CN103850718A - Novel air-film hole with adjoint hole structures - Google Patents
Novel air-film hole with adjoint hole structures Download PDFInfo
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- CN103850718A CN103850718A CN201410025333.XA CN201410025333A CN103850718A CN 103850718 A CN103850718 A CN 103850718A CN 201410025333 A CN201410025333 A CN 201410025333A CN 103850718 A CN103850718 A CN 103850718A
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- China
- Prior art keywords
- air film
- film hole
- hole
- main
- cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an air-film cooling structure applicable to a turbine blade of an aeroengine. The air-film cooling structure comprises main cooling holes and adjoint cooling holes positioned at the two sides of main air-film holes. The air-film cooling structure is characterized in that the two sides of each main cooling hole are respectively provided with an adjoint cooling hole symmetrically penetrating. The novel air-film hole not only is easy in processing, but also is much higher in air-film cooling efficiency than the conventional air-film hole and has good application prospect.
Description
Technical field
In aeroengine, the Cooling Design of high-temperature component has determined overall performance and reliability to a great extent.The present invention relates to a kind of cooling structure of the turbine blade that is applicable to aeroengine and gas turbine engine.This structure comprises columniform main air film hole and two symmetrical auxiliary air film holes, can meet the requirement of High Performance Aeroengine of new generation for high-temperature component cooling performance.
Background technique
At present the common high-temperature unit of aircraft engine type of cooling has that air film is cooling, convection current is cooling, disperse cooling and Compound cooling etc.Air film cooling technology is the type of cooling of comparatively commonly using, and how the more effective air film of organizing is cooling, reduces cold air consumption, improves cooling effect, is the major issue that artificer pays close attention to always.In the cooling research of air film, in the last few years, in order to obtain higher gas film cooling efficiency, carried out a large amount of research both at home and abroad.Because traditional cylindric air film hole can produce kidney shape whirlpool in the process of Film Cooling and main combustion gas mixing, the blending of cold air and combustion gas around can be accelerated in kidney shape whirlpool, thereby reduce the area of effective coverage of cold air air film to hot-end component surface, reduce cooling effect, particularly with respect to flow direction on the film overcast of air film hole side direction, traditional column air film hole covering performance is poorer.Therefore,, in order to improve coverage property and the gas film cooling efficiency of cold air, the geometrical shape of air film hole has become the key issue of air film cooling technology primary study with arrangement mode.The research of air film hole pattern at present mainly concentrates on the following aspects mostly: compound angle jet, shaped film-hole, the air film with tab etc.The result of these researchs all shows to adopt this type of air film hole can effectively improve the cold air covering problem bringing due to the kidney shape whirlpool of columned film cooling holes generation, has obtained than traditional better Film Cooling of cylindric air film hole.It is all very complicated in geometrical construction that but these air film holes have comparatively common feature, and the geometric properties of these indents or evagination difficulty in manufacturing is huge, can produce the difficult problem such as processing technology and manufacture cost control thereupon.In addition, these geometric properties likely impact the aeroperformance of turbine blade, or even increase aerodynamic loss, reduce engine efficiency.What the present invention proposed is the Novel air fenestra that a kind of band is followed hole structure, the geometry pattern that air film pass adopts is all isometrical cylindrical holes, therefore be equal to conventional cylinder air film hole on difficulty of processing, the cooling effectiveness of the air film hole of the conventional single round hole pattern of this novel cooling boring ratio wants high a lot, by rational design and layout, its cooling effectiveness can reach the level of other air film holes such as compound angle jet air film hole.This Novel air fenestra is not only easy to processing but also can obtains more than the much higher gas film cooling efficiency of conventional cylinder air film hole in a word, is a kind of film cooling holes type that has very much practical prospect.
Summary of the invention
The object of this invention is to provide a kind of air film cooling structure that is applicable to aero engine turbine blades, comprise main Cooling Holes (1), what be positioned at main air film hole (1) both sides follows Cooling Holes (2), its major character is: respectively have one to follow Cooling Holes (2) in each main Cooling Holes (1) both sides, these two are followed Cooling Holes (2) is symmetrical, and following Cooling Holes (2) is penetration hole, and taking a main air film hole (1) and the monosymmetric air film hole (2) of following thereof as a cell cube (5), main air film hole (1) and follow air film hole (2) to be cylindrical, main air film hole (1) with dull and stereotyped be 10 °～50 ° along flowing to angle (α) scope, the diameter range of following air film hole (2) is 25%～100% of main air film hole (1) diameter (D), it is 0.2 (D)～2 (D) that main air film hole (1) is followed the span of the spacing (P1) of air film hole (2) with both sides, in air inlet one side, main Cooling Holes (1) and two follow the center in hole (2) in straight line, the side of giving vent to anger, follow the angle in hole (2) flowing to and free variation radially, following air film hole (2) and radial angle (β) scope of main air film hole (1) is 5 °～30 °, following air film hole (2) and dull and stereotyped angle (α 1) scope along the flow direction is 10 °～45 °.
The advantage of air film cooling structure of the present invention is: 1) main air film hole (1) and the geometry pattern of following air film hole (2) to adopt are all isometrical cylindrical holes, and therefore this Novel hole is equal to conventional cylinder air film hole on difficulty of processing, is convenient to practical application; 2) eddy current and the main air film hole (1) of following air film hole (2) to go out miscarriage life go out the raw vortex interaction of miscarriage, the kidney shape whirlpool producing can weaken main aperture and go out to flow time, make to draw the air film of stream not too early with high temperature mainstream gas (3) blending, cooled gas (4) can more cover and need cooling surface, thereby improve cooling air film area coverage problem, obtain higher cooling effectiveness; 3) because main air film hole (1) side direction goes out stream, side pressure is reduced, thus the flowing more to both sides diffusions of main air film hole (1), thus the overall film overcast rate of this pass is improved greatly; 4) specific blowing than and the stream that goes out in main and auxiliary hole can also effectively reduce aerodynamic loss and raise the efficiency in than scope.Above various features of the present invention can absolutely prove this pass be a kind of cooling effectiveness high and be easy to processing new pass.
Brief description of the drawings
Fig. 1 structure plan view of the present invention
Fig. 2 structural representation of the present invention
Fig. 3 schematic side view of the present invention
In figure: 1. main air film hole 2. is followed air film hole 3. high temperature main flow 4. cooled gases
5. structural unite body
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Shown in Figure 1, the present invention is a kind of air film cooling structure that is applicable to aero engine turbine blades.The structure of following air film hole (2) wherein running through is the major character that is different from other conventional air film hole.Follow the minimum unit body (5) of air film hole (2) as air film hole with 1 main air film hole (1) and taking the axis of main air film hole (1) as symmetry axis two, whole air film hole structure can think by multiple such cell cubes according to periodically and symmetry properties copy to expand and form.
Shown in Fig. 2,3, cooled gas (4) is entered by the import of main air film hole (1), above flat board, be high temperature mainstream gas (3), cooled gas (4) is from main air film hole (1) and auxiliary air film hole (2) outflow, under the effect of high temperature mainstream gas (3), be bent downwardly, stick near wall, the cold air film that formation temperature is lower, isolates wall with high temperature mainstream gas (3).Because the both sides of main air film hole (1) have oblique auxiliary air film hole (2), the kidney shape whirlpool of generation when the going out the raw eddy current of miscarriage and main air film hole (1) and go out the raw vortex interaction of miscarriage and can weaken main air film hole (1) and go out to flow of auxiliary air film hole (2), the air film that makes to draw stream can be not prematurely and high temperature mainstream gas (3) blending, cold air can more cover and need cooling surface, improves cooling effectiveness; Because the stream that goes out of auxiliary air film hole (2) reduces the mobile side pressure of main air film hole (1), flowing of winner's air film hole (1) more spread to both sides, thereby improve the coverage scale of air film hole sidepiece simultaneously, the film overcast rate of this pass is improved greatly.
Refer to shown in Fig. 1,2 and 3, generally, auxiliary air film hole (2) is that the symmetrical both sides and the diameter that are distributed in main air film hole (1) equates, also can be designed to as required asymmetric or diameter is unequal, but according to the principle of similitude, still think structure shown in the present, it is generally acknowledged main air film hole and dull and stereotyped be 10 °～50 ° along flowing to angle (α) scope, the radial angle (β) of following air film hole (2) and main air film hole (1) of the side of giving vent to anger is 5 °～30 °, the angle (α 1) of following air film hole (2) and dull and stereotyped edge to flow to of the side of giving vent to anger is 10 °～45 °, the center of following air film hole (2) and main air film hole (1) of air inlet one side is-3 (D)～3 (D) along the span of the distance (B) flowing to, following air film hole (2) and the diameter ratio of main air film hole (1) is 0.25～1, adjacent main air film hole (1) is 0.2 (D)～2 (D) with following the exhibition of air film hole (2) to the span of spacing (P1).The needs cooling according to air film, main aperture and the dull and stereotyped angle (α) along flowing to, the radial angle (β) of following air film hole (2) and main air film hole (1) of the side of giving vent to anger, the angle (α 1) of following air film hole (2) and dull and stereotyped edge to flow to of the side of giving vent to anger, air inlet one side follows the center of air film hole (2) and main air film hole (1) along the distance (B) flowing to, follow the diameter ratio of air film hole (2) and main air film hole (1), follow air film hole (2) and the span distance (P1) of main air film hole (1) to change, but because these all belong to theory of the present invention and principle, still think structure shown in the present.
The present invention has passed through the checking of Three-dimensional simulation and experiment, and under specific blowing ratio, its cooling effectiveness can improve 200%～300% than the cooling effectiveness of traditional round column air film hole, and cold air covers wider more even.
Claims (1)
1. one kind is applicable to the air film cooling structure of aero engine turbine blades, comprise main Cooling Holes (1), what be positioned at main air film hole (1) both sides follows Cooling Holes (2), its major character is: respectively have one to follow Cooling Holes (2) in each main Cooling Holes (1) both sides, these two are followed Cooling Holes (2) is symmetrical, and following Cooling Holes (2) is penetration hole, and taking a main air film hole (1) and the monosymmetric air film hole (2) of following thereof as a cell cube (5), main air film hole (1) and follow air film hole (2) to be cylindrical, main air film hole (1) with dull and stereotyped be 10 °～50 ° along flowing to angle (α) scope, the diameter range of following air film hole (2) is 25%～100% of main air film hole (1) diameter (D), it is 0.2 (D)～2 (D) that main air film hole (1) is followed the span of the spacing (P1) of air film hole (2) with both sides, in air inlet one side, main Cooling Holes (1) and two follow the center in hole (2) in straight line, the side of giving vent to anger, follow the angle in hole (2) flowing to and free variation radially, following air film hole (2) and radial angle (β) scope of main air film hole (1) is 5 °～30 °, following air film hole (2) and dull and stereotyped angle (α 1) scope along the flow direction is 10 °～45 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410025333.XA CN103850718A (en) | 2014-01-20 | 2014-01-20 | Novel air-film hole with adjoint hole structures |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410025333.XA CN103850718A (en) | 2014-01-20 | 2014-01-20 | Novel air-film hole with adjoint hole structures |
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| CN103850718A true CN103850718A (en) | 2014-06-11 |
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| CN201410025333.XA Pending CN103850718A (en) | 2014-01-20 | 2014-01-20 | Novel air-film hole with adjoint hole structures |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105626161A (en) * | 2015-12-25 | 2016-06-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Turbine blade with uneven cooling intensity in radial direction |
| CN106640216A (en) * | 2017-01-05 | 2017-05-10 | 河北工业大学 | Air film cooling hole structure |
-
2014
- 2014-01-20 CN CN201410025333.XA patent/CN103850718A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105626161A (en) * | 2015-12-25 | 2016-06-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Turbine blade with uneven cooling intensity in radial direction |
| CN106640216A (en) * | 2017-01-05 | 2017-05-10 | 河北工业大学 | Air film cooling hole structure |
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Application publication date: 20140611 |