flying direction before the line on the midpoint, base that contacts with fuselage, the cross section of described curved slab and corresponding summit and helicopter can also set according to practical situation. Such as, in an alternative embodiment, the included angle B flying direction with fuselage before the line on the midpoint, base that the cross section of curved slab contacts and corresponding summit and helicopter is 20 °; In another alternative, the included angle B flying direction with fuselage before the line on the midpoint, base that the cross section of curved slab contacts and corresponding summit and helicopter is 60 degree; And the included angle B flying direction before the line on the midpoint, base that contacts with fuselage, the cross section of curved slab and corresponding summit and helicopter arbitrarily can set as required between 20 ° to 60 °.
The angle flying direction with fuselage before the line on the midpoint, base that the cross section of curved slab contacts and corresponding summit and helicopter is 20 ° to 60 °, has an advantage in that: is conducive to the water conservancy diversion of tail gas and alleviates the resistance that helicopter is caused by curved slab.
In the present embodiment, described curved slab height H on fuselage is 100 millimeters.
It is understood that the height H that curved slab is on fuselage can set according to actual needs. Such as, in an alternative enforcement, curved slab height H on fuselage is 30 millimeters; In in another alternative enforcement, curved slab height H on fuselage is 200 millimeters; And the height H that curved slab is on fuselage arbitrarily can set between 30 millimeters to 200 millimeters.
It is understandable that, the setting of included angle B flying direction with fuselage before the line on the midpoint, base that the cross section of curved slab contacts and corresponding summit and helicopter should consider with the setting of described curved slab height H on fuselage, height at the premise lower surface camber plate ensureing water conservancy diversion effect should reduce as far as possible, and then alleviates the weight of curved slab.
It is understandable that, when the flight resistance that helicopter is caused by curved slab does not affect its flying quality, distance between forward terminal and the aft terminal of curved slab is the size in this line direction more than air inlet 1 and gas outlet 2 preferably, and namely the forward terminal of curved slab should be big as much as possible with the distance of aft terminal; Meanwhile, the height H of curved slab also should choose higher value as far as possible, to improve the water conservancy diversion effect that gas outlet 2 is discharged tail gas.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit. Although the present invention being described in detail with reference to previous embodiment, it will be understood by those within the art that: the technical scheme described in foregoing embodiments still can be modified by it, or wherein portion of techniques feature is carried out equivalent replacement; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (6)
1. a side air inlet helicopter tail gas guiding device, it is characterized in that: described guiding device (3) is arranged between the air inlet (1) of helicopter and gas outlet (2), for isolating the gas entering described air inlet (1) with from described gas outlet (2) expellant gas, described guiding device (3) is fixing with fuselage outer surface to be connected.
2. air inlet helicopter tail gas guiding device in side as claimed in claim 1, it is characterised in that: described guiding device (3) is curved slab.
3. air inlet helicopter tail gas guiding device in side as claimed in claim 2, it is characterized in that: the projection on fuselage of the described curved slab has forward terminal (31) and an aft terminal (32), the angle flying direction before the line of described forward terminal (31) and described aft terminal (32) and helicopter is 30 ° to 60 °.
4. air inlet helicopter tail gas guiding device in side as claimed in claim 3, it is characterised in that: the cross section being perpendicular to forward terminal (31) and aft terminal (32) line direction of described curved slab is triangle.
5. air inlet helicopter tail gas guiding device in side as claimed in claim 4, it is characterised in that: the angle flying direction with fuselage before the line on the midpoint, base that the cross section of described curved slab contacts and corresponding summit and helicopter is 20 ° to 60 °.
6. air inlet helicopter tail gas guiding device in side as claimed in claim 3, it is characterised in that: described curved slab height on fuselage is 30 millimeters to 200 millimeters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610151336.7A CN105667765A (en) | 2016-03-17 | 2016-03-17 | Tail gas guiding device for lateral gas inflow helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610151336.7A CN105667765A (en) | 2016-03-17 | 2016-03-17 | Tail gas guiding device for lateral gas inflow helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105667765A true CN105667765A (en) | 2016-06-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610151336.7A Pending CN105667765A (en) | 2016-03-17 | 2016-03-17 | Tail gas guiding device for lateral gas inflow helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105667765A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3940097A (en) * | 1974-06-25 | 1976-02-24 | The United States Government As Represented By The National Aeronautics And Space Administration Office Of General Counsel-Code Gp | Exhaust flow deflector |
| US6123290A (en) * | 1994-12-19 | 2000-09-26 | Eurocopter France | Helicopters equipped with jet dilution/deflection means for the combustion gases |
| US7192462B2 (en) * | 2004-04-14 | 2007-03-20 | Aerospace Filtration Systems, Inc. | Engine air filter and sealing system |
| CN101549758A (en) * | 2009-05-13 | 2009-10-07 | 南京航空航天大学 | Intake and exhaust device of air breathing supersonic/hypersonic aerocraft |
| DE202011102025U1 (en) * | 2011-06-18 | 2011-07-21 | Christian Fuchs | Improving the operational field of vision of aircraft |
| KR20120054235A (en) * | 2010-11-19 | 2012-05-30 | 한국항공우주산업 주식회사 | Infrared suppressor of helicopter |
| CN205022877U (en) * | 2015-09-28 | 2016-02-10 | 湖北易瓦特科技股份有限公司 | A passageway for air current switches on |
-
2016
- 2016-03-17 CN CN201610151336.7A patent/CN105667765A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3940097A (en) * | 1974-06-25 | 1976-02-24 | The United States Government As Represented By The National Aeronautics And Space Administration Office Of General Counsel-Code Gp | Exhaust flow deflector |
| US6123290A (en) * | 1994-12-19 | 2000-09-26 | Eurocopter France | Helicopters equipped with jet dilution/deflection means for the combustion gases |
| US7192462B2 (en) * | 2004-04-14 | 2007-03-20 | Aerospace Filtration Systems, Inc. | Engine air filter and sealing system |
| CN101549758A (en) * | 2009-05-13 | 2009-10-07 | 南京航空航天大学 | Intake and exhaust device of air breathing supersonic/hypersonic aerocraft |
| KR20120054235A (en) * | 2010-11-19 | 2012-05-30 | 한국항공우주산업 주식회사 | Infrared suppressor of helicopter |
| DE202011102025U1 (en) * | 2011-06-18 | 2011-07-21 | Christian Fuchs | Improving the operational field of vision of aircraft |
| CN205022877U (en) * | 2015-09-28 | 2016-02-10 | 湖北易瓦特科技股份有限公司 | A passageway for air current switches on |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160615 |
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| RJ01 | Rejection of invention patent application after publication |