CN103291459A - Gas film hole used for cooling gas turbine engine - Google Patents
Gas film hole used for cooling gas turbine engine Download PDFInfo
- Publication number
- CN103291459A CN103291459A CN2013102367805A CN201310236780A CN103291459A CN 103291459 A CN103291459 A CN 103291459A CN 2013102367805 A CN2013102367805 A CN 2013102367805A CN 201310236780 A CN201310236780 A CN 201310236780A CN 103291459 A CN103291459 A CN 103291459A
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- virtual cylinder
- hole
- sides
- air film
- inducer
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a gas film hole used for cooling a gas turbine engine, the gas film hole can be applied to cool high-temperature subassemblies such as a combustion chamber and a turbine of the gas turbine engine. The gas film hole comprises an inlet section and an expansion section, wherein the inlet section is a cylindrical hole, the expansion section is formed by a two-side virtual cylinder and a middle virtual cylinder which are superposed with each other and in connection, the two-side virtual cylinder is formed by expanding to two sides and then inclining forwards, the middle virtual cylinder is formed by extending the inlet section, the connection mode of the two-side virtual cylinder and the middle virtual cylinder adopts a way that two ends of a straight line are respectively tangent to and connected with the middle virtual cylinder and the two-side virtual cylinder, or adopts the way that two ends of multi-section polygonal lines and curves are respectively tangent to and connected with the middle virtual cylinder and the two-side virtual cylinder, and a chamfering is formed in an included angle; the gas film hole is expanded in the side direction through an outlet, so that the coverage area of cool air in the side direction is increased, and meanwhile, a flow field structure which is good for cooling the gas film is constructed by the forward inclining of a two-side virtual cylinder hole, so that the gas film cooling effect is integrally improved.
Description
Technical field
The present invention relates to gas turbine engine, specifically comprise generating heavy duty gas turbine, aeroengine and naval vessel gas turbine etc., it is the novel hole structure of a kind of discrete hole air film cooling (annotating: be also referred to as the film cooling), can improve the gas film cooling efficiency of high temperature parts such as gas-turbine unit turbine, firing chamber, be applicable to the air film cooling of all discrete hole forms.
Background technique
The operating temperature of modern gas turbine engines all surpasses the withstand temperature of metallic material.The air film cooling is widely used in the high-temperature component cooling of heavy duty gas turbine, aeroengine and naval vessel gas turbine as a kind of type of cooling efficiently.The air film cooling is cooled gas jet from one or more discrete hole, forms one deck gas membrane at wall and is not ablated by high-temperature gas with the protection wall.In gas turbine engine, the air that is used for cooling generally is the pressurized air of extracting out from the gas compressor corresponding stage, and the height of gas film cooling efficiency is directly connected to the size of air supply, thereby influences operational efficiency and the performance of complete machine.Air film cooling be by the leading two bursts of mutual blending of different temperatures fluid of convection current and with the convection heat exchange problem of cooling wall, and the key that improves gas film cooling efficiency to be restriction cold air eject the back from air film hole blows off with cooling wall, enlarge cooled gas simultaneously in the area coverage of wall, particularly enlarge the side direction coverage area of cold air; Therefore, particularly important with the formed flow field structure of high temperature main flow behind the cool air injection.Traditional cylinder type air film hole has formed kidney shape vortex pair in the air film coolant flow field, this vortex system structure makes cold air and cooling wall blow off under the high temperature main flow is involved in the cold air jet from both sides, causes the deterioration of cooling effect; And traditional moulding hole has enlarged the area of hole exits, reduced the outlet momentum of impinging jet of cold air, thereby weakened the generation in kidney shape whirlpool, in addition owing to discharge area enlarges the side direction coverage area that has increased cold air, thereby obtained the air film cooling effect that more has with respect to cylindrical hole, but traditional moulding hole also still can't initiatively produce the flow field vortex system structure that is conducive to the air film cooling; Subsequently in order to construct the flow field vortex system structure that is conducive to the air film cooling, by experts and scholars two or more cylindrical holes are formed an air film hole unit, as the dijection discharge orifice, tripod hole etc., however there is the difficulty of manufacturing aspect in the air film hole structure that these porous are formed and is difficult to the deficiency of aspects such as being applied under the limited air supply space condition of blade.
Summary of the invention
The objective of the invention is to disclose a kind of air film hole for the gas turbine engine cooling, to improve the gas film cooling efficiency of gas turbine engine.
Technological scheme of the present invention is as follows:
A kind of air film hole for the gas turbine engine cooling, it is characterized in that: this air film hole comprises inducer and extending section, inducer is cylindrical hole, extending section is formed by connecting by intermediate virtual cylinder and both sides virtual cylinder, be specially: extending section is that initial point begins to expand to bilateral symmetry with the terminal center of circle of inducer, form and the isodiametric both sides of inducer virtual cylinder, both sides virtual cylinder center line and inducer center line form angle β, the both sides virtual cylinder is that initial point leans forward with the terminal center of circle of inducer subsequently, form top rake γ on the front elevation projection plane with the intermediate virtual cylinder, both sides virtual cylinder and intermediate virtual cylinder mutual superposition and be connected to form extending section, the Placement of both sides virtual cylinder and intermediate virtual cylinder adopts the straight line two ends respectively with the intermediate virtual cylinder and the both sides virtual cylinder is tangent is connected, or employing multistage broken line, the curve two ends are respectively with the intermediate virtual cylinder and the both sides virtual cylinder is tangent is connected, and form the chamfering of circular arc or irregular curvature in the angle.
Air film hole entrance length L of the present invention
1With the hole total length L
0Ratio delta between 0～1, general span is between 1/3 to 2/3; The span of the both sides angle β of both sides virtual cylinder and intermediate virtual cylinder is 8 °～25 °, and the span of top rake γ is 1 °～4.5 °; The angle of this air film hole and cooling wall in the use, namely efflux angle is 20 °～60 °.
The present invention has the following advantages and the technique effect of high-lighting: this film cooling holes structure can will enlarge cold air side direction coverage area and be configured with the flow field vortex system structure two great tradition moulding holes that are beneficial to the air film cooling and advantage that the porous combination is had respectively rolls into one, namely this air film hole increases the hole exits area by the both sides expansion, thereby increase the side direction coverage area of cold air, leaning forward and be connected with the smooth of intermediate virtual cylindrical hole by virtual cylinder hole, both sides simultaneously, construct the flow field structure that is conducive to the air film cooling, thus the whole air film cooling effect that improves; Showing by dull and stereotyped air film cooling experiment, is under 1.0 and 1.5 conditions at the density ratio, and than being in 0.5～2.0 scope, the zone leveling gas film cooling efficiency of film cooling holes of the present invention can improve 20%～40% than traditional moulding hole in blowing.
Description of drawings
Fig. 1 is the schematic three dimensional views of a kind of air film hole for gas turbine engine cooling of the present invention.
Fig. 2 is the plan view of film cooling holes of the present invention.
Fig. 3 is the front elevation of film cooling holes of the present invention.
Fig. 4 is that film cooling holes of the present invention is perpendicular to the sectional view of axially bored line.
Fig. 5 is the axially bored line sectional view of the similar structural change of film cooling holes topology of the present invention.
Fig. 6 is applied to the schematic representation of dull and stereotyped air film cooling for film cooling holes of the present invention.
Fig. 7 be film cooling holes of the present invention be used for dull and stereotyped air film cooling experimental measurements and with the comparing result in the traditional moulding of identical operating mode hole.
Embodiment
Below in conjunction with accompanying drawing structure of the present invention, principle and performance are described:
The present invention is a kind of hole structure that is applicable to the cooling of gas turbine engine type air film, its basic cell structure is as shown in Figure 1: this air film hole comprises inducer 1 and extending section 2, inducer 1 is cylindrical hole, extending section 2 is formed by connecting by intermediate virtual cylinder 3 and both sides virtual cylinder 4, be specially: extending section 2 is that initial point begins to expand to bilateral symmetry with the inducer 1 terminal center of circle, form and the isodiametric both sides of inducer virtual cylinder 4, both sides virtual cylinder 4 center lines and inducer 1 center line form angle β, as shown in Figure 2; Both sides virtual cylinder 4 is that initial point leans forward with the inducer 1 terminal center of circle subsequently, forms top rake γ on the front elevation projection plane with intermediate virtual cylinder 3, as shown in Figure 3; Both sides virtual cylinder 4 is with intermediate virtual cylinder 3 mutual superposition and be connected to form extending section 2, the Placement of both sides virtual cylinder 4 and intermediate virtual cylinder 3 adopt the straight line two ends respectively with intermediate virtual cylinder 3 and 4 tangent connections of both sides virtual cylinder, or adopt multistage broken line, curve two ends respectively with intermediate virtual cylinder 3 and 4 tangent connections of both sides virtual cylinder, and form the chamfering of circular arc or irregular curvature in the angle, as shown in Figure 4; What Fig. 5 showed is the air film hole vertical axis schematic cross-section that intermediate virtual cylinder 3 is connected by broken line with both sides virtual cylinder 4 and forms when the end angle adopts circular arc chamfering.The length of this air film hole inducer 1 is L
1,, the length of extending section is L
2,, the length L of air film hole inducer
1With the hole total length L
0Ratio delta between 0 to 1, general value is between 1/3 to 2/3; Both sides virtual cylinder 4 is 8 °～25 ° with the span of the both sides angle β of intermediate virtual cylinder 3, and the span of top rake γ is 1 °～4.5 °; The angle of this air film hole and cooling wall in the use, namely efflux angle α is generally 20 °～60 °.
Fig. 6 is the application example of novel air film hole structure of the present invention in dull and stereotyped air film cooling, and the efflux angle α of this air film hole is 30 ° in this application example.The cooled gas 5 air film hole of the present invention ejection of flowing through forms air films on cooling wall 6 surfaces and covers, simultaneously dissipation final with the 7 mutual blending of high temperature main flow.The air film coverage effect directly depends on the jet form of cold airflow behind air film hole and the flow field structure in downstream air film district.Air film hole of the present invention increases the hole exits area by the both sides expansion, thereby increase the side direction coverage area of cold air, leaning forward and be connected with the smooth of intermediate virtual cylinder 3 by both sides virtual cylinder 4 simultaneously, construct the flow field structure that is conducive to the air film cooling, thus the whole air film cooling effect that improves.The ratio delta of inducer 1 length and hole total length, lateral spread angle beta and both sides top rake γ are the major character parameters of film cooling holes of the present invention, also are the key parameters that influences its air film cooling performance.
Fig. 7 is the experimental measurements that film cooling holes of the present invention is applied to dull and stereotyped air film cooling, and experiment condition is 1.0 and 1.5 for the density ratio, and blowing is than being 0.5～2.0, and experiment compares under identical working condition with traditional moulding hole simultaneously.Curve 8 and curve 9 are respectively air film holes of the present invention in density than being zone leveling gas film cooling efficiency under 1.0 and 1.5 conditions, curve 10 and curve 11 are respectively traditional moulding holes in density than being zone leveling gas film cooling efficiency under 1.0 and 1.5 conditions, contrast the zone leveling gas film cooling efficiency of air film hole of the present invention and the zone leveling gas film cooling efficiency in traditional moulding hole, and the zone leveling gas film cooling efficiency of air film hole of the present invention and the zone leveling gas film cooling efficiency in traditional moulding hole, the result shows that at the density ratio be under 1.0 and 1.5 conditions, than being in 0.5～2.0 scope, the zone leveling gas film cooling efficiency of film cooling holes of the present invention can improve 20%～40% than traditional moulding hole in blowing.
Claims (3)
1. one kind is used for the air film hole that gas turbine engine cools off, it is characterized in that: this air film hole comprises inducer (1) and extending section (2), inducer (1) is cylindrical hole, extending section (2) is formed by connecting by intermediate virtual cylinder (3) and both sides virtual cylinder (4), be specially: extending section is that initial point begins to expand to bilateral symmetry with the terminal center of circle of inducer (1), form and the isodiametric both sides of inducer virtual cylinders (4), both sides virtual cylinder (4) center line and inducer (1) center line form angle β, both sides virtual cylinder (4) is that initial point leans forward with the terminal center of circle of inducer (1) subsequently, form top rake γ on the front elevation projection plane with intermediate virtual cylinder (3), both sides virtual cylinder (4) is with intermediate virtual cylinder (3) mutual superposition and be connected to form extending section (2), the Placement of both sides virtual cylinder (4) and intermediate virtual cylinder (3) adopt the straight line two ends respectively with intermediate virtual cylinder (3) and tangent connection of both sides virtual cylinder (4), or employing multistage broken line, the curve two ends respectively with intermediate virtual cylinder (3) and tangent connection of both sides virtual cylinder (4), and form the chamfering of circular arc or irregular curvature in the angle.
2. according to the described a kind of air film hole for the gas turbine engine cooling of claim 1, it is characterized in that: the length L of the inducer of described air film hole (1)
1With the hole total length L
0Ratio delta between 0～1; Both sides virtual cylinder (4) is 8 °～25 ° with the span of the both sides angle β of intermediate virtual cylinder (3), and the span of top rake γ is 1 °～4.5 °.
3. according to the described a kind of air film hole for the gas turbine engine cooling of claim 2, it is characterized in that: the length L of the inducer of described air film hole (1)
1With the hole total length L
0Ratio delta between 1/3 to 2/3; The angle of this air film hole and cooling wall in the use, namely efflux angle is 20 °～60 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310236780.5A CN103291459B (en) | 2013-06-14 | 2013-06-14 | A kind of air film hole for gas turbine engine cooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310236780.5A CN103291459B (en) | 2013-06-14 | 2013-06-14 | A kind of air film hole for gas turbine engine cooling |
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| Publication Number | Publication Date |
|---|---|
| CN103291459A true CN103291459A (en) | 2013-09-11 |
| CN103291459B CN103291459B (en) | 2016-02-24 |
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| CN201310236780.5A Active CN103291459B (en) | 2013-06-14 | 2013-06-14 | A kind of air film hole for gas turbine engine cooling |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104598684A (en) * | 2015-01-19 | 2015-05-06 | 西北工业大学 | Parametric modeling method for film hole |
| CN105298649A (en) * | 2015-11-20 | 2016-02-03 | 清华大学 | Gas film cooling hole structure used for thin-walled hot end part of gas turbine engine |
| CN106555617A (en) * | 2017-01-05 | 2017-04-05 | 西北工业大学 | A kind of turbo blade for having oblique bottom blowing type film cooling holes |
| CN106640216A (en) * | 2017-01-05 | 2017-05-10 | 河北工业大学 | Air film cooling hole structure |
| CN107631881A (en) * | 2017-08-30 | 2018-01-26 | 华能国际电力股份有限公司 | Full-size multifunctional gas turbine combustion test system |
| CN112855280A (en) * | 2021-01-29 | 2021-05-28 | 南京航空航天大学 | Large-inclination-angle air film cooling hole based on ceramic matrix composite material and design method thereof |
| CN113279818A (en) * | 2021-06-24 | 2021-08-20 | 中国科学院工程热物理研究所 | Contraction type double-jet air film hole |
| CN114893255A (en) * | 2022-05-12 | 2022-08-12 | 中国航发四川燃气涡轮研究院 | Crescent air film hole structure and forming method, turbine blade and machining method thereof |
| CN116085117A (en) * | 2023-04-10 | 2023-05-09 | 清华大学 | Guiding structure |
| CN116085118A (en) * | 2023-04-10 | 2023-05-09 | 清华大学 | Guiding structure |
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| CN86108864A (en) * | 1985-12-23 | 1987-08-19 | 联合工艺公司 | Air film cooling channel through improving with fillet |
| EP0648918A1 (en) * | 1993-10-15 | 1995-04-19 | United Technologies Corporation | Film cooling passages for thin walls |
| US6287075B1 (en) * | 1997-10-22 | 2001-09-11 | General Electric Company | Spanwise fan diffusion hole airfoil |
| CN203362321U (en) * | 2013-06-14 | 2013-12-25 | 清华大学 | Film hole used for cooling of gas turbine engine |
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2013
- 2013-06-14 CN CN201310236780.5A patent/CN103291459B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86108864A (en) * | 1985-12-23 | 1987-08-19 | 联合工艺公司 | Air film cooling channel through improving with fillet |
| EP0648918A1 (en) * | 1993-10-15 | 1995-04-19 | United Technologies Corporation | Film cooling passages for thin walls |
| US6287075B1 (en) * | 1997-10-22 | 2001-09-11 | General Electric Company | Spanwise fan diffusion hole airfoil |
| CN203362321U (en) * | 2013-06-14 | 2013-12-25 | 清华大学 | Film hole used for cooling of gas turbine engine |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104598684B (en) * | 2015-01-19 | 2017-07-18 | 西北工业大学 | A kind of air film hole parametric modeling method |
| CN104598684A (en) * | 2015-01-19 | 2015-05-06 | 西北工业大学 | Parametric modeling method for film hole |
| CN105298649A (en) * | 2015-11-20 | 2016-02-03 | 清华大学 | Gas film cooling hole structure used for thin-walled hot end part of gas turbine engine |
| CN106555617A (en) * | 2017-01-05 | 2017-04-05 | 西北工业大学 | A kind of turbo blade for having oblique bottom blowing type film cooling holes |
| CN106640216A (en) * | 2017-01-05 | 2017-05-10 | 河北工业大学 | Air film cooling hole structure |
| CN106555617B (en) * | 2017-01-05 | 2018-07-10 | 西北工业大学 | A kind of turbo blade for having oblique bottom blowing type film cooling holes |
| CN106640216B (en) * | 2017-01-05 | 2019-12-10 | 河北工业大学 | Air film cooling hole type structure |
| CN107631881B (en) * | 2017-08-30 | 2023-06-13 | 华能国际电力股份有限公司 | Full-size multifunctional gas turbine combustion test system |
| CN107631881A (en) * | 2017-08-30 | 2018-01-26 | 华能国际电力股份有限公司 | Full-size multifunctional gas turbine combustion test system |
| CN112855280A (en) * | 2021-01-29 | 2021-05-28 | 南京航空航天大学 | Large-inclination-angle air film cooling hole based on ceramic matrix composite material and design method thereof |
| CN112855280B (en) * | 2021-01-29 | 2022-06-17 | 南京航空航天大学 | Large-inclination-angle air film cooling hole based on ceramic matrix composite and design method thereof |
| CN113279818B (en) * | 2021-06-24 | 2022-10-21 | 中国科学院工程热物理研究所 | Contraction type double-jet air film hole |
| CN113279818A (en) * | 2021-06-24 | 2021-08-20 | 中国科学院工程热物理研究所 | Contraction type double-jet air film hole |
| CN114893255A (en) * | 2022-05-12 | 2022-08-12 | 中国航发四川燃气涡轮研究院 | Crescent air film hole structure and forming method, turbine blade and machining method thereof |
| CN114893255B (en) * | 2022-05-12 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | Crescent air film hole structure, forming method, turbine blade and processing method thereof |
| CN116085117A (en) * | 2023-04-10 | 2023-05-09 | 清华大学 | Guiding structure |
| CN116085118A (en) * | 2023-04-10 | 2023-05-09 | 清华大学 | Guiding structure |
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| CN103291459B (en) | 2016-02-24 |
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