CN110318881B - Pore plate forward-inclined type aero-engine cap single-hole impact heat exchange structure - Google Patents
Pore plate forward-inclined type aero-engine cap single-hole impact heat exchange structure Download PDFInfo
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- CN110318881B CN110318881B CN201910617191.9A CN201910617191A CN110318881B CN 110318881 B CN110318881 B CN 110318881B CN 201910617191 A CN201910617191 A CN 201910617191A CN 110318881 B CN110318881 B CN 110318881B
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- impact
- front edge
- wall surface
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- hole
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
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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
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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
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
- F02C7/1435—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages by water injection
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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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
Abstract
The invention discloses a pore plate forward-inclined type aero-engine cap single-hole impact heat exchange structure.A forward-inclined triangular structure with the same central axis is arranged at an impact hole on an impact pore plate to form a forward-inclined expansion channel, the forward-inclined expansion channel and the side wall surface of the impact pore plate form an integral structure, and a hot gas channel is formed between the forward-inclined expansion channel and the front edge wall surface of a cap; the inner cavity of the front edge impact area on the inner side of the front edge wall surface of the cap cover is an impact heat exchange area; hot gas introduced from the gas compressor is sprayed from the impact hole, flows to the front edge impact inner cavity region through the impact hole plate with the forward-inclined triangular structure and impacts the front edge wall surface of the cap cover, and flows from the hot gas channel to the front edge wall surface in the circumferential direction and flows out through the annular outlet of the channel; the turbulence of the impact air flow on the front edge of the cap cover is improved through the forward-inclined expanding channel structure, and the rolling flow field is compressed through the forward-inclined expanding channel structure, so that the jet flow velocity of the wall surface of the front edge is increased, the impact heat exchange strength is enhanced, and the effect of the heat exchange strength of the wall surface of the front edge of the cap cover is improved.
Description
Technical Field
The invention relates to a heat exchange and anti-icing technology for the front edge of an aeroengine hood, in particular to a single-hole impact orifice plate forward-leaning heat exchange structure of an aeroengine inlet fairing hood.
Background
When the aircraft engine works under low-temperature meteorological conditions, ice accumulation phenomena can be generated on inlet parts of the aircraft engine, such as the front edge of an air inlet passage and a fairing in an air inlet part of the engine due to low temperature. When the heat exchange anti-icing measures implemented by the engine fairing are insufficient and the peripheral heat exchange capability of the front edge of the fairing is uneven, icing can occur. Firstly, due to insufficient circumferential hot gas impact heat exchange capacity of the front edge, the rear half part of the wall surface of the front edge of the engine hood is close to the position of an inlet of an air flow entering the engine, the accumulated ice can cause blockage of the position of the inlet, the inlet air flow of the engine can be reduced, and the surge operation of the engine can even be caused; secondly, when the accumulated ice is accumulated on the surface of the front edge wall surface of the hood or is removed, the fan and the propeller rotate unevenly, and the running vibration frequency and amplitude of the engine are increased; most seriously, the falling ice accretion can easily damage the blades of the fan or the air compressor, and cause the running failure of the engine and even accidents. Therefore, the design of an efficient cap front edge impact heat exchange structure and the enhancement of the whole heat exchange capacity and the uniformity of the heat exchange capacity of the circumferential wall surface of the cap front edge are important measures for ensuring the stable work of the aero-engine.
In the document 'research on the heat exchange coefficient of the icing surface of the rotary cap cover of the aircraft engine' (propulsion technology, 2017(04):138 and 144.), the influence of different rotating speeds, incoming flow speeds and incoming flow temperatures on the heat exchange coefficient of the surface of the rotary cap cover with the cone angle of 40 degrees and the cone height of 176mm is researched. The results show that: the cone tip area is mainly influenced by the incoming flow speed; the incoming flow temperature has an effect on the heat transfer coefficient across the surface. The scheme of the research on enhancing the heat exchange effect is to increase the consumption of the incoming hot gas. Therefore, the front edge impact heat exchange structure of the aircraft engine hood is developed and innovated, the heat exchange effect is further improved on the basis of not increasing the consumption of hot gas, and the front edge impact heat exchange structure is very necessary and has great significance for the development of advanced high-performance aircraft engines.
An anti-icing heat transfer structure of an aero-engine inlet fairing is disclosed in a patent CN201420003992, aiming at the problem that the unit area anti-icing heat requirement of a leading edge area is large, the leading edge adopts an impact heat exchange structure; the anti-icing hot gas flows backwards along the hot gas channel from the front edge of the cap cover, the characteristic of high initial temperature of the anti-icing hot gas is fully utilized to solve the problem of high heat demand of the front edge of the cap cover in unit area, and the higher initial enthalpy value of the anti-icing hot gas is effectively utilized. Meanwhile, the middle section of the cap cover is provided with an anti-icing hot gas jet hole to enhance anti-icing heat supply of the middle section and the tail end; the anti-icing hot gas is finally exhausted through the exhaust hole at the tail end part of the cap cover. Although the impact heat exchange structure is applied to the problem that the requirement for the ice heat prevention of the unit area of the front edge area in the structure is large, the impact speed of hot gas is reduced due to the fact that a large cavity is formed in the impact hole and the impact heat exchange area, and therefore the convection heat exchange strength of the front edge of the cap cover and the utilization efficiency of the hot gas are reduced.
Disclosure of Invention
In order to avoid the defects in the prior art, the invention provides a pore plate forward-inclined type aero-engine cap cover single-pore impact heat exchange structure, a forward-inclined expanding channel is used for a cap cover single-pore impact pore plate by the cap cover single-pore impact heat exchange structure, and the integral heat exchange effect of the front edge of a cap cover and the wall surface of a hot gas channel is enhanced on the premise of not increasing the flow rate of an impact hole; the forward-inclined expanding channel structure is additionally arranged on the impact inner cavity side of the impact orifice plate, so that the impact orifice plate has good impact heat exchange characteristic and better processing feasibility.
The technical scheme adopted by the invention for solving the technical problems is that the device comprises an air inlet large cavity, an impact orifice plate, an impact orifice, a forward-inclined expansion channel, a front edge impact area inner cavity, a hood front edge wall surface, a hot gas channel and a channel annular outlet, and is characterized in that the impact orifice on the impact orifice plate is provided with a forward-inclined triangular structure with the same central axis to form the forward-inclined expansion channel, the forward-inclined expansion channel and the impact orifice plate side wall surface form an integral structure, and the forward-inclined expansion channel and the hood front edge wall surface form the hot gas channel in the middle; the inner cavity of the front edge impact area on the inner side of the front edge wall surface of the cap cover is an impact heat exchange area, and the impact area of the airflow impacting to the front edge wall surface of the cap cover is enlarged through the forward-inclined triangular structure before the airflow impacts to the front edge wall surface of the cap cover through the impact holes; hot gas introduced from the gas compressor is sprayed from the impact hole, flows to the front edge impact inner cavity region through the impact hole plate with the forward-inclined triangular structure and impacts the front edge wall surface of the cap cover, flows to the front edge wall surface from the hot gas channel in the circumferential direction, and flows out through the annular outlet of the channel;
the wall surface of the front edge of the cap cover is of a conical curved surface structure, the value range of the cone angle is 60-84 degrees, and the ratio of the radius inner diameter D of the front edge of the cap cover to the diameter D of the impact hole is 0.5-2;
the impact hole is a cylindrical round hole, the ratio of the length of the impact hole to the diameter of the impact hole is 0.25-1.25, and the ratio of the distance H from the impact hole to the front edge rounding surface of the cap cover to the diameter D of the impact hole is 6-10;
the included angle between the wall surface of the forward-inclined expanding channel and the horizontal incoming flow is 30-42 degrees, the ratio of the length L of the forward-inclined expanding channel to the aperture D of the impact hole is 3-5, and the ratio of the exit aperture M of the forward-inclined expanding channel to the aperture D of the impact hole is 3-5.
The distance between the two wall surfaces of the hot gas channel gradually shrinks and becomes smaller from the front end of the fairing cap cover to the annular outlet of the channel.
Advantageous effects
The invention provides a pore plate forward-inclined type aero-engine cap cover single-hole impact heat exchange structure, which is applied to a cap cover single-hole impact pore plate through a forward-inclined expanding type channel structure, enhances the integral heat exchange effect of the front edge of a cap cover and the wall surface of a hot gas channel impact area on the premise of not increasing the flow rate of an impact hole, relieves the condition of uneven heat exchange of the wall surface of the hot gas channel, increases a forward-inclined triangular structure on the impact pore plate on the impact inner cavity side to form a forward-inclined expanding jet hole channel, reduces the space of an inner cavity of the front edge, has reasonable design and simple structure, and is characterized in that hot gas is ejected from the impact hole, flows to the inner cavity area of the front edge through the forward-inclined expanding type channel to impact the wall surface of the cap cover, improves the turbulence of impact air flow on the front edge of the cap cover through the forward-inclined expanding type channel structure, compresses a rolling flow field, and increases the jet flow velocity of the front edge wall, the impact heat exchange strength is enhanced, so that the effect of improving the heat exchange strength of the front edge wall surface of the cap cover is obtained, and the condition of uneven heat exchange of the wall surface of the hot gas channel is effectively relieved.
The aeroengine inlet fairing cap single-hole impact orifice plate structure with the forward-inclined expansion type passage heat exchange structure has the advantages that the forward-inclined expansion type passage structure is additionally arranged on the impact inner cavity side of the impact orifice plate, so that the aeroengine inlet fairing cap single-hole impact orifice plate structure has good impact heat exchange characteristics and better processing feasibility; the method can be used for various aeroengine fairing covers.
Drawings
The single-hole impact heat exchange structure of the orifice plate forward-inclined type aircraft engine hood of the invention is further described in detail with reference to the accompanying drawings and the implementation mode.
FIG. 1 is an axonometric view of a single-hole impact heat exchange structure of a pore plate forward-inclined aero-engine cap cover.
Fig. 2 is a partially enlarged view of fig. 1.
Fig. 3 is a sectional view taken along line a-a of fig. 1.
Fig. 4 is a partially enlarged view of fig. 3.
Fig. 5 is a side view of fig. 3 of the present invention.
In the figure:
1. air inlet big cavity 2, impact orifice plate 3, impact orifice 4, forward inclined expanding channel 5, front edge impact zone inner cavity 6, cap cover front edge wall 7, hot gas channel 8, channel annular outlet
D is the radius inner diameter D of the front edge of the cap cover, the diameter H of the impact hole and the distance from the impact hole to the radius surface of the front edge of the cap cover
L is the length M of the anteversion expansion channel and is the outlet aperture of the anteversion expansion channel
Detailed Description
The embodiment is a pore plate forward-inclined type aero-engine cap single-hole impact heat exchange structure.
Referring to fig. 1 to 5, the orifice plate forward-inclined aero-engine bonnet single-orifice impact heat exchange structure of the embodiment is applied to a leading edge impact area in an aero-engine fairing. The pore plate forward-inclined type aero-engine hood single-hole impact heat exchange structure comprises an air inlet large cavity 1, an impact pore plate 2, impact holes 3, a forward-inclined expanding channel 4, a front edge impact area inner cavity 5, a hood front edge wall surface 6, a hot gas channel 7 and a channel annular outlet 8; wherein, a forward-inclined triangular structure with the same central axis is arranged at the impact hole 2 on the impact orifice plate 2 to form a forward-inclined expansion passage 4, the forward-inclined expansion passage 4 and the side wall surface of the impact orifice plate 2 form an integral structure, and a hot air passage 7 is formed between the forward-inclined expansion passage 4 and the front edge wall surface 6 of the cap cover. The front edge impact area inner cavity 5 on the inner side of the front edge wall surface 6 of the cap cover is an impact heat exchange area, and the impact area of airflow impacting to the front edge wall surface of the cap cover is enlarged through the forward-inclined triangular structure before the airflow impacts to the front edge wall surface 6 of the cap cover through the impact holes. Hot gas introduced from the compressor is sprayed from the impact holes, flows to the front edge impact cavity 5 region through the impact hole plate with the forward-inclined triangular structure, impacts the front edge wall surface of the cap cover, flows to the front edge wall surface from the hot gas channel in the circumferential direction, and flows out through the channel annular outlet 8.
In the embodiment, the wall surface of the front edge of the cap cover is of a conical curved surface structure, the value range of the taper angle is 60-84 degrees, and the ratio of the radius inner diameter D of the front edge of the cap cover to the diameter D of the impact hole is 0.5-2. The impact hole 3 is a cylindrical round hole, the ratio of the length of the impact hole to the diameter of the impact hole is 0.25-1.25, and the ratio of the distance H from the impact hole to the front edge rounding surface of the cap cover to the diameter D of the impact hole is 6-10. The included angle between the wall surface of the forward-inclined expanding channel 4 and the horizontal incoming flow is 30-42 degrees, the ratio of the length L of the forward-inclined expanding channel to the aperture D of the impact hole is 3-5, and the ratio of the exit aperture M of the forward-inclined expanding channel to the aperture D of the impact hole is 3-5. The impact orifice plate 2 and the hood front edge wall surface 6 are combined with a hot gas channel 7 in the middle, and the distance between the two wall surfaces gradually shrinks and becomes smaller from the front end of the fairing hood to a channel annular outlet 8.
In the embodiment, a forward-inclined triangular structure is arranged between the outlet of the impact hole 3 and the inner cavity 5 of the front edge impact area to form a forward-inclined expansion channel 4, and before the airflow impacts the front edge wall surface 7 of the cap cover through the impact hole, the forward-inclined expansion channel plays an expansion role on the airflow channel, so that the impact area of the airflow impacting the front edge wall surface of the cap cover is enlarged. Compared with the traditional structure, the pore plate forward-inclined channel can extrude the rolling flow field in the front edge core area forward, so that the flow velocity of airflow near the wall surface of the front edge area is higher, the heat exchange performance of the heat exchange area of the front edge impact area is increased, meanwhile, the forward-inclined expanding channel reduces the space of the front edge inner cavity, the turbulent flow effect in the front edge inner cavity is formed, and the turbulence degree of the airflow in the front edge inner cavity is increased. Meanwhile, the forward-inclined expanding structure compresses the rolling flow field to improve the effect of the heat exchange strength of the front edge wall surface of the cap cover, and finally, the conditions of poor heat exchange capacity and uneven heat exchange of the wall surface of the hot gas channel are effectively relieved. The application of the pore plate forward-inclined type aero-engine hood single-hole impact heat exchange structure improves the heat exchange performance of the front edge wall surface of the anti-icing hood.
Claims (2)
1. A pore plate forward-inclined type aero-engine hood single-hole impact heat exchange structure comprises an air inlet large cavity, an impact pore plate, impact holes, a forward-inclined expansion channel, a front edge impact area inner cavity, a hood front edge wall surface, a hot gas channel and a channel annular outlet, and is characterized in that a forward-inclined triangular structure with the same central axis is arranged at the impact holes on the impact pore plate to form the forward-inclined expansion channel, the forward-inclined expansion channel and the impact pore plate side wall surface form an integral structure, and the forward-inclined expansion channel and the hood front edge wall surface form the hot gas channel; the inner cavity of the front edge impact area on the inner side of the front edge wall surface of the cap cover is an impact heat exchange area, and the impact area of the airflow impacting the front edge wall surface of the cap cover is enlarged by a forward-inclined triangular structure before the airflow impacts the front edge wall surface of the cap cover through the impact holes; hot gas introduced from the gas compressor is sprayed from the impact hole, flows into an inner cavity of a front edge impact area after passing through the impact hole plate with a forward-inclined triangular structure, impacts the wall surface of the front edge of the cap cover, flows from the hot gas channel to the circumferential direction of the wall surface of the front edge, and flows out through the annular outlet of the channel;
the wall surface of the front edge of the cap cover is of a conical curved surface structure, the value range of the cone angle is 60-84 degrees, and the ratio of the radius inner diameter D of the front edge of the cap cover to the diameter D of the impact hole is 0.5-2;
the impact hole is a cylindrical round hole, the ratio of the length of the impact hole to the diameter of the impact hole is 0.25-1.25, and the ratio of the distance H from the impact hole to the front edge rounding surface of the cap cover to the diameter D of the impact hole is 6-10;
the included angle between the wall surface of the forward-inclined expanding channel and the horizontal incoming flow is 30-42 degrees, the ratio of the length L of the forward-inclined expanding channel to the aperture D of the impact hole is 3-5, and the ratio of the exit aperture M of the forward-inclined expanding channel to the aperture D of the impact hole is 3-5.
2. The orifice plate forward-inclined aero-engine cap single-orifice impingement heat exchange structure of claim 1 wherein the distance between the two walls of the hot gas channel gradually shrinks from the front end of the fairing cap to the annular outlet of the channel.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910617191.9A CN110318881B (en) | 2019-07-10 | 2019-07-10 | Pore plate forward-inclined type aero-engine cap single-hole impact heat exchange structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910617191.9A CN110318881B (en) | 2019-07-10 | 2019-07-10 | Pore plate forward-inclined type aero-engine cap single-hole impact heat exchange structure |
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| CN110318881A CN110318881A (en) | 2019-10-11 |
| CN110318881B true CN110318881B (en) | 2021-09-14 |
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| CN201910617191.9A Active CN110318881B (en) | 2019-07-10 | 2019-07-10 | Pore plate forward-inclined type aero-engine cap single-hole impact heat exchange structure |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113027612B (en) * | 2021-04-14 | 2022-05-17 | 中国航空发动机研究院 | Heat exchanger adjusting mechanism for high-speed precooling engine and engine |
| CN113090391A (en) * | 2021-05-11 | 2021-07-09 | 西北工业大学 | Cap cover anti-icing heat transfer structure with air film hole and front edge impact |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB741336A (en) * | 1953-07-03 | 1955-11-30 | Armstrong Siddeley Motors Ltd | Anti-icing means for a gas turbine engine of an aircraft |
| GB846038A (en) * | 1958-03-21 | 1960-08-24 | Marston Excelsior Ltd | Improvements relating to anti-icing systems |
| US3925979A (en) * | 1973-10-29 | 1975-12-16 | Gen Electric | Anti-icing system for a 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 |
| CN105508054A (en) * | 2014-09-23 | 2016-04-20 | 中航商用航空发动机有限责任公司 | Engine gas inlet pipe anti-icing system and aircraft engine |
| CN105736145A (en) * | 2016-01-28 | 2016-07-06 | 南京航空航天大学 | Aircraft engine rectification cap anti-icing device and method adopting axial rotating heat pipe |
-
2019
- 2019-07-10 CN CN201910617191.9A patent/CN110318881B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB741336A (en) * | 1953-07-03 | 1955-11-30 | Armstrong Siddeley Motors Ltd | Anti-icing means for a gas turbine engine of an aircraft |
| GB846038A (en) * | 1958-03-21 | 1960-08-24 | Marston Excelsior Ltd | Improvements relating to anti-icing systems |
| US3925979A (en) * | 1973-10-29 | 1975-12-16 | Gen Electric | Anti-icing system for a 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 |
| CN105508054A (en) * | 2014-09-23 | 2016-04-20 | 中航商用航空发动机有限责任公司 | Engine gas inlet pipe anti-icing system and aircraft engine |
| CN105736145A (en) * | 2016-01-28 | 2016-07-06 | 南京航空航天大学 | Aircraft engine rectification cap anti-icing device and method adopting axial rotating heat pipe |
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| CN110318881A (en) | 2019-10-11 |
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