CN201650376U - Single-inlet double-outlet hole structure applied to turbine blade air film cooling technology - Google Patents
Single-inlet double-outlet hole structure applied to turbine blade air film cooling technology Download PDFInfo
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- CN201650376U CN201650376U CN2010201419448U CN201020141944U CN201650376U CN 201650376 U CN201650376 U CN 201650376U CN 2010201419448 U CN2010201419448 U CN 2010201419448U CN 201020141944 U CN201020141944 U CN 201020141944U CN 201650376 U CN201650376 U CN 201650376U
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- turbine blade
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- cylinder hole
- air film
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Abstract
The utility model relates to a single-inlet double-outlet hole structure applied to a turbine blade air film cooling technology. The structure comprises a turbine blade, an air film hole inlet, a main cylinder hole and a secondary cylinder hole, wherein the air film hole inlet, the main cylinder hole and the secondary cylinder hole are arranged on the turbine blade; the included angle between the central axis of the main cylinder hole and the wall surface of the turbine blade is 20-60 degrees; the second cylinder hole is arranged on the inner wall of the main cylinder hole and intersects with the main cylinder hole; the diameter of the secondary cylinder hole is smaller than the diameter of the main cylinder hole; the inclined angle between the central axis of the secondary cylinder hole and the surface wall of the turbine blade is 30-90 degrees, which is larger than the inclined angle of the central axis of the main cylinder hole and the wall surface of the turbine blade; the inclined angle (i.e. the azimuth angle of the secondary hole) between the projection of the central axis of the main cylinder and the projection of the central axis of the secondary cylinder on the surface of the turbine blade is 30-90 degrees; and a distance from the intersection point of the axis of the secondary cylinder hole and the axis of the main cylinder hole to the center of an air film inlet is L which is 1.5 times as large as the diameter of the main cylinder hole. The utility model has simple structure, easy processing and good heat insulation effect.
Description
Technical field: the utility model relates to the cooling technology on a kind of gas turbine blades, especially a kind of single inlet-two exit orifice structures that are applied to turbine blade air film cooling technology.
Background technique: the air film cooling is the cooling technology that is applied on the gas turbine blades, promptly extract high pressure cold and be transported to the blade interior passage from the gas compressor final stage, cold air is strengthened convection heat exchange a part of heat is taken away in passage, a part of cold air sprays from the air film hole on the blade wall simultaneously, under the squeezing action of high-temperature fuel gas, be attached to blade surface, high-temperature fuel gas and blade surface are separated, to reach the purpose that blade is not burnt out by high-temperature fuel gas.Mainly be cylindrical hole and export expansion type hole on the turbine blade at present, not only flow resistance is big when cylindrical hole sprays into high-temperature fuel gas from the cooling channel for cold air, and effect of heat insulation is also limited.The effect of heat insulation of cold air when the expanding hole sprays into high-temperature fuel gas is better, but the difficulty of processing in expanding hole is big, the cost height.Along with motor power continues to increase, the gas compressor pressure ratio improves constantly, and fuel gas temperature also constantly rises, and adopts the deficiency of cylindrical hole just to seem more and more outstanding in the air film cooling technology.
Summary of the invention: in order to reduce difficulty of processing, improve the yield rate of blade processing, the utility model proposes single inlet-two fenestras of working off one's feeling vent one's spleen of being made up of two cylindrical holes, this pass has high effect of heat insulation, less cold air circulating resistance and simple machining process.
For achieving the above object, the technical solution adopted in the utility model is: be applied to single inlet-two exit orifice structures of turbine blade air film cooling technology, comprise turbine blade and the air film hole inlet, principal cylindrical bore and the inferior cylindrical hole that are on the turbine blade.Principal cylindrical bore central axis and turbine blade wall angle are 20 to spend to 60 degree, and inferior cylindrical hole is on the inwall of principal cylindrical bore, intersects with principal cylindrical bore, and the diameter of inferior cylindrical hole is less than the diameter of principal cylindrical bore.Inferior cylindrical hole central axis and turbine blade wall angle be greater than principal cylindrical bore central axis and turbine blade wall angle, is 30 to spend to 90 degree.The principal cylindrical bore medial axis turbine blade surface projection and time cylindrical hole medial axis the angle (i.e. time azimythal angle, hole) of turbine blade surface projection be 30 spend spend to 90 between.The intersection point of inferior cylindrical hole axis and principal cylindrical bore axis is 1～1.5 times of principal cylindrical bore diameter to the distance L at air film hole inlet center.
The utility model is originally simple in structure, easy processing, good heat-insulation effect.
Description of drawings:
Fig. 1 is the structural representation of principal cylindrical bore and time cylindrical hole.
Fig. 2 is the structural representation of principal cylindrical bore at the turbine blade diverse location.
Fig. 3 is air film hole viewpoint definition figure.
Embodiment:
As shown in Figure 1-Figure 3, be applied to single inlet-two exit orifice structures of turbine blade air film cooling technology, comprise turbine blade 7 and the air film hole inlet 3, principal cylindrical bore 1 and the inferior cylindrical hole 2 that are on the turbine blade 7.Principal cylindrical bore 1 central axis and turbine blade 7 wall angles are 20 to spend to 60 degree, and inferior cylindrical hole 2 is on the inwall of principal cylindrical bore 1, intersects with principal cylindrical bore 1, and the diameter of inferior cylindrical hole 2 is less than the diameter of principal cylindrical bore 1.Inferior cylindrical hole 2 central axis and turbine blade 7 wall angles are greater than principal cylindrical bore 1 central axis and turbine blade wall 7 angles, are 30 to spend to 90 degree.At first on turbine blade 7, need the position of perforate to utilize cylindrical drill to be processed into cylindrical hole, it is principal cylindrical bore 1, the inclination alpha in hole (being hole central axis and turbine blade wall angle) be 20 spend to 60 the degree, the drill bit processing time cylindrical hole 2 of bit diameter when utilizing diameter then less than the processing main aperture, its angle of inclination beta (being hole central axis and turbine blade wall angle) be 30 spend to 90 the degree, inferior hole azimythal angle γ be 30 spend to 90 the degree between.And guarantee that time cylindrical hole 2 inclination angles are greater than principal cylindrical bore 1 inclination angle.Inferior cylindrical hole 2 degree of depth are and principal cylindrical bore 1 crossing getting final product.Principal cylindrical bore 1 diameter is between 0.3mm～1mm, and inferior cylindrical hole diameter is 0.5～0.9 times of principal cylindrical bore diameter.The intersection point of inferior cylindrical hole axis and principal cylindrical bore axis is 1～1.5 times of principal cylindrical bore diameter to the distance L at air film hole inlet center.
Pressure side at turbine blade 7 utilizes the principal cylindrical bore of cylindrical drill processing diameter for 0.5mm, and α is 30 degree.Process time hole then, β is 60 degree, and inferior hole azimythal angle γ is 45 degree, and inferior bore dia is 0.4mm, and inferior cylindrical hole hole depth and main aperture are crossing to get final product, and the L distance that the focus of inferior cylindrical hole axis and principal cylindrical bore axis arrives air film hole inlet center is 0.75mm.
Utilize the principal cylindrical bore of cylindrical drill processing diameter for 0.4mm at turbine blade 7 suction faces, α is 45 degree.Processing time hole then, β is 75 degree, and inferior hole azimythal angle γ is 60 degree, and inferior bore dia is 0.3mm, and inferior cylindrical hole hole depth and main aperture intersect and get final product, and the intersection point of inferior cylindrical hole axis and principal cylindrical bore axis enters the mouth the L at center apart from being 0.5mm to air film hole.
Claims (2)
1. be applied to single inlet-two exit orifice structures of turbine blade air film cooling technology, the air film hole that comprises turbine blade and be on the turbine blade enters the mouth and principal cylindrical bore, it is characterized in that: also comprise being in cylindrical hole on the turbine blade and inferior, principal cylindrical bore central axis and turbine blade wall angle be 20 spend to 60 the degree, inferior cylindrical hole is on the inwall of principal cylindrical bore, intersect with principal cylindrical bore, the diameter of inferior cylindrical hole is less than the diameter of principal cylindrical bore; Inferior cylindrical hole central axis and turbine blade wall angle be greater than principal cylindrical bore central axis and turbine blade wall angle, is 30 to spend to 90 degree; The principal cylindrical bore medial axis is 30 to spend between 90 degree in turbine blade surface projection and inferior cylindrical hole medial axis at the angle of turbine blade surface projection; The intersection point of inferior cylindrical hole axis and principal cylindrical bore axis is 1～1.5 times of principal cylindrical bore diameter to the distance L at air film hole inlet center.
2. the single inlet-two exit orifice structures that are applied to turbine blade air film cooling technology as claimed in claim 1, it is characterized in that: the diameter of principal cylindrical bore is between 0.3mm～1mm, and the diameter of inferior cylindrical hole is 0.5～0.9 times of principal cylindrical bore diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201419448U CN201650376U (en) | 2010-03-26 | 2010-03-26 | Single-inlet double-outlet hole structure applied to turbine blade air film cooling technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201419448U CN201650376U (en) | 2010-03-26 | 2010-03-26 | Single-inlet double-outlet hole structure applied to turbine blade air film cooling technology |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201650376U true CN201650376U (en) | 2010-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201419448U Expired - Fee Related CN201650376U (en) | 2010-03-26 | 2010-03-26 | Single-inlet double-outlet hole structure applied to turbine blade air film cooling technology |
Country Status (1)
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| CN (1) | CN201650376U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102116178A (en) * | 2011-01-18 | 2011-07-06 | 中国科学院工程热物理研究所 | Dual-jet hole cooling structure of air cooled turbine |
| CN104879171A (en) * | 2015-05-08 | 2015-09-02 | 西北工业大学 | Y-shaped air film hole structure used for turbine blade |
| CN104895620A (en) * | 2015-04-20 | 2015-09-09 | 西北工业大学 | Arrow-shaped double-hole unit structure for air film cooling |
| CN105952496A (en) * | 2016-05-26 | 2016-09-21 | 沈阳航空航天大学 | Turbine blade with large inclined holes and small vertical holes arranged in staggered manner |
| CN106246238A (en) * | 2016-07-25 | 2016-12-21 | 西北工业大学 | A kind of stepped ramp type shrinks film hole structure |
| CN107701240A (en) * | 2017-11-27 | 2018-02-16 | 中国科学院工程热物理研究所 | A kind of branch film hole structure of air-cooled turbine |
| US10508555B2 (en) | 2017-12-05 | 2019-12-17 | United Technologies Corporation | Double wall turbine gas turbine engine blade cooling configuration |
| US10648345B2 (en) | 2017-12-05 | 2020-05-12 | United Technologies Corporation | Double wall turbine gas turbine engine blade cooling configuration |
| CN112761733A (en) * | 2021-01-08 | 2021-05-07 | 西安交通大学 | Cross air film cooling hole structure capable of inhibiting development of kidney-shaped vortex pairs and application thereof |
| CN113090334A (en) * | 2021-04-23 | 2021-07-09 | 西北工业大学 | Front and rear hole split-flow type air film injection structure for turbine blade |
-
2010
- 2010-03-26 CN CN2010201419448U patent/CN201650376U/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102116178A (en) * | 2011-01-18 | 2011-07-06 | 中国科学院工程热物理研究所 | Dual-jet hole cooling structure of air cooled turbine |
| CN104895620A (en) * | 2015-04-20 | 2015-09-09 | 西北工业大学 | Arrow-shaped double-hole unit structure for air film cooling |
| CN104895620B (en) * | 2015-04-20 | 2016-08-10 | 西北工业大学 | A kind of arrowhead-shaped diplopore cellular construction for gaseous film control |
| CN104879171A (en) * | 2015-05-08 | 2015-09-02 | 西北工业大学 | Y-shaped air film hole structure used for turbine blade |
| CN105952496B (en) * | 2016-05-26 | 2018-06-26 | 沈阳航空航天大学 | A kind of big angling hole and the staggered turbo blade of small upright opening |
| CN105952496A (en) * | 2016-05-26 | 2016-09-21 | 沈阳航空航天大学 | Turbine blade with large inclined holes and small vertical holes arranged in staggered manner |
| CN106246238A (en) * | 2016-07-25 | 2016-12-21 | 西北工业大学 | A kind of stepped ramp type shrinks film hole structure |
| CN107701240A (en) * | 2017-11-27 | 2018-02-16 | 中国科学院工程热物理研究所 | A kind of branch film hole structure of air-cooled turbine |
| CN107701240B (en) * | 2017-11-27 | 2019-02-15 | 中国科学院工程热物理研究所 | A kind of branch's film hole structure of air-cooled turbine |
| US10508555B2 (en) | 2017-12-05 | 2019-12-17 | United Technologies Corporation | Double wall turbine gas turbine engine blade cooling configuration |
| US10648345B2 (en) | 2017-12-05 | 2020-05-12 | United Technologies Corporation | Double wall turbine gas turbine engine blade cooling configuration |
| CN112761733A (en) * | 2021-01-08 | 2021-05-07 | 西安交通大学 | Cross air film cooling hole structure capable of inhibiting development of kidney-shaped vortex pairs and application thereof |
| CN113090334A (en) * | 2021-04-23 | 2021-07-09 | 西北工业大学 | Front and rear hole split-flow type air film injection structure for turbine blade |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101124 Termination date: 20150326 |
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| EXPY | Termination of patent right or utility model |