CN115489740A - Helicopter engine air inlet sand discharging device with abrasion-proof axial flow fan blades - Google Patents
Helicopter engine air inlet sand discharging device with abrasion-proof axial flow fan blades Download PDFInfo
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- CN115489740A CN115489740A CN202211174193.3A CN202211174193A CN115489740A CN 115489740 A CN115489740 A CN 115489740A CN 202211174193 A CN202211174193 A CN 202211174193A CN 115489740 A CN115489740 A CN 115489740A
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- 239000004576 sand Substances 0.000 title claims abstract description 151
- 238000007599 discharging Methods 0.000 title claims abstract description 33
- 238000000926 separation method Methods 0.000 claims abstract description 38
- 239000000428 dust Substances 0.000 claims abstract description 36
- 238000002347 injection Methods 0.000 claims abstract description 19
- 239000007924 injection Substances 0.000 claims abstract description 19
- 238000005192 partition Methods 0.000 claims description 14
- 238000009792 diffusion process Methods 0.000 claims description 9
- 230000007423 decrease Effects 0.000 claims 1
- 238000005299 abrasion Methods 0.000 abstract description 5
- 239000002245 particle Substances 0.000 description 7
- 230000009471 action Effects 0.000 description 6
- 230000002093 peripheral effect Effects 0.000 description 5
- 239000000243 solution Substances 0.000 description 4
- 238000001914 filtration Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 244000035744 Hura crepitans Species 0.000 description 1
- 239000003570 air Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012876 topography Methods 0.000 description 1
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- 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0246—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising particle separators
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- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
A helicopter engine air inlet sand discharge device with abrasion-proof axial flow fan blades comprises a sand-dust separation device and a sand-dust discharge device; the sand-dust separation device comprises a panel component and a vortex pipe separator, a sand collecting box and a gas collecting box are formed by the panel component, the vortex pipe separator is arranged in the sand collecting box, an air inlet hole and an air outlet hole are formed in the sand collecting box, a pipe body of the vortex pipe separator is provided with a sand discharge channel communicated with the sand collecting box, sand-containing air is introduced into the vortex pipe separator through the air inlet hole, and clean air is introduced into the gas collecting box through the air outlet hole; the sand and dust discharging device comprises an injection sand discharging pipe, an air guide pipeline, an axial flow fan, a main air outlet pipe and a cyclone separator, wherein the injection sand discharging pipe is communicated with a sand collecting box, a side surface of the injection sand discharging pipe is provided with a bypass port and is communicated with a gas collecting box through the air guide pipeline, the axial flow fan is arranged in the air guide pipeline, the cyclone separator is arranged between the axial flow fan and the gas collecting box, and the gas collecting box is provided with a main air outlet. The invention can avoid the abrasion of sand grains to the fan and improve the sand discharge efficiency.
Description
Technical Field
The invention belongs to the technical field of air inlet of a helicopter engine, and particularly relates to an abrasion-proof sand discharging device for an air inlet of a helicopter engine, which comprises an axial flow fan blade and a sand discharging device.
Background
Because of their special purpose and small size, helicopters are often used for fast, short-haul flights and are not very demanding on the flight site. Helicopters often land in the field and take off and land in different climates, and special take-off and land topography and environment require that the engine inlet be provided with a sand control device. The sand control device at the inlet of the helicopter aims to purify air, reduce the sand content of gas entering an engine and prevent sand grains from abrading blades. They are generally classified into vortex tube separators, integral particle separators and barrier particle separators according to the principle and location of sand discharge. Both the vortex tube separator and the integral particle separator utilize inertia principle to separate gas from solid by means of gravity and centrifugal force. The vortex tube type separator is an independent component and is arranged in front of an air inlet of the helicopter engine; and the integral particle separator is part of the engine. The barrier particle separator is different from the former two in principle, and adopts a fiber layer net material to adhere particles in air. At present, the vortex tube type separator is commonly used, is used as an independent device, is convenient to disassemble and replace, and has high separation efficiency and light weight.
The sand discharging device is provided with a sand dust discharging device besides a gas-solid separation device. At present, axial flow fans are mostly adopted on helicopters, and sand grains in a sand box are discharged to the outside by utilizing the pressure difference generated by the front and the back of the blades when the axial flow fan blades rotate. Axial fan is located sand discharge box exit, and the sand grain can wear and tear the blade when discharging, influences the fan life-span, and needs regularly to change.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and provides a sand discharging device for an air inlet of a helicopter engine, which prevents abrasion of axial flow fan blades, improves sand discharging efficiency, reduces the frequency of replacing the fan and saves economic cost.
In order to achieve the purpose, the invention has the following technical scheme:
a kind of axial fan blade abrasionproof helicopter engine air inlet sand discharge device, including sand dust separator and sand dust exhaust apparatus; the sand-dust separation device comprises a panel component and a vortex pipe separator, wherein a separated sand collecting box and a separated gas collecting box are formed by the panel component, the vortex pipe separator is arranged in the sand collecting box, an air inlet hole and an air outlet hole are formed in the sand collecting box, a pipe body of the vortex pipe separator is provided with a sand discharge channel communicated with the sand collecting box, sand-containing air is introduced into the vortex pipe separator through the air inlet hole, and clean air separated by the vortex pipe separator is introduced into the gas collecting box through the air outlet hole;
the sand and dust discharging device comprises an injection sand discharge pipe, an air guide pipeline, an axial flow fan, a main air outlet pipe and a cyclone separator, wherein the injection sand discharge pipe is communicated with a sand collecting box, a side face of the injection sand discharge pipe is provided with a bypass port and is communicated with a gas collecting box through the air guide pipeline, the axial flow fan is installed in the air guide pipeline, the cyclone separator is arranged between the axial flow fan and the gas collecting box, a main air outlet is formed in the gas collecting box, and the main air outlet of the gas collecting box and an air inlet of a helicopter engine are connected through the main air outlet pipe.
Preferably, the panel components includes top panel, middle partition panel, lower panel and week side panel, the top panel is opened there are a plurality of round hole as the inlet port, middle partition panel is opened and is had a plurality of round hole as the exhaust hole, constitutes the sand-collecting box through top panel, middle partition panel, week side panel, constitutes the gas tank through middle partition panel, lower panel and week side panel.
Preferably, the upper panel is provided with 9 × 9 uniformly distributed round holes as air inlet holes, the middle separation panel is provided with 9 × 9 uniformly distributed round holes as air outlet holes at positions corresponding to the air inlet holes of the upper panel, the number of the vortex tube separators is 9 × 9, and a vortex tube separator is correspondingly connected between each pair of air inlet holes and air outlet holes.
Preferably, the face plates of the sand collecting box and the gas collecting box respectively extend forwards and converge, and only one circular opening is reserved at the converging end and is respectively used as a sand discharge port and a main air outlet; the sand ejecting pipe is connected to the circular opening of the sand collecting box, the main air outlet pipe is connected to the circular opening of the air collecting box, a side port is formed in the side face of the main air outlet pipe, and the air guide pipeline is connected between the main air outlet pipe and the side port of the sand ejecting pipe.
Preferably, the swirl tube separator consists of a swirl tube and a separation section; the vortex tube comprises a vortex blade arranged in a section of the circular tube and a blade central body for mounting the vortex blade, and an air inlet is arranged above the vortex blade; the separation section is a trumpet-shaped diffusion main flow pipe, the diameter of the separation section is gradually increased from the air inlet to the air outlet, and a section of separation section with the same diameter is arranged at the air outlet; the inner diameter of the vortex tube is larger than the outer diameter of the air inlet of the separation section; the vortex pipe is sleeved outside the separation section, and a clearance between the vortex pipe and the separation section forms a sand discharge channel; the central line of the vortex tube and the central line of the separation section are on the same straight line.
Preferably, the two ends of the vortex pipe and the two ends of the separation section of the vortex pipe separator are respectively and tightly connected with the air inlet hole and the air outlet hole of the sand collecting box, and the vortex pipe separator, the air inlet hole and the air outlet hole are on the same central axis.
Preferably, the injection sand discharge pipe is of a hollow structure and comprises an inner pipe and an outer pipe, the inner pipe is communicated with the sand collection box, the outer pipe is connected to a panel of the sand collection box, and an annular air ring is arranged in a gap between the inner pipe and the outer pipe; the length of the outer pipe is greater than that of the inner pipe, and the head of the outer pipe extends out of the head of the inner pipe; a slit air outlet is arranged in the inner tube; a coanda surface is arranged at a position close to the slit air outlet; the bypass port is disposed at a lower side of the outer tube.
Preferably, the cyclone separator is installed in the bleed air line; the air inlet pipe of the cyclone separator faces the inside of the air collection box, the ash discharge pipe leads to the sand collection box, and the exhaust pipe faces the axial flow fan.
Compared with the prior art, the invention at least has the following beneficial effects:
when the helicopter flies in an environment with more sand and dust, sand-containing air is introduced into the vortex pipe separator from the air inlet of the sand collecting box, the separation of air and sand and dust is completed in the vortex pipe separator, the sand and dust enters the sand collecting box through the sand discharge channel of the vortex pipe separator, clean air separated by the vortex pipe separator is introduced into the air collecting box through the air discharge hole of the sand collecting box, a small part of air in the air collecting box is sucked into the air guide pipeline under the action of the axial flow fan, then enters the injection sand discharge pipe after secondary filtration of the cyclone separator, and the sand and dust are discharged through the injection sand discharge pipe according to the Bernoulli principle by the generated pressure difference; the clean air is discharged from the main air outlet pipe and is used by the helicopter engine. The sand discharge device can reduce most of sand dust in air sucked by the engine, and sends clean air into the engine of the helicopter, thereby reducing the damage of the sand dust to the engine and prolonging the service life of the engine. The application of the bladeless fan principle of the invention moves a centrifugal fan or an axial flow fan positioned at the outlet of a sand discharging box in the traditional sand discharging device into an air guide pipeline, and in addition, a cyclone separator is arranged in front of the axial flow fan, thereby greatly reducing the abrasion of sand dust to the fan blades, avoiding frequent replacement of the fan, ensuring the use stability of the device and saving the economic cost to a certain extent.
Drawings
FIG. 1 is a schematic diagram of an external structure of an air inlet sand discharge device of a helicopter engine with abrasion-proof axial flow fan blades according to an embodiment of the invention;
FIG. 2 is a schematic view of the internal structure of an air inlet sand ejector of a helicopter engine with axial flow fan blades being wear-resistant according to an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of a swirl tube separator according to an embodiment of the invention.
In the drawings: 1-a sand-dust separation device; 2-a sand dust discharging device; 11-a panel assembly; 12-swirl tube separator; 21-ejecting sand discharge pipe; 22-a bleed air line; 23-an axial fan; 24-a main gas outlet pipe; 25-a cyclone separator; 111-an upper panel; 112-an intermediate separation panel; 113-a lower panel; 114-a peripheral side panel; 115-sand collecting box; 116-a gas collection box; 121-vortex tube; 122-a separation section; 1211-swirl vanes; 1212-blade hub; 1221-a diffusion main flow pipe; 1222-a sand discharge channel; 211-an inner tube; 212-an outer tube; 213-annular wind ring; 214-slit air outlet.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the present invention, and it should be understood that the described embodiments are a part of the embodiments of the present invention, rather than the whole embodiments, and are only applicable to the explanation of the present invention and are not intended to limit the scope of the present invention as claimed.
As shown in fig. 1 and fig. 2, an axial flow fan blade abrasion-proof helicopter engine air inlet sand discharge device according to an embodiment of the present invention includes a sand-dust separation device 1 and a sand-dust discharge device 2. Wherein, the sand-dust separating device 1 comprises a panel component 11 and a vortex tube separator 12; the sand dust discharging device 2 comprises an injection sand discharge pipe 21, an air guide pipeline 22, an axial flow fan 23, a main air outlet pipe 24 and a cyclone separator 25. In a possible embodiment, the panel assembly 11 comprises an upper panel 111, a middle partition panel 112, a lower panel 113 and a peripheral side panel 114, wherein the upper panel 111 is provided with 9 × 9 uniformly distributed circular small holes for the air intake of the swirl tube separator 12; the middle separation panel 113 is also provided with 9 × 9 uniformly distributed circular small holes for exhausting the vortex tube separator 12; the middle partition panel 112 separates clean air from dust. In the present embodiment, the cope flask 115 is constituted by the upper panel 111, the intermediate partition panel 112, and the peripheral side panel 114; a gas collecting box 116 is formed by the middle separation panel 112, the lower panel 113 and the peripheral side panel 114; the air collection box 116 is located below the collection box 115.
The panels of the sand collecting box 115 and the air collecting box 116 of the embodiment of the invention extend forwards and converge respectively, and only one circular opening is reserved respectively for sand discharge or air exhaust; the sand discharge device has different structural shapes and different air inlet directions according to different air inlet amounts of the engine, a circular opening can be arranged at the lowest side of the sand collecting box 115, and sand grains flow to a sand discharge opening along the inclined plane of the convergence part under the action of gravity. The swirl tube separator 12 is disposed between the upper panel 111 and the intermediate partition panel 112, and mainly consists of two parts, i.e., a swirl tube 121 and a separation section 122, as shown in fig. 3, the swirl tube 121 of the present embodiment includes swirl blades 1211 and a blade center body 1212 disposed in one end circular tube, and an upper passage of the swirl blades 1211 has an air inlet; the separation section 122 is a trumpet-shaped diffusion main flow pipe 1221, the diameter of which is gradually increased from the air inlet to the air outlet, and a section of which is constant at the air outlet; the inner diameter of the vortex tube 121 is larger than the outer diameter of the separation section 122 at the air inlet; the vortex tube 121 is sleeved outside the separation section 122, and a clearance between the vortex tube 121 and the separation section forms a sand discharge passage 1222; the centerline of the swirl tube 121 is collinear with the centerline of the separator section 122. The sand-containing air enters the vortex tube 121 through the air inlet, a rotating flow field is generated inside the vortex tube 121 under the flow guiding action of the vortex blades 1211, sand dust with density higher than that of the air is thrown to the tube wall of the vortex tube 121 under the action of inertia force in the rotating flow field, collides with the tube wall, loses the original movement speed, moves downwards along with the air flow near the wall surface in a spiral mode, enters the sand collecting box 115 through the sand discharge channel 1222, and clean air enters the air collecting box 116 through the diffusion main flow tube 1221 at the center. The number of the swirl tube separators 12 in the present embodiment is equal to the number of the circular holes of the upper panel 111 and the middle partition panel 112; the diffusion main flow pipe 1221 is tightly connected with the small circular holes of the middle partition panel 112, so that sand and dust in the sand collecting box 115 are prevented from entering the air collecting box 116, and the separation efficiency is prevented from being affected.
The design of the injection sand discharge pipe 21 in the embodiment of the invention uses the principle of a bladeless fan for reference, the injection sand discharge pipe is of a hollow structure and comprises an inner pipe 211 and an outer pipe 212, the inner pipe 211 is connected with a circular opening of a sand collection box 115, the outer pipe 212 is welded on a panel of the sand collection box, and a gap between the inner pipe 211 and the outer pipe 212 is an annular air ring 213; sand and dust can enter the sand discharging channel in the middle of the ejection sand discharging pipe 21 from the sand collecting box 115; an annular slit air outlet 214 is arranged in the middle of the inner pipe 211 of the injection sand discharge pipe 21; a coanda surface is arranged at the position close to the air outlet; a bypass port is arranged at the lower side of the outer pipe 212 of the injection sand discharge pipe 21.
In the embodiment of the invention, one end of the air-guiding pipeline 22 is connected with a bypass port of the injection sand discharge pipe 21, and the other end is connected with the air collection box 116; a cyclone filter 25 and an axial flow fan 23 are installed in the air guide pipeline 22, an air inlet pipe of the cyclone filter 25 faces an inlet of the air guide pipeline 22, an ash discharge pipe leads to the sand collecting box 115, an air exhaust pipe faces the axial flow fan 23, the cyclone filter 25 can perform secondary filtration on air which is about to flow through the axial flow fan 23, abrasion of fan blades is reduced, the filtered air enters an annular air ring 213 which is used for ejecting the sand discharge pipe 21, and sand grains enter the sand collecting box 115 through the ash discharge pipe. One end of the main outlet pipe 24 is connected to the circular opening of the header 116 and the other end is connected to the inlet diffuser of the helicopter engine.
The working process of the helicopter engine air inlet sand discharge device with the abrasion-proof axial flow fan blades provided by the embodiment of the invention is as follows:
when the helicopter flies in an environment with high sand dust content, under the action of the suction force of the engine, sand-containing gas enters the 9 x 9 vortex tube separators 12 which are uniformly distributed through the circular small holes of the upper panel 111, and the flow guiding effect of the vortex blades 1211 enables the interior of the vortex tube 121 to generate a rotating flow field. In the rotating flow field, the swirl vanes 1211 make the sand-containing gas have both a radial velocity and a tangential velocity, and sand particles having a density greater than that of air gradually move toward the wall surface of the swirl tube 121 by the centrifugal force. When sand collides with the wall surface of the vortex tube 121, the sand cannot keep its original speed, and thus moves downward by gravity and enters the sand collecting box 115 from the sand discharge passage 1222, while clean air enters the air collecting box 116 from the middle diffusion main flow tube 1221, thereby completing the separation of air and sand dust.
Under the action of the axial flow fan 23, a small part of the first filtered clean air in the air collecting box 116 is sucked into the air introducing pipeline 22, after the second filtering is completed in the cyclone separator 25, the air enters the annular air ring 213 between the inner pipe 211 and the outer pipe 212 of the ejection sand discharge pipe 21, the air flow is forcibly ejected from the slit air outlet 214 of the inner pipe at a high speed, and due to the coanda surface existing close to the air outlet, more peripheral air is driven to move towards the opening direction of the slit air outlet 214 (i.e. the direction far away from the sand collecting box 115). The air in the radial direction of the slit air outlet 214 is driven by the air flow of the air outlet to move in the direction away from the sand-collecting box 115, and a negative pressure area (based on bernoulli principle) is formed in the sand-discharging channel in the middle of the sand-discharging pipe, so that the sand and dust in the sand-collecting box 115 are sucked to the sand-discharging channel and then discharged. Most of the clean gas in the header 116 is delivered to the engine for use after passing through the main outlet duct 24.
The sand discharging device at the air inlet of the helicopter engine can reduce most of sand dust in the sucked air, and clean air is sent into the engine of the helicopter, so that the damage of the sand dust to the engine is reduced, and the service life of the engine is prolonged; the centrifugal fan or the axial flow fan at the outlet of the sand discharging box in the traditional sand discharging device is moved to the air guide pipeline 22 based on the application of the bladeless fan principle, and in addition, the cyclone separator 25 is arranged in front of the axial flow fan 23, so that the abrasion of sand dust to the fan blades is greatly reduced, the frequent replacement of the fan is avoided, the use stability of the device is ensured, and the economic cost is saved to a certain extent.
The above-mentioned embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the embodiments of the present application, and they should be construed as being included in the present application.
Claims (8)
1. The utility model provides a helicopter engine air inlet sand discharging device of axial fan blade abrasionproof decreases which characterized in that: comprises a sand-dust separating device (1) and a sand-dust discharging device (2); the sand-dust separation device (1) comprises a panel component (11) and a vortex pipe separator (12), wherein a separated sand collecting box (115) and a separated gas collecting box (116) are formed by the panel component (11), the vortex pipe separator (12) is arranged in the sand collecting box (115), a gas inlet hole and a gas outlet hole are formed in the sand collecting box (115), a pipe body of the vortex pipe separator (12) is provided with a sand discharge channel (1222) communicated with the sand collecting box (115), sand-containing air is introduced into the vortex pipe separator (12) through the gas inlet hole, and clean air separated by the vortex pipe separator (12) is introduced into the gas collecting box (116) through the gas outlet hole; the sand and dust discharging device (2) comprises an injection sand discharge pipe (21), an air guide pipeline (22), an axial flow fan (23), a main air outlet pipe (24) and a cyclone separator (25), wherein the injection sand discharge pipe (21) is communicated with a sand collection box (115), a bypass port is formed in the side surface of the injection sand discharge pipe (21) and communicated with a gas collection box (116) through the air guide pipeline (22), the axial flow fan (23) is installed in the air guide pipeline (22), the cyclone separator (25) is arranged between the axial flow fan (23) and the gas collection box (116), a main air outlet is formed in the gas collection box (116), and the main air outlet of the gas collection box (116) is connected with an air inlet of a helicopter engine through the main air outlet pipe (24).
2. A helicopter engine air inlet bleed with axial flow fan blades wear resistant according to claim 1 wherein: panel components (11) include top panel (111), middle partition panel (112), lower panel (113) and week side panel (114), top panel (111) are opened there are a plurality of round hole as the inlet port, middle partition panel (112) are opened there are a plurality of round hole as the exhaust hole, constitute sand-collecting box (115) through top panel (111), middle partition panel (112), week side panel (114), constitute gas tank (116) through middle partition panel (112), lower panel (113) and week side panel (114).
3. A helicopter engine air inlet bleed with axial flow fan blades wear resistant according to claim 2 wherein: the upper panel (111) is provided with 9 x 9 uniformly distributed round holes as air inlet holes, the middle separation panel (112) is provided with 9 x 9 uniformly distributed round holes as air outlet holes corresponding to the air inlet holes of the upper panel (111), the number of the vortex tube separators (12) is 9 x 9, and one vortex tube separator (12) is correspondingly connected between each pair of air inlet holes and air outlet holes.
4. A helicopter engine air inlet bleed with axial fan blade wear protection as claimed in claim 1, wherein: the panels of the sand collecting box (115) and the gas collecting box (116) extend forwards and converge respectively, and only one circular opening is reserved at the convergence end respectively and is used as a sand discharging port and a main air outlet respectively; the sand ejecting and discharging pipe (21) is connected to the circular opening of the sand collecting box (115), the main air outlet pipe (24) is connected to the circular opening of the air collecting box (116), a side face of the main air outlet pipe (24) is provided with a bypass port, and the air guiding pipeline (22) is connected between the main air outlet pipe (24) and the bypass port of the sand ejecting and discharging pipe (21).
5. A helicopter engine air inlet bleed with axial fan blade wear protection as claimed in claim 1, wherein: the swirl tube separator (12) consists of a swirl tube (121) and a separation section (122); the vortex tube (121) comprises a vortex blade (1211) arranged in a section of the circular tube and a blade central body (1212) provided with the vortex blade (1211), and an air inlet is formed above the vortex blade (1211); the separation section (122) is a flared diffusion main flow pipe (1221), the diameter of the diffusion main flow pipe is gradually increased from an air inlet to an air outlet, and the diameter of the diffusion main flow pipe is constant at the air outlet; the inner diameter of the vortex tube (121) is larger than the outer diameter of the vortex tube at the air inlet of the separation section (122); the vortex tube (121) is sleeved outside the separation section (122), and a sand discharge channel (1222) is formed by a gap between the vortex tube and the separation section; the central line of the vortex tube (121) and the central line of the separation section (122) are on the same straight line.
6. A helicopter engine air inlet bleed with axial fan blade wear protection as claimed in claim 5, wherein: two ends of a vortex pipe (121) and a separation section (122) of the vortex pipe separator (12) are respectively and tightly connected with an air inlet hole and an air outlet hole of the sand collecting box (115), and the vortex pipe separator (12), the air inlet hole and the air outlet hole are on the same central axis.
7. A helicopter engine air inlet bleed with axial flow fan blades wear resistant according to claim 1 wherein: the injection sand discharge pipe (21) is of a hollow structure and comprises an inner pipe (211) and an outer pipe (212), the inner pipe (211) is communicated with the sand collection box (115), the outer pipe (212) is connected to a panel of the sand collection box (115), and an annular air ring (213) is arranged in a gap between the inner pipe (211) and the outer pipe (212); the length of the outer pipe (212) is larger than that of the inner pipe (211), and the head of the outer pipe (212) extends out of the head of the inner pipe (211); a slit air outlet (214) is arranged in the inner tube (211); a coanda surface is provided in close proximity to the slit exit (214); the bypass port is provided at a lower side of the outer tube (212).
8. A helicopter engine air inlet bleed with axial fan blade wear protection as claimed in claim 1, wherein: the cyclone separator (25) is installed in the bleed air line (22); the air inlet pipe of the cyclone separator (25) faces the inside of the air collecting box (116), the ash discharging pipe leads to the sand collecting box (115), and the air outlet pipe faces the axial flow fan (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211174193.3A CN115489740A (en) | 2022-09-26 | 2022-09-26 | Helicopter engine air inlet sand discharging device with abrasion-proof axial flow fan blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211174193.3A CN115489740A (en) | 2022-09-26 | 2022-09-26 | Helicopter engine air inlet sand discharging device with abrasion-proof axial flow fan blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115489740A true CN115489740A (en) | 2022-12-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211174193.3A Pending CN115489740A (en) | 2022-09-26 | 2022-09-26 | Helicopter engine air inlet sand discharging device with abrasion-proof axial flow fan blades |
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| Country | Link |
|---|---|
| CN (1) | CN115489740A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116374182A (en) * | 2023-02-23 | 2023-07-04 | 江苏恒铭达航空设备有限公司 | Sand control device and method thereof |
-
2022
- 2022-09-26 CN CN202211174193.3A patent/CN115489740A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116374182A (en) * | 2023-02-23 | 2023-07-04 | 江苏恒铭达航空设备有限公司 | Sand control device and method thereof |
| CN116374182B (en) * | 2023-02-23 | 2024-04-02 | 江苏恒铭达航空设备有限公司 | Sand control device and method thereof |
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