CN109736897A - A kind of chiasma type Y air film hole cooling structure for turbo blade - Google Patents
A kind of chiasma type Y air film hole cooling structure for turbo blade Download PDFInfo
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- CN109736897A CN109736897A CN201910007232.2A CN201910007232A CN109736897A CN 109736897 A CN109736897 A CN 109736897A CN 201910007232 A CN201910007232 A CN 201910007232A CN 109736897 A CN109736897 A CN 109736897A
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Abstract
It is to arrange two rows Y air film hole along flow direction on air film orifice plate, and air film hole is arranged using chiasma type the invention discloses a kind of chiasma type Y air film hole cooling structure for turbo blade；Y air film hole is formed by extending its interface after mutually passing through two cylindrical air film holes intersections, and the outlet of two cylindrical air film holes is extended to there is certain tilt angle.Chiasma type Y air film hole cooling structure make that jet stream is more easier point to both sides, increase the exhibition of jet stream to covering, and reduce the aerodynamic loss of jet stream；By the interaction of front two rows Y air film hole, curls inward is formed to whirlpool in air film hole downstream, so that the cold air for leaving Y air film hole is tightly covered near wall, effect protection is formed with to air film hole downstream wall surface.Y air film hole has an air film hole entrance, and section is divided into two strands of cold air in the channel, so that the gas output of Y air film hole two outlets is more uniform, Y air film hole has structure simple, easy to process, and the feature that film overcast effect is good.
Description
Technical field
The present invention relates to the cooling technology fields of turbine blade of gas turbine, specifically, being related to a kind of for turbine leaf
The chiasma type Y air film hole cooling structure of piece.
Technical background
Gas turbine since the advent of the world, is widely used in industry after decades of development.In industrial application, design
Turbine inlet temperature has been gradually increased according to engineering thermal circulation theory in persons, this makes the performance of gas turbine obtain effectively mentioning
It rises.But it is constrained to the temperature capability of turbo blade material, the temperature before turbine has reached a bottleneck, therefore, it is necessary to whirlpool
Impeller blade, which carries out effective cooling, just can guarantee that gas turbine safely and efficiently works.Gaseous film control is as a kind of external cooling side
Formula is widely used in the Cooling Design of turbo blade.The basic principle of gaseous film control: on high-temperature component slot driller or
Aperture sprays into cold air to mainstream in a certain direction, and under pressure and the frictional force effect of mainstream, jet stream bending is covered in high-temperature portion
Wall surface is isolated with high-temperature fuel gas, and takes away part high-temperature fuel gas or clear flame by part surface, the lower cold air film of formation temperature
To the radiations heat energy of wall surface, to play a good protective effect to wall surface.
Initially applying the film cooling holes on turbo blade is cylindrical hole, and Eckert et al. is earlier to cylinder air film hole
Cooling effect carried out experimental study, cylindrical hole of the discovery with compound angle has good Film Cooling.With grinding
Study carefully going deep into for work, domestic and foreign scholars have found cylindrical hole due to its structural limitations, and the exhibition of cold airflow is bad to coverage effect；And
And since the cold flow normal direction momentum projected from cylindrical hole is larger, cause jet stream cooling effect near wall poor.Based on this, state
The inside and outside research about pass concentrates in profiled holes.The scholars such as Goldstein, which study discovery scallop hole, can reduce cold airflow
Normal direction momentum increases cold air in the area coverage of turbine blade surface, ultimately improves gas film cooling efficiency.In order to more into one
Step improves Film Cooling, and the cooling pore structure in shrinkage expansion hole is also suggested.It is worth noting that, profiled holes provide Gao Leng
But aerodynamic loss is also increased while efficiency.
Summary of the invention
In order to avoid the shortcomings of the prior art, the present invention proposes a kind of chiasma type Y air film hole for turbo blade
Cooling structure；The structure can continue to improve the exhibition of jet stream to covering, and reduce the aerodynamic loss of jet stream, so that leaving air film hole
Cold air is tightly covered near wall, promotes the gas output uniformity of different air film hole exits, and easy to manufacture.
The technical solution adopted by the present invention to solve the technical problems is: including air film orifice plate, upstream Y air film hole, downstream Y
Air film hole, cylinder air film hole, pressure face chiasma type Y air film hole, suction surface chiasma type Y air film hole, inner cooling path, in turbo blade
Pressure face is equipped with pressure face chiasma type Y air film hole, and suction surface chiasma type Y air film hole, pressure are equipped on turbo blade suction surface
The both ends of power face chiasma type Y air film hole and suction surface chiasma type Y air film hole are respectively formed outlet and the entrance of air-flow, and with it is interior cold
But channel communicates, it is characterised in that along flow direction arrangement two rows Y air film hole on air film orifice plate, and two rows of air film holes use chiasma type
Arrangement, Y air film hole are formed by extending its interface after mutually passing through two cylindrical air film hole intersections, two cylindrical air films
The outlet in hole is extended to there is certain tilt angle, and the distance of upstream two hole exits central points of Y air film hole is W, downstream Y gas
The distance of two hole exits central points of fenestra is V, and wherein the value of W is more than or equal to the value of V；Upstream Y air film hole and downstream Y air film hole
Flow to spacing be P；The exhibition of upstream Y air film hole to the exhibition of spacing and downstream Y air film hole to spacing be S；Upstream Y air film hole and
The span distance of the cylindrical hole crossing center point of downstream Y air film hole is 0.5S；The smallest cross-sectional equivalent diameter D of cylinder air film holef,
Value range is 0.5~1.5mm.
Two cylinder air film hole intersecting angles of the upstream Y air film hole are α, and value range is 45~95 °, upstream Y gas
The value range that fenestra flows to inclination angle theta is 30~60 °, and two cylinder air film hole intersecting angles of downstream Y air film hole are β, value
Range is 40~90 °, and the value range for flowing to tilt angle gamma of downstream Y air film hole is 30~60 °.
The spacing that flows to of the upstream Y air film hole and downstream Y air film hole is P, in the range of 2Df~5Df, upstream Y air film hole
Exhibition with downstream Y air film hole to spacing be S, in the range of 4Df~8Df。
Beneficial effect
A kind of chiasma type Y air film hole cooling structure for turbo blade proposed by the present invention, is the edge on air film orifice plate
Flow direction arrangement two rows Y air film hole, and air film hole is arranged using chiasma type；Y air film hole is by intersecting two cylindrical air film holes
Extend its interface after mutually passing through to form, the outlet of two cylindrical air film holes is extended to there is certain tilt angle.Chiasma type Y
Air film hole cooling structure make that jet stream is more easier point to both sides, increase the exhibition of jet stream to covering, and reduce the pneumatic of jet stream
Loss；By the interaction of front two rows Y air film hole, curls inward is formed to whirlpool, so that leaving Y air film hole in air film hole downstream
Cold air is tightly covered near wall, is formed with effect protection to air film hole downstream wall surface；Y air film hole has an air film hole entrance,
Section is divided into two strands of cold air in the channel, so that the gas output of Y air film hole two outlets is more uniform, Y air film hole has structure letter
It is single, it is easy to process, and the feature that film overcast effect is good.
Detailed description of the invention
With reference to the accompanying drawing with embodiment to a kind of chiasma type Y air film hole cooling structure for turbo blade of the present invention
It is described in further detail.
Fig. 1 is the chiasma type Y air film hole cooling structure schematic diagram that the present invention is used for turbo blade.
Fig. 2 is the chiasma type Y air film hole cooling structure top view that the present invention is used for turbo blade.
Fig. 3 is the chiasma type Y air film hole cooling structure front view that the present invention is used for turbo blade.
Fig. 4 is the chiasma type Y air film hole cooling structure position view that the present invention is used for turbo blade.
Fig. 5 is upstream Y type film hole structure schematic diagram of the invention.
Fig. 6 is downstream Y type film hole structure schematic diagram of the invention.
In figure
1. 2. upstream Y air film hole inducer of air film orifice plate, 3. upstream 4. first cylinder air film hole of Y air film hole, 5. downstream Y
6. downstream Y air film hole of air film hole inducer, 7. 8. inner cooling path of third cylinder air film hole, 9. pressure face chiasma type Y air film hole
10. 11. suction surface chiasma type Y air film hole of inner cooling path, 12. pressure face chiasma type Y air film hole, 13. second cylinder air film hole
14. the 4th cylinder air film hole
A. the cooling air film G. of the cooling air film E. cooling air-flow F. of the cooling air film D. of mainstream combustion gas B. cooling air-flow C. is cold
But under the air film H. combustion gas cold air blending upstream fluid Df. air film hole smallest cross-sectional equivalent diameter α Y air film hole angle of the crossing β
Trip the upstream Y air film hole angle of the crossing θ Y air film hole flow to the downstream tilt angle gamma Y air film hole flow to the inclination angle upstream P. Y air film hole with
Downstream Y air film hole flows to spacing
S. the exhibition of upstream Y air film hole and downstream Y air film hole is to pitch of holes
W. in upstream Y air film hole two cylindrical hole export center points distance
V. in downstream Y air film hole two cylindrical hole export center points distance；
Specific embodiment
The present embodiment is a kind of chiasma type Y air film hole cooling structure for turbo blade.
Refering to fig. 1~Fig. 6, the present embodiment are used for the chiasma type Y air film hole cooling structure of turbo blade, are by the first circle
Column air film hole 4 and the second cylinder air film hole 13 extend its interface formation upstream Y air film hole inducer 2 after intersecting intersection, on
It swims Y air film hole inducer 2, the first cylinder air film hole 4 and the second cylinder air film hole 13 and forms upstream Y air film hole 3.Third cylinder gas
Fenestra 7 and the 4th cylinder air film hole 14 intersect intersection and extend its interface formation downstream Y air film hole inducer 5, downstream Y air film hole
Inducer 5, third cylinder air film hole 7 and the 4th cylinder air film hole 14 form downstream Y air film hole 6.Upstream Y air film hole 3 and downstream Y
The fork arrangement of air film hole 6 sets to form chiasma type Y air film hole cooling structure；Wherein, the first cylinder air film hole 4 and the second cylinder air film hole
13 with the smallest cross-sectional equivalent diameter D of third cylinder air film hole 7 and the 4th cylinder air film hole 14fIt is identical, value range be 0.5~
1.5mm；The intersecting angle of first cylinder air film hole 4 and the second cylinder air film hole 13 is α in upstream Y air film hole 3, and value range is
45~95 °, the inclination angle theta value range that flows to of upstream Y air film hole 3 is 30~60 °；Third cylinder air film hole in downstream Y air film hole 6
7 and the 4th cylinder air film hole 14 intersecting angle be β, value range be 40~90 °, the tilt angle gamma that flows to of downstream Y air film hole 6 takes
Being worth range is 30~60 °.
In the present embodiment, the flow to spacing and the spacing that flows to of downstream Y air film hole 6 of upstream Y air film hole 3 are P, range
For 2Df~5Df；The exhibition of upstream Y air film hole 3 and downstream Y air film hole 6 to air film pitch of holes be S, in the range of 4Df~8Df；On
The span distance for swimming the cylindrical hole crossing center point of Y air film hole 3 and downstream Y air film hole 6 is 0.5S；First cylinder air film hole, 4 He
The distance of second cylinder air film hole, 13 export center point is W, in third cylinder air film hole 7 and 14 hole exits of the 4th cylinder air film hole
The distance of heart point is V, and wherein the value of W is more than or equal to the value of V.
Embodiment one
In the present embodiment, pressure face chiasma type Y air film hole 9 and pressure face chiasma type Y are arranged in the pressure face of turbo blade
Air film hole 12 is supplied by inner cooling path 8 and inner cooling path 10, arranges suction surface chiasma type Y air film hole in turbo blade suction surface
11, it is supplied by inner cooling path 10.Wherein, the first cylinder air film hole 4 and the second cylinder air film hole 13, which intersect, penetrates through and stretches its friendship
Junction forms upstream Y air film hole 3；Third cylinder air film hole 7 and the 4th cylinder air film hole 14, which intersect, to be penetrated through and stretches its interface
Downstream Y air film hole 6 is formed, upstream Y air film hole 3 combines to form chiasma type Y air film hole cooling structure with the fork row of downstream Y air film hole 6.
In the present embodiment, the first cylinder air film hole 4, the second cylinder air film hole 13, third cylinder air film hole 7 and the 4th cylinder
The smallest cross-sectional equivalent diameter Df of air film hole 14 is 0.6mm.First cylinder air film hole 4 and the second cylinder gas in upstream Y air film hole 3
The angle of the crossing α of fenestra 13 is 80 °, and the value that upstream Y air film hole 3 flows to inclination angle theta is 45 °.Third cylinder in downstream Y air film hole 6
The angle of the crossing of air film hole 7 and the 4th cylinder air film hole 14 is β, and value is 70 °, the value for flowing to tilt angle gamma of downstream Y air film hole 6
It is 45 °.The spacing P that flows to of upstream Y air film hole 3 and downstream Y air film hole 6 is 3Df.The exhibition of upstream Y air film hole 3 is to air film pitch of holes
Exhibition with downstream Y air film hole 6 to air film pitch of holes be S, value 6Df.The circle of upstream Y air film hole 3 and downstream Y air film hole 6
The span distance of post holes crossing center point is 0.5S.13 export center point of first cylinder air film hole 4 and the second cylinder air film hole
Distance is W, and the distance of 14 export center point of third cylinder air film hole 7 and the 4th cylinder air film hole is V, and wherein the value of W is greater than
Value equal to V.
In the present embodiment, the exhibition of upstream Y air film hole 3 and downstream Y air film hole 6 to air film pitch of holes be S, value 6Df,
Belong to moderate value in its value range, promotes upstream Y air film hole 3 and downstream Y air film hole 6 can at this point, opening up to spacing is smaller
In hole, downstream area forms the stronger curls inward of intensity to whirlpool, so that the cold air for leaving Y type air film hole is tightly covered near wall,
Effect protection is formed with to air film hole downstream wall surface.
Embodiment two
In the present embodiment, chiasma type Y air film hole 9 and chiasma type Y air film hole 12 are arranged in the pressure face of turbo blade, by interior
Cold passage 8 and inner cooling path 10 supply, and arrange chiasma type Y air film hole 11 in turbo blade suction surface, are supplied by inner cooling path 10.
Wherein, the first cylinder air film hole 4 and the second cylinder air film hole 13, which intersect, penetrates through and stretches its interface formation upstream Y air film hole 3；
Third cylinder air film hole 7 and the 4th cylinder air film hole 14, which intersect, penetrates through and stretches its interface formation downstream Y air film hole 6；Upstream Y
Air film hole 3 combines to form chiasma type Y air film hole cooling structure with the fork row of downstream Y air film hole 6.
In the present embodiment, the first cylinder air film hole 4, the second cylinder air film hole 13, third cylinder air film hole 7 and the 4th cylinder
The smallest cross-sectional equivalent diameter Df of air film hole 14 is 0.6mm.First cylinder air film hole 4 and the second cylinder gas in upstream Y air film hole 3
The angle of the crossing α of fenestra 13 is 100 °, and the value that upstream Y air film hole 3 flows to inclination angle theta is 45 °.Third cylinder in downstream Y air film hole 6
The angle of the crossing of air film hole 7 and the 4th cylinder air film hole 14 is β, and value is 90 °, the value for flowing to tilt angle gamma of downstream Y air film hole 6
It is 45 °.The spacing P that flows to of upstream Y air film hole 3 and downstream Y air film hole 6 is 3.5Df.The exhibition of upstream Y air film hole 3 is between air film hole
Away from the exhibition with downstream Y air film hole 6 to air film pitch of holes be S, value 7.5Df.Upstream Y air film hole 3 and downstream Y air film hole 6
Cylindrical hole crossing center point span distance be 0.5S.13 export center of first cylinder air film hole 4 and the second cylinder air film hole
The distance of point is W, and the distance of 14 export center point of third cylinder air film hole 7 and the 4th cylinder air film hole is V, and wherein the value of W is wanted
Value more than or equal to V.
In the present embodiment, the exhibition of upstream Y air film hole 3 and downstream Y air film hole 6 is larger to air film hole interval S, upstream Y air film
The value of the angle of the crossing β of the angle of the crossing α and downstream Y air film hole 6 in hole 3 is also larger.Due to opening up the increase to air film pitch of holes, reduce
The intersecting angle of the flow of cooling gas, upstream Y air film hole and downstream Y air film hole increases, so that air film hole downstream was formed
To vortices breakdown there is no weakening because the increase to air film pitch of holes is opened up, obtained curls inward is bigger to the shape in whirlpool for curls inward, has
Effect increases the exhibition of jet stream to coverage area.
Embodiment three
In the present embodiment, chiasma type Y air film hole 9 and chiasma type Y air film hole 12 are arranged in the pressure face of turbo blade, by interior
Cold passage 8 and inner cooling path 10 supply, and arrange chiasma type Y air film hole 11 in turbo blade suction surface, are supplied by inner cooling path 10,
Wherein, the first cylinder air film hole 4 and the second cylinder air film hole 13, which intersect, penetrates through and stretches its interface formation upstream Y air film hole 3；
Third cylinder air film hole 7 and the 4th cylinder air film hole 14, which intersect, penetrates through and stretches its interface formation downstream Y air film hole 6；Upstream Y
Air film hole 3 combines to form chiasma type Y air film hole cooling structure with the fork row of downstream Y air film hole 6.
In the present embodiment, the first cylinder air film hole 4, the second cylinder air film hole 13, third cylinder air film hole 7 and the 4th cylinder
The smallest cross-sectional equivalent diameter Df of air film hole 14 is 0.6mm.First cylinder air film hole 4 and the second cylinder gas in upstream Y air film hole 3
The angle of the crossing α of fenestra 13 is 80 °, and the value that upstream Y air film hole 3 flows to inclination angle theta is 30 °.Third cylinder in downstream Y air film hole 6
The angle of the crossing of air film hole 7 and the 4th cylinder air film hole 14 is β, and value is 70 °, the value for flowing to tilt angle gamma of downstream Y air film hole 6
It is 30 °.The spacing P that flows to of upstream Y air film hole 3 and downstream Y air film hole 6 is 4.5Df.The exhibition of upstream Y air film hole 3 is between air film hole
Away from the exhibition with downstream Y air film hole 6 to air film pitch of holes be S, value 6Df.Upstream Y air film hole 3 and downstream Y air film hole 6
The span distance of cylindrical hole crossing center point is 0.5S.13 export center point of first cylinder air film hole 4 and the second cylinder air film hole
Distance be W, the distance of 14 export center point of third cylinder air film hole 7 and the 4th cylinder air film hole is V, and wherein the value of W is big
In the value for being equal to V.
The present embodiment is compared with embodiment one, embodiment two, by reducing upstream Y air film hole and downstream Y air film hole
Inclination angle is flowed to, method phase velocity of the cooling air-flow after leaving air film hole is effectively reduced, increases the exhibition Xiang Sudu of cooling air-flow,
Avoiding being emitted directly toward mainstream after leaving air film hole due to the larger cooling gas of method phase velocity can not be formed effectively near wall
Film overcast, and due to exhibition to speed improve so that the cooling gas of adjacent upstream Y air film hole and downstream Y air film hole
Collision is more violent, and cooling gas is effectively covered above turbo blade wall surface, is formed with by the involute strength enhancing to whirlpool
The film overcast of effect.
Claims (3)
1. a kind of chiasma type Y air film hole cooling structure for turbo blade, including air film orifice plate, upstream Y air film hole, downstream Y
Air film hole, cylinder air film hole, pressure face chiasma type Y air film hole, suction surface chiasma type Y air film hole, inner cooling path, in turbo blade
Pressure face is equipped with pressure face chiasma type Y air film hole, and suction surface chiasma type Y air film hole, pressure are equipped on turbo blade suction surface
The both ends of power face chiasma type Y air film hole and suction surface chiasma type Y air film hole are respectively formed outlet and the entrance of air-flow, and with it is interior cold
But channel communicates, it is characterised in that: along flow direction arrangement two rows Y air film hole on air film orifice plate, and two rows of air film holes use and intersect
Type arrangement, Y air film hole are formed by extending its interface after mutually passing through two cylindrical air film hole intersections, two cylindrical gas
The outlet of fenestra is extended to there is certain tilt angle, and the distance of upstream two hole exits central points of Y air film hole is W, downstream Y
The distance of two hole exits central points of air film hole is V, and wherein the value of W is more than or equal to the value of V；Upstream Y air film hole and downstream Y air film
The spacing that flows in hole is P；The exhibition of upstream Y air film hole to the exhibition of spacing and downstream Y air film hole to spacing be S；Upstream Y air film hole
Span distance with the cylindrical hole crossing center point of downstream Y air film hole is 0.5S；The smallest cross-sectional equivalent diameter of cylinder air film hole
Df, value range is 0.5~1.5mm.
2. the chiasma type Y air film hole cooling structure according to claim 1 for turbo blade, it is characterised in that: described
Two cylinder air film hole intersecting angles of upstream Y air film hole are α, and value range is 45~95 °, and upstream Y air film hole flows to inclination angle theta
Value range be 30~60 °, two cylinder air film hole intersecting angles of downstream Y air film hole are β, and value range is 40~90 °,
The value range for flowing to tilt angle gamma of downstream Y air film hole is 30~60 °.
3. the chiasma type Y air film hole cooling structure according to claim 1 for turbo blade, it is characterised in that: described
The spacing that flows to of upstream Y air film hole and downstream Y air film hole is P, in the range of 2Df~5Df, upstream Y air film hole and downstream Y air film
The exhibition in hole to spacing be S, in the range of 4Df~8Df。
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910007232.2A CN109736897A (en) | 2019-01-04 | 2019-01-04 | A kind of chiasma type Y air film hole cooling structure for turbo blade |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910007232.2A CN109736897A (en) | 2019-01-04 | 2019-01-04 | A kind of chiasma type Y air film hole cooling structure for turbo blade |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113719323A (en) * | 2021-07-09 | 2021-11-30 | 北京航空航天大学 | Composite cooling structure for turbine blade of gas turbine |
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| US5326224A (en) * | 1991-03-01 | 1994-07-05 | General Electric Company | Cooling hole arrangements in jet engine components exposed to hot gas flow |
| GB2310896A (en) * | 1996-03-05 | 1997-09-10 | Rolls Royce Plc | Air cooled wall |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN113719323A (en) * | 2021-07-09 | 2021-11-30 | 北京航空航天大学 | Composite cooling structure for turbine blade of gas turbine |
| CN113719323B (en) * | 2021-07-09 | 2022-05-17 | 北京航空航天大学 | Composite cooling structure for turbine blade of gas turbine |
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Application publication date: 20190510 |
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