CN113090391A - Cap cover anti-icing heat transfer structure with air film hole and front edge impact - Google Patents
Cap cover anti-icing heat transfer structure with air film hole and front edge impact Download PDFInfo
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- CN113090391A CN113090391A CN202110510604.0A CN202110510604A CN113090391A CN 113090391 A CN113090391 A CN 113090391A CN 202110510604 A CN202110510604 A CN 202110510604A CN 113090391 A CN113090391 A CN 113090391A
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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
- F02C7/047—Heating to prevent icing
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention relates to a hood anti-icing heat transfer structure with air film holes and front edge impact, belonging to the technical field of aeroengine hood front edge air heat anti-icing; the device comprises an impact orifice plate, a hood front edge wall surface, a hood inner wall and a hood outer wall, wherein an annular gap between the hood inner wall and the hood outer wall forms a double-wall hot gas channel, and a cavity in the hood inner wall is an air inlet cavity; the center of the impact orifice plate is provided with an impact orifice with the diameter D, and a cavity between the impact orifice plate and the front edge wall surface of the cap cover is an impact inner cavity of the front edge of the cap cover; the outer wall of the cap is provided with an array air film hole; the hot gas in the air inlet cavity is sprayed to the front edge inner cavity area through the impact holes to impact the front edge wall surface of the cap cover, and flows through the hot gas channel between the double-layer walls to heat the outer wall surface and then flows out through the gas film holes. The mixing of hot gas and mainstream cold air improves the gas temperature of heat exchange between the outside and the cap cover, thereby realizing the purpose of external anti-icing. Simultaneously, the ice crystals and rain drops in the air are blown to reduce the possibility of the ice crystals and the rain drops attaching to the surface of the cap cover.
Description
Technical Field
The invention belongs to the technical field of aerothermal anti-icing of the front edge of a hood of an aircraft engine, and particularly relates to an anti-icing and heat-transfer structure of a hood with an air film hole and front edge impact.
Background
When the aircraft passes through a low temperature cloud with ice crystals, rain drops. The probability of icing on the surface of each part of the aircraft, including wings, empennage, air inlet leading edge, windshield and the like, is greatly increased. The accumulation of ice layers can change the aerodynamic characteristics of the airplane, increase the weight of the airplane, reduce the working efficiency of the airplane, even threaten the operation safety of the airplane, cause permanent damage and the like. Particularly for parts of an aircraft engine which are subjected to severe working conditions, the deicing structure is an important component for ensuring the operation of the engine.
The principle of the ice prevention of the cap cover at the front edge of the inlet of the aero-engine is that high-temperature gas is led from a gas compressor, and the surface needing ice prevention is heated, so that water is evaporated or an ice layer is melted. Its advantages are simple structure, light weight, mature technology and high reliability. The disadvantages are that the working environment of the compressor is deteriorated and the power-applying capacity of the engine is reduced by introducing air from the compressor. The efficient heat exchange structure can reduce air entraining amount as much as possible while meeting the anti-icing requirement, and ensures the working performance of the engine.
Disclosed in patent CN203753413U in 2014 is an anti-icing heat transfer structure for an aircraft engine inlet fairing cap, which comprises jet holes at the front edge of the inner wall of the cap, jet holes uniformly distributed in the circumferential direction on the inner wall of the cap, an anti-icing hot gas channel, and vent holes at the tail end of the cap. The anti-icing hot gas channel consists of an inner thin wall and an outer thin wall, the distance between the two thin walls is gradually reduced from the front end to the tail end of the fairing, and a heat exchange channel is formed in the middle.
Although the structure solves the problem of large demand of ice-proof heat in unit area of the front edge of the cap cover, the adopted impact heat exchange structure is simple, the heat exchange strength is not large, and part of gas still carrying a large amount of heat is only discharged from the tail part, so that the waste of heat is caused. Meanwhile, the impact heat exchange high-efficiency area of hot gas on the wall surface of the front edge of the hood is small, only internal anti-icing measures are considered, and external anti-icing measures are ignored.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides an anti-icing heat transfer structure of a cap with air film holes and front edge impact, namely, a certain number of air film holes are arranged on the outer wall of the cap, the anti-icing effect of the front edge area is enhanced by utilizing internal impact heat exchange, so that air after impact heat exchange forms an air film on the outer side of the cap through the air film holes in the process of convective heat exchange with the outer wall surface, and the temperature of the air actually contacted with the outer wall surface of the cap is increased by mixing internal hot air and external cold air, thereby achieving the purpose of external anti-icing. Meanwhile, the ice crystal and raindrops have certain blowing effect, and the possibility of the ice crystal and raindrops attaching to the surface of the cap cover is reduced. The high-temperature gas flowing from the compressor is effectively utilized, and the comprehensive anti-icing effect of the cap cover is improved.
The technical scheme of the invention is as follows: a cap cover anti-icing heat transfer structure with a gas film hole and front edge impact comprises an impact hole plate, a cap cover front edge wall surface, a cap cover inner wall and a cap cover outer wall, wherein an annular gap between the cap cover inner wall and the cap cover outer wall forms a hot gas channel between double layers of walls, and a cavity in the cap cover inner wall is an air inlet cavity; the impact orifice plate is coaxially arranged at the front edge of the inner wall of the cap cover, the center of the impact orifice plate is provided with an impact orifice with the diameter of D, and a cavity between the impact orifice plate and the wall surface of the front edge of the cap cover is an impact inner cavity of the front edge of the cap cover; the method is characterized in that: the device also comprises an array air film hole on the outer wall of the cap cover;
the gas film holes are distributed in a linear array along a bus of the outer wall of the cap cover, and the hole spacing is 3.5-4.5D along the bus direction; the axes of the first exhaust film holes on the wall surface of the front edge of the cap cover are positioned on the same plane, the distance between the plane and the rounding surface of the front edge of the cap cover is L, and the ratio of L to the diameter D of the impact holes is 1.2-2.4;
the hot gas in the air inlet cavity is sprayed to the front edge inner cavity area through the impact holes to impact the front edge wall surface of the cap cover, and flows through the hot gas channel between the double-layer walls to heat the outer wall surface and then flows out through the gas film holes.
The further technical scheme of the invention is as follows: the film holes on the outer wall of the cap cover are distributed in 7 rows along a bus linear array, and 14 holes in each row are uniformly distributed along the circumferential direction.
The further technical scheme of the invention is as follows: diameter d of the gas film hole1The ratio of the impact hole diameter D to the impact hole diameter D is 0.3-0.5.
The further technical scheme of the invention is as follows: the included angle between the axis of the air film hole and the axis of the cap cover is 90 degrees, and the hole type is a cylindrical hole.
The further technical scheme of the invention is as follows: the cone angle of the cap is 60-84 degrees.
The further technical scheme of the invention is as follows: the ratio of the radius inner diameter D of the front edge of the cap to the diameter D of the impact hole is 0.5-2.
The further technical scheme of the invention is as follows: the ratio of the axial length of the impact hole to the diameter of the impact hole is 0.25-1.25.
The further technical scheme of the invention is as follows: the ratio of the impact distance H of the impact hole to the diameter D of the impact hole is 6-10, and the impact distance is the distance between the end face of the impact hole and the front edge rounding face of the cap cover.
The further technical scheme of the invention is as follows: the distance between the inner wall of the cap cover and the outer wall of the cap cover is 0.4-0.8D.
Advantageous effects
The invention has the beneficial effects that:
according to the cap cover anti-icing heat transfer structure with the air film holes impacting the front edge, firstly, the impact structure is arranged in the front edge area of the cap cover to improve the internal heat exchange effect of the front edge area, in addition, a certain number of air film holes are formed in the outer wall of the cap cover, the air which is subjected to internal impact heat exchange and still has partial heat is used for an external air film, the temperature of the air subjected to external heat exchange with the cap cover is improved through mixing of hot air and main stream cold air, and therefore the purpose of external anti-icing is achieved. Simultaneously, the ice crystals and rain drops in the air are blown to reduce the possibility of the ice crystals and the rain drops attaching to the surface of the cap cover.
In addition, under the main flow effect, the external air film can extend on the outer wall surface of the cap cover so as to improve the external anti-icing effect, and in conclusion, the anti-icing structure with the air film holes and the front edge impact has good comprehensive heating characteristic and better processing feasibility; the method can be used for various aeroengine fairing covers.
From the numerical simulation results, it was found that the temperature of the outer wall surface of the substructure with the impingement hole structure was 305K at a primary flow temperature of 300K and a secondary flow temperature of 320K. The temperature of the outer side wall surface of the cap anti-icing heat transfer structure with the impact of the air film holes and the front edge is 319K. The anti-icing effect of the cap cover is effectively improved.
Drawings
FIG. 1 is a top plan view and a half sectional view of a cap anti-icing heat transfer structure of the present invention with film holes impinging on the leading edge.
FIG. 2 is an isometric view of a cap anti-icing heat transfer structure of the present invention with air film holes impinging on the leading edge.
FIG. 3 is a front view of the inner wall of an anti-icing heat transfer structure of a cap with film holes impinging on the leading edge of the present invention.
FIG. 4 is a top view of the inner wall of an anti-icing heat transfer structure of a cap with film holes impinging on the leading edge of the present invention.
FIG. 5 is an isometric view of the inner wall of an anti-icing heat transfer structure of a cap with film holes impinging on the leading edge, in accordance with the present invention.
FIG. 6 is an elevational view of the outer wall of an anti-icing heat transfer structure of a cap with film holes impinging on the leading edge of the present invention.
FIG. 7 is a top view of the outer wall of an anti-icing heat transfer structure of a cap with film holes impinging on the leading edge of the present invention.
FIG. 8 is an isometric view of the outer wall of an anti-icing heat transfer structure of a cap with film holes impinging on the leading edge of the present invention.
Description of reference numerals: 1. the structure comprises an air inlet cavity, 2 parts of a cap outer wall, 3 parts of a hot gas channel between double walls, 4 parts of a cap inner wall, 5 parts of an air film hole, 6 parts of an impact orifice plate, 7 parts of a cap front edge impact inner cavity, 8 parts of a cap front edge wall surface and 9 parts of an impact hole.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Referring to fig. 1 to 8, the anti-icing heat transfer structure of the cap with the air film hole and the impact of the front edge is applied to the fairing of the aircraft engine. The device consists of an air inlet cavity 1, a cap outer wall 2, a hot gas channel 3 between double walls, a cap inner wall 4, a gas film hole 5, an impact orifice plate 6, a cap front edge impact inner cavity 7, a cap front edge wall surface 8 and a front edge impact hole 9. The outer wall surface of the cap is provided with air film holes, hot air is sprayed to the inner cavity area of the front edge from the impact holes to impact the front edge wall surface of the cap, and the hot air flows through the hot air channel between the double walls to heat the outer wall surface and then flows out through the air film holes. The cone angle of the cap is 60-84 degrees, the ratio of the radius inner diameter D of the front edge of the cap to the diameter D of the impact hole is 0.5-2, the ratio of the length of the impact hole to the diameter of the impact hole is 0.25-1.25, and the impact distance, namely the ratio of the distance H between the impact hole and the rounding surface of the front edge of the cap to the diameter D of the impact hole is 6-10. The distance between the inner wall and the outer wall is 0.4-0.8D, the outer wall air film holes are distributed in 7 rows along the bus linear array at intervals of 3.5-4.5D, and 14 holes in each row are evenly distributed around the circumference of the center point of the front edge of the cap cover. The ratio of the distance L between the plane of the axis of the first exhaust film hole and the rounded surface of the front edge of the cap cover to the diameter D of the impact hole is 1.2-2.4. Diameter d of the gas film hole1The ratio of the impact hole diameter D to the impact hole diameter D is 0.3-0.5. The included angle between the axis of the air film hole and the axis of the cap cover is 90 degrees, and the hole type is a cylindrical hole.
In the embodiment, hot gas from the air inlet cavity 1 passes through the impact orifice plate 6, is blown out from the impact orifice 9, enters the inner cavity 7 of the impact area at the front edge of the cap cover, is subjected to impact heat exchange with the wall surface 8 at the front edge of the cap cover, then passes through the hot gas channel 3 between the double-layer walls formed by the inner wall 4 of the cap cover and the outer wall 2 of the cap cover, is subjected to convection heat exchange with the outer wall 4 of the cap cover, and is sprayed out from the gas film hole 5 to form a gas film on the outer wall. The outer wall surface is provided with the air film hole, so that the air subjected to heat convection forms an air film on the outer surface of the cap cover, and meanwhile, the internal energy and the kinetic energy of hot air flow are utilized, and the effective utilization rate of the hot air is improved. Meanwhile, the gas film hole of the outer wall improves the temperature of gas actually contacting with the outer wall surface of the cap cover through the mixing of main stream cold air and secondary stream hot air, so that the aim of external anti-icing is fulfilled, and in addition, the external gas film can continuously extend on the outer wall surface of the cap cover under the action of the main stream, so that the outer wall surface of the cap cover is protected. And has certain blowing effect on ice crystals and raindrops, and the probability of the ice crystals and the raindrops attaching to the surface of the cap cover is reduced. Therefore, the double-wall structure with the air film holes greatly improves the integral heating effect of the outer surface of the cap cover.
From the numerical simulation results, it was found that the temperature of the outer wall surface of the substructure with the impingement hole structure was 305K at a primary flow temperature of 300K and a secondary flow temperature of 320K. The temperature of the outer side wall surface of the cap anti-icing heat transfer structure with the impact of the air film holes and the front edge is 319K. The anti-icing effect of the cap cover is effectively improved.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (9)
1. A cap cover anti-icing heat transfer structure with a gas film hole and front edge impact comprises an impact hole plate, a cap cover front edge wall surface, a cap cover inner wall and a cap cover outer wall, wherein an annular gap between the cap cover inner wall and the cap cover outer wall forms a hot gas channel between double layers of walls, and a cavity in the cap cover inner wall is an air inlet cavity; the impact orifice plate is coaxially arranged at the front edge of the inner wall of the cap cover, the center of the impact orifice plate is provided with an impact orifice with the diameter of D, and a cavity between the impact orifice plate and the wall surface of the front edge of the cap cover is an impact inner cavity of the front edge of the cap cover; the method is characterized in that: the device also comprises an array air film hole on the outer wall of the cap cover;
the gas film holes are distributed in a linear array along a bus of the outer wall of the cap cover, and the hole spacing is 3.5-4.5D along the bus direction; the axes of the first exhaust film holes on the wall surface of the front edge of the cap cover are positioned on the same plane, the distance between the plane and the rounding surface of the front edge of the cap cover is L, and the ratio of L to the diameter D of the impact holes is 1.2-2.4;
the hot gas in the air inlet cavity is sprayed to the front edge inner cavity area through the impact holes to impact the front edge wall surface of the cap cover, and flows through the hot gas channel between the double-layer walls to heat the outer wall surface and then flows out through the gas film holes.
2. The anti-icing and heat-transfer structure of a cap with film holes and leading edge impingement according to claim 1, wherein: the film holes on the outer wall of the cap cover are distributed in 7 rows along a bus linear array, and 14 holes in each row are uniformly distributed along the circumferential direction.
3. The anti-icing and heat-transfer structure of a cap with film holes and leading edge impingement according to claim 1, wherein: diameter d of the gas film hole1The ratio of the impact hole diameter D to the impact hole diameter D is 0.3-0.5.
4. The anti-icing and heat-transfer structure of a cap with film holes and leading edge impingement according to claim 1, wherein: the included angle between the axis of the air film hole and the axis of the cap cover is 90 degrees, and the hole type is a cylindrical hole.
5. The anti-icing and heat-transfer structure of a cap with film holes and leading edge impingement according to claim 1, wherein: the cone angle of the cap is 60-84 degrees.
6. The anti-icing and heat-transfer structure of a cap with film holes and leading edge impingement according to claim 1, wherein: the ratio of the radius inner diameter D of the front edge of the cap to the diameter D of the impact hole is 0.5-2.
7. The anti-icing and heat-transfer structure of a cap with film holes and leading edge impingement according to claim 1, wherein: the ratio of the axial length of the impact hole to the diameter of the impact hole is 0.25-1.25.
8. The anti-icing and heat-transfer structure of a cap with film holes and leading edge impingement according to claim 1, wherein: the ratio of the impact distance H of the impact hole to the diameter D of the impact hole is 6-10, and the impact distance is the distance between the end face of the impact hole and the front edge rounding face of the cap cover.
9. The anti-icing and heat-transfer structure of a cap with film holes and leading edge impingement according to claim 1, wherein: the distance between the inner wall of the cap cover and the outer wall of the cap cover is 0.4-0.8D.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110510604.0A CN113090391A (en) | 2021-05-11 | 2021-05-11 | Cap cover anti-icing heat transfer structure with air film hole and front edge impact |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110510604.0A CN113090391A (en) | 2021-05-11 | 2021-05-11 | Cap cover anti-icing heat transfer structure with air film hole and front edge impact |
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| CN202110510604.0A Pending CN113090391A (en) | 2021-05-11 | 2021-05-11 | Cap cover anti-icing heat transfer structure with air film hole and front edge impact |
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Citations (9)
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|---|---|---|---|---|
| CH330268A (en) * | 1953-07-03 | 1958-05-31 | Armstrong Siddeley Motors Ltd | Gas turbine propulsion installation for an aircraft |
| GB1210202A (en) * | 1969-03-06 | 1970-10-28 | Rolls Royce | Gas turbine engine |
| CN203753413U (en) * | 2014-01-03 | 2014-08-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Anti-icing heat conduction structure of rectifying cover hood at inlet of aviation engine |
| US20160311542A1 (en) * | 2015-04-16 | 2016-10-27 | The Boeing Company | Weeping ferrofluid anti-ice system |
| CN108757180A (en) * | 2018-05-31 | 2018-11-06 | 中国航发沈阳发动机研究所 | Engine Anti-Ice rotates calotte |
| CN110318882A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of calotte leading edge inner passage ice prevention structure with pentalpha impact opening |
| CN110318883A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of aero-engine calotte single hole impingement heat transfer structure in helical curve channel |
| CN110318881A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of orifice plate forward tilt aero-engine calotte single hole impingement heat transfer structure |
| US20200032670A1 (en) * | 2018-07-24 | 2020-01-30 | United Technologies Corporation | Systems and methods for fan blade de-icing |
-
2021
- 2021-05-11 CN CN202110510604.0A patent/CN113090391A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH330268A (en) * | 1953-07-03 | 1958-05-31 | Armstrong Siddeley Motors Ltd | Gas turbine propulsion installation for an aircraft |
| GB1210202A (en) * | 1969-03-06 | 1970-10-28 | Rolls Royce | Gas turbine engine |
| CN203753413U (en) * | 2014-01-03 | 2014-08-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Anti-icing heat conduction structure of rectifying cover hood at inlet of aviation engine |
| US20160311542A1 (en) * | 2015-04-16 | 2016-10-27 | The Boeing Company | Weeping ferrofluid anti-ice system |
| CN108757180A (en) * | 2018-05-31 | 2018-11-06 | 中国航发沈阳发动机研究所 | Engine Anti-Ice rotates calotte |
| US20200032670A1 (en) * | 2018-07-24 | 2020-01-30 | United Technologies Corporation | Systems and methods for fan blade de-icing |
| CN110318882A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of calotte leading edge inner passage ice prevention structure with pentalpha impact opening |
| CN110318883A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of aero-engine calotte single hole impingement heat transfer structure in helical curve channel |
| CN110318881A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of orifice plate forward tilt aero-engine calotte single hole impingement heat transfer structure |
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Application publication date: 20210709 |