CN106168143B - A kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket - Google Patents
A kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket Download PDFInfo
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- CN106168143B CN106168143B CN201610546265.0A CN201610546265A CN106168143B CN 106168143 B CN106168143 B CN 106168143B CN 201610546265 A CN201610546265 A CN 201610546265A CN 106168143 B CN106168143 B CN 106168143B
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- cooling
- trailing edge
- blade
- socket
- ball
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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
- 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
-
- 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
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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 kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket, there is the turbine blade blade interior cooling chamber and cooling fluid to flow into pipe, and blade interior cooling chamber hot surface is staggeredly equipped with some blade interior cooling chamber dividing plates, U-shaped cooling duct inside turbine blade is constituted with blade interior cooling chamber hot surface；Blade trailing edge internal cooling socket arrangement nearby has been evenly arranged on blade interior cooling chamber hot surface near blade trailing edge, some lateral pumping grooves are arranged in trailing edge cooling duct side nearby, split in blade trailing edge and be evenly arranged blade trailing edge cooling socket arrangement at seam at leaf back, some lateral pumping grooves are used to internal cooling channel with outside cooling duct being connected, and form internal cooling and the cooling structure of outside cooling integrated formula.The present invention solves the problems, such as to arrange heat transfer structure difficulty in narrower blade trailing edge internal cooling channel, improves heat transfer structure and bring heat transmission resistance to increase the problem of excessive.
Description
Technical field：
It is more particularly to a kind of that there is lateral pumping groove and ball-and-socket the present invention relates to a kind of turbine blade internal cooling structure
Turbine blade trailing edge cooling structure.
Background technology：
Gas turbine/aero-engine as industrial quarters " jewel on imperial crown ", its turbine blade part operationally by
To great thermic load, in order to ensure its safe operation, it is necessary to design and build substantial amounts of cooling structure to ensure turbine blade
Temperature be located in rational scope, obvious drag losses at the same time can't be brought, in order to avoid be unfavorable for the cooling of blade
Efficiency.Therefore, developing efficient lower resistance augmentation of heat transfer structure just becomes the research work of urgent need to resolve.In turbine blade
Cooling structure is often divided into two classes of internal cooling and outside cooling, and wherein internal cooling mainly includes impinging cooling, turbulent flow reinforced biography
Heat etc., arrangement internal cooling channel is the most common type of cooling in turbine blade, passes through cooling gas in internal cooling channel
The effect that cooling blade wall is played from the heat flow of blade exterior conduction is taken away in heat transfer with wall, logical in blade interior cooling
U-shaped, serpentine cooling channel and turbulent flow reinforced heat transfer structure in road are the most typically to strengthen heat compensator conducting property；And outside cooling master
To completely cut off high-temperature fuel gas by forming air film in blade surface to play a part of protecting blade, turbine including gaseous film control etc.
The leading edge of blade, middle string region, trailing edge are split at seam all frequently with mode of the gaseous film control as protection blade surface.In actual height
In warm turbine blade, the various types of cooling are usually coupled, to reach optimal cooling effect.The trailing edge region of high-temperature turbine blade
Key position when being blade cooling structure design, under the contact of high-temperature gas, relatively thin blade trailing edge region generally requires
A variety of type of cooling collective effects are to ensure its security.In the trailing edge design of high-temperature turbine blade, often in trailing edge pressure
" splitting seam " structure is arranged in surface side, and connects the trailing edge groove of internal cooling channel pumping nearby.
Research shows although turbine trailing edge employs different methods for cooling, but still suffer from flowing flow resistance it is big, along Cheng Wensheng
Height, the problem of turbine trailing edge portion temperature is still of a relatively high；According to the shape of vane type line, the inside of blade trailing edge part is cold
But passage is often narrower (compared with aspect ratio AR), and in the region, arrangement fin has certain difficulty, and in this slype
Arrangement fin often brings more obvious drag losses, unfavorable to blade cooling efficiency.Based on the reason, in turbine blade tail
Edge region is frequently with structures such as pin fin, vortex structure generators as cooling structure；Though some cooling structures in turbine trailing edge
Relatively good cooling effect can so be reached, but it is complicated.Therefore, it is simple efficient low that turbine blade trailing edge structures are developed
Resistance augmentation of heat transfer structure, it is further to reduce one of main direction of studying of blade working temperature at present.
The content of the invention：
The purpose of the present invention is to be directed to above-mentioned the deficiencies in the prior art, there is provided one kind is applied to turbine blade tail and cooled down
The turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket.This turbine leaf with lateral pumping groove and ball-and-socket
Piece trailing edge cooling structure does not produce projection in flow field, and it is relatively low to be arranged in drag losses in relatively thin trailing edge cooling duct, and
Preferable heat-transfer effect can be played.
To reach above-mentioned purpose, the present invention adopts the following technical scheme that to realize：
A kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket, the turbine blade have blade interior
Cooling chamber and it is arranged on the cooling fluid being connected on turbine blade end face with blade interior cooling chamber and flows into pipe, and in blade
Blade interior cooling chamber hot surface in portion's cooling chamber is staggeredly equipped with some blade interior cooling chamber dividing plates, blade interior cooling
Chamber hot surface constitutes U-shaped cooling duct inside turbine blade with some blade interior cooling chamber dividing plates；
Blade trailing edge internal cooling ball nearby has been evenly arranged on blade interior cooling chamber hot surface near blade trailing edge
Nest structure, some lateral pumping grooves are arranged in trailing edge, and nearby cooling duct side, the blade trailing edge near leaf basin lip split seam
Blade trailing edge cooling socket arrangement is evenly arranged at place's leaf back, some lateral pumping grooves are attached for that will be disposed with blade trailing edge
The internal cooling channel of nearly internal cooling socket arrangement and the outside cooling duct phase for being disposed with blade trailing edge cooling socket arrangement
Connection, form this turbine blade trailing edge internal cooling with lateral pumping groove and ball-and-socket and the cooling of outside cooling integrated formula
Structure.
Of the invention further improve be, blade trailing edge nearby for wrong arrangement put or in-line arrangement by internal cooling socket arrangement
Arrangement.
Further improve of the invention is that internal cooling socket arrangement arrangement flows to spacing P near blade trailing edges/D
Between 0.5 to 2, open up to spacing Pd/ D is between 0.5 to 2, between relative depth δ/D of ball-and-socket is 0.05 to 0.5.
Further improve of the invention is that the lateral groove that is evacuated is rectangular channel or trapezoidal channel.
Of the invention further improve be, the lateral length for being evacuated groove in 8mm between 16mm, highly in 1.5mm extremely
Between 3.5mm, spacing is flowed in 15mm between 30mm.
Further improve of the invention is that cooling blast splits seam height t/H between 0.5 to 1.5, splits seam inclined angle alpha
Between 5 ° to 15 °.
Further improve of the invention is that cooling gas sprays from the jet flow groove split near seam, and air film is blown to exist than M
Between 0.2 to 1.5.
Further improve of the invention is that blade trailing edge cooling socket arrangement is put for wrong arrangement or in-line arrangement arrangement, cloth
The spacing that flows to put is 10~20mm, and it is 7~17mm to open up to spacing, and flow direction includes 5~9 vollyball nests, opened up to including 2~4 vollyballs
Nest, between relative depth δ/D of ball-and-socket is 0.05 to 0.5.
Compared with prior art, the present invention has the advantages that：
1st, the present invention is reasonable in design, simple in construction, solves and biography is arranged in narrower blade trailing edge internal cooling channel
The problem of heat structure difficulty；
2nd, this turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket does not produce projection, cloth in flow field
It is relatively low to put the drag losses in relatively thin trailing edge cooling duct, and can also play preferable heat-transfer effect；
3rd, in the case where arranging this turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket, flow field is mutually dry
Relate to, fluid flows through socket arrangement and the flow separation of complexity, attached, phenomena such as even turning to twist in advance again occurs, by logical in cooling
Arrange that socket arrangement can generally produce significant augmentation of heat transfer effect in road, and wrong arrangement puts lower ball-and-socket and covers internal hot surface
More regions, therefore there is higher heat transfer coefficient in the central area of passage；
4th, inside the ball-and-socket that wrong arrangement is put in blade trailing edge cooling duct, separation whirlpool merges with the vortex in main channel,
Cooling blast absorption forms the preferable air film layer of quality on the surface of ball-and-socket, is just gradually beaten until leaving last ball-and-socket
Break and mixed with high temperature main flow rapidly so that gas film cooling efficiency obtains a certain degree of lifting, enhances trailing edge blade back surface side
Cooling effect at solid；
5th, internal cooling channel and the blade back outer surface contacted with high temperature main flow are arranged simply near blade trailing edge
Ball-and-socket heat transfer structure, and inside and outside cooling duct are connected using lateral pumping groove, not only with good heat-transfer character, and
With preferable processing integraty, more exploitativeness.
Brief description of the drawings：
Fig. 1 is that nearby section view is combined in internal cooling channel and outside cooling duct to turbine blade of embodiment of the present invention trailing edge
Figure；
Fig. 2 is that the local ball-and-socket of internal cooling channel near blade trailing edge arranges schematic diagram；
Fig. 3 is that nearby local pumping groove arranges schematic diagram to blade trailing edge；
Fig. 4 is that the local ball-and-socket of cooling duct outside blade trailing edge arranges schematic diagram；
Wherein：1st, cooling fluid flows into pipe, and 2, blade interior cooling chamber, 3, blade interior cooling chamber hot surface, 4, blade
Internal cooling cavity dividing plate, 5, the neighbouring internal cooling socket arrangement of blade trailing edge, 6, be laterally evacuated groove, 7, blade trailing edge split leaf at seam
The back side, 8, leaf basin lip, 9, blade trailing edge cooling socket arrangement.
Embodiment：
Embodiments of the invention are elaborated below in conjunction with the accompanying drawings, the present embodiment is using technical solution of the present invention before
Carry, give detailed embodiment and specific operating process, but protection scope of the present invention is not limited to following embodiments.
As shown in Figures 1 to 4, the turbine blade trailing edge cooling knot with lateral pumping groove and ball-and-socket provided by the invention
Structure, including cooling fluid flow into pipe 1, blade interior cooling chamber 2, blade interior cooling chamber hot surface 3, blade interior cooling chamber every
Nearby internal cooling socket arrangement 5, lateral pumping groove 6, blade trailing edge split leaf back 7 at seam, leaf basin lip 8 for plate 4, blade trailing edge
Socket arrangement 9 is cooled down with blade trailing edge, wherein, cooling fluid flows into pipe 1 and connects blade interior cooling chamber 2, blade interior cooling
Chamber hot surface 3 and multiple blade interior cooling chamber dividing plates 4 constitute the U-shaped cooling duct of blade interior, the leaf near blade trailing edge
Blade trailing edge internal cooling socket arrangement 5 nearby is evenly arranged on piece internal cooling cavity hot surface 3, the lateral groove 6 that is evacuated is arranged
The cooling duct side near trailing edge, the blade trailing edge near leaf basin lip 8 are split and have been evenly arranged blade at leaf back 7 at seam
Trailing edge cools down socket arrangement 9, and blade trailing edge nearby put for wrong arrangement (specifically or in-line arrangement cloth by internal cooling socket arrangement 5
Put), arrangement flows to spacing Ps/ D is opened up to spacing P between 0.5 to 2d/ D is between 0.5 to 2, relative depth δ/D of ball-and-socket
Between (ball-and-socket depth/ball-and-socket diameter) is 0.05 to 0.5, the lateral groove 6 that is evacuated is evenly arranged in trailing edge cooling duct side, as
Trailing edge splits the cooling blast entrance of air film at seam, and its length, between 16mm, highly flows in 8mm in 1.5mm between 3.5mm
To spacing in 15mm between 30mm, cooling blast splits seam height t/H between 0.5 to 1.5, splits seam inclined angle alpha at 5 ° to 15 °
Between, cooling gas is sprayed from the lateral pumping groove 6 split near seam, and air film is blown than M between 0.2 to 1.5, determines cooling
The corresponding inlet velocity value of gas, blade trailing edge cooling socket arrangement 9 put (specifically or in-line arrangement arrangement), cloth for wrong arrangement
The spacing that flows to put is 10~20mm, and it is 7~17mm to open up to spacing, and flow direction includes 5~9 vollyball nests, opened up to including 2~4 vollyballs
Nest, between relative depth δ/D (ball-and-socket depth/ball-and-socket diameter) of ball-and-socket is 0.05 to 0.5.
In the present invention, cooling air-flow flows into pipe 1 into blade interior cooling chamber 2 from cooling fluid, by blade interior
Cooling chamber hot surface 3 is with behind the U-shaped cooling duct of blade interior of multiple blade interior cooling chamber dividing plates 4 composition, flowing into blade tail
The internal cooling channel of internal cooling socket arrangement 5 near edge, split the lateral trailing edge for being evacuated groove 6 of seam inflow arrangement through trailing edge and cool down
Passage, cooling air constantly flow out along flow direction out of each lateral pumping groove 6.Split the leaf basin of crack structure connection trailing edge
With leaf back, split the seam blade interior cooling chamber 2 adjacent with trailing edge region and communicate, cooling gas is along blowout at seam is split, with leaf basin
The high temperature main flow mixing that lip 8 impacts, split the side surface of leaf back 7 at seam in corresponding blade trailing edge and form air film, simultaneously
Heat of the part from suction surface side is taken away in a manner of convection heat transfer' heat-transfer by convection, collective effect carries out cold to blade trailing edge regional area
But, the phenomenon that an outside cooling be combined with each other with internal cooling is formed.Cooling gas flows through what is contacted with high temperature main flow
The blade trailing edge of arrangement blade trailing edge cooling socket arrangement 9 splits leaf back 7 at seam, and the small separation whirlpool that ball-and-socket chamber is internally formed will be cold
But jet is adsorbed on the surface of ball-and-socket, and the preferable air film layer of one layer of quality is formd on the surface of ball-and-socket, is isolated with high temperature main flow,
Fluid temperature (F.T.) close to the trailing edge ball-and-socket near surface of outlet is still relatively low, until leaving last socket arrangement, air film layer
Just gradually broken and mixed with high temperature main flow rapidly, therefore can predict that the arrangement of blade trailing edge cooling socket arrangement 9 can be more
Good " protection " air film layer trailing edge surface covering, and with the isolation of high temperature main flow, so as to obtain higher gas film cooling efficiency,
Enhance blade trailing edge and split cooling effect at seam at the side solid of leaf back 7.In addition, the cooling air film of socket region occurs
Flow separation is attached again, will also change the convective heat-transfer coefficient on trailing edge surface.At the same time, to put Fluid field mutual in mistake arrangement for ball-and-socket
Interference, and wrong arrangement puts lower ball-and-socket and covers the more regions of internal cooling cavity hot surface and trailing edge surface, therefore in passage
Central area has higher heat transfer coefficient.
The processing technology of the present invention is simple, can be by the way of model casting by leaf as traditional cooling structure
Nearby internal cooling socket arrangement 5, blade trailing edge cool down socket arrangement 9 and blade interior cooling chamber dividing plate 4 and leaf to piece trailing edge
Piece is together cast out；But compared with traditional structure for being applied to trailing edge cooling, the present invention is this to have lateral pumping groove 6, leaf
Piece trailing edge nearby the turbine blade trailing edge internal cooling of internal cooling socket arrangement 5 and blade trailing edge cooling socket arrangement 9 with it is outer
The cooling structure of portion's cooling integrated formula, does not produce projection in flow field, and drag losses is relatively low, and can also play preferably heat transfer effect
Fruit, solve the problems, such as to arrange heat transfer structure difficulty in narrower blade trailing edge internal cooling channel；It is logical in blade trailing edge cooling
Inside the blade trailing edge cooling socket arrangement 9 that wrong arrangement is put in road, separation whirlpool merges with the vortex in main channel, and cooling blast is inhaled
The surface for being attached to ball-and-socket forms the preferable air film layer of quality, until leave last ball-and-socket just by gradually broken and rapidly with
High temperature main flow mixes so that gas film cooling efficiency obtains a certain degree of lifting, enhances cold at the solid of trailing edge blade back surface side 7
But effect；It is this with internal cooling socket arrangement 5, blade trailing edge cooling near lateral pumping groove 6 and blade trailing edge arranging
Under the turbine blade trailing edge cooling structure of socket arrangement 9, flow field interferes, and fluid flows through the stream that complexity occurs in socket arrangement
Dynamic separation, again attached, phenomena such as even turning to twist in advance, can produce significant augmentation of heat transfer effect, and wrong arrange is put lower ball-and-socket and covered
Blade interior cooling chamber hot surface 3 and blade trailing edge split 7 more regions of leaf back at seam, therefore in the central area of passage
With higher heat transfer coefficient.The cooling structure has important for the cooling effect in further lifting turbine blade trailing edge region
Meaning.
Claims (8)
1. a kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket, it is characterised in that the turbine blade has
There is blade interior cooling chamber (2) and be arranged on the cooling stream being connected on turbine blade end face with blade interior cooling chamber (2)
Body flows into pipe (1), and the blade interior cooling chamber hot surface (3) in blade interior cooling chamber (2) is staggeredly equipped with some blades
Internal cooling cavity dividing plate (4), blade interior cooling chamber hot surface (3) constitute with some blade interior cooling chamber dividing plates (4)
U-shaped cooling duct inside flat blade；
Blade trailing edge internal cooling ball-and-socket nearby has been evenly arranged on blade interior cooling chamber hot surface (3) near blade trailing edge
Structure (5), some lateral pumping grooves (6) are arranged in trailing edge cooling duct side nearby, in the blade tail of leaf basin lip (8) nearby
Edge splits leaf back at seam (7) place and has been evenly arranged blade trailing edge cooling socket arrangement (9), and some lateral pumping grooves (6) are used for will
Being disposed with blade trailing edge, nearby the internal cooling channel of internal cooling socket arrangement (5) cools down ball-and-socket knot with being disposed with blade trailing edge
The outside cooling duct of structure (9) is connected.
2. a kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket according to claim 1, it is special
Sign is that nearby for wrong arrangement put or in-line arrangement is arranged by internal cooling socket arrangement (5) for blade trailing edge.
3. a kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket according to claim 2, it is special
Sign is that internal cooling socket arrangement (5) arrangement flows to spacing P near blade trailing edges/ D is opened up to spacing between 0.5 to 2
Pd/ D is between 0.5 to 2, and between relative depth δ/D of ball-and-socket is 0.05 to 0.5, wherein D is ball-and-socket diameter.
4. a kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket according to claim 1, it is special
Sign is that it is rectangular channel or trapezoidal channel to be laterally evacuated groove (6).
5. a kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket according to claim 4, it is special
Sign is, is laterally evacuated the length of groove (6) in 8mm between 16mm, highly exists in 1.5mm between 3.5mm, flowing to spacing
15mm is between 30mm.
6. a kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket according to claim 1, it is special
Sign is that cooling blast splits seam height t/H between 0.5 to 1.5, splits seam inclined angle alpha between 5 ° to 15 °, wherein H is leaf basin
Lip thickness.
7. a kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket according to claim 1, it is special
Sign is that cooling gas sprays from the jet flow groove split near seam, and air film is blown than M between 0.2 to 1.5.
8. a kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket according to claim 1, it is special
Sign is, blade trailing edge cooling socket arrangement (9) is put for wrong arrangement or in-line arrangement arrangement, arrangement flow to spacing for 10~
20mm, it is 7~17mm to open up to spacing, flow direction comprising 5~9 vollyball nests, open up to including 2~4 vollyball nests, the relative depth δ of ball-and-socket/
Between D is 0.05 to 0.5, wherein D is ball-and-socket diameter.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610546265.0A CN106168143B (en) | 2016-07-12 | 2016-07-12 | A kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610546265.0A CN106168143B (en) | 2016-07-12 | 2016-07-12 | A kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket |
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| CN106168143A CN106168143A (en) | 2016-11-30 |
| CN106168143B true CN106168143B (en) | 2017-12-15 |
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| CN107060893A (en) * | 2017-06-01 | 2017-08-18 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure |
| CN107269319A (en) * | 2017-06-01 | 2017-10-20 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with sphere pit partly splits seam cooling structure |
| CN107013255A (en) * | 2017-06-01 | 2017-08-04 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with continuous straight rib partly splits seam cooling structure |
| CN107035421A (en) * | 2017-06-01 | 2017-08-11 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with array pin rib partly splits seam cooling structure |
| CN107013254A (en) * | 2017-06-01 | 2017-08-04 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with sphere projection partly splits seam cooling structure |
| FR3102794B1 (en) * | 2019-10-31 | 2022-09-09 | Safran Aircraft Engines | TURBOMACHINE COMPONENT FEATURING ENHANCED COOLING HOLES |
| CN112177685A (en) * | 2020-10-21 | 2021-01-05 | 中国航发沈阳发动机研究所 | Tail seam cooling structure of high-pressure turbine rotor blade |
| CN112523810B (en) * | 2020-12-14 | 2021-08-20 | 北京航空航天大学 | Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam |
| CN113356931B (en) * | 2021-06-30 | 2022-12-09 | 西安交通大学 | Modeling micro-pit structure for enhancing cooling performance of blade trailing edge slotting wall surface |
| CN113586165B (en) * | 2021-07-20 | 2022-09-16 | 西安交通大学 | Turbine blade with single kerosene cooling channel |
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| CN1995708A (en) * | 2005-12-05 | 2007-07-11 | 通用电气公司 | Blade with parallel serpentine cooling channels |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US7553131B2 (en) * | 2006-07-21 | 2009-06-30 | United Technologies Corporation | Integrated platform, tip, and main body microcircuits for turbine blades |
| US7766615B2 (en) * | 2007-02-21 | 2010-08-03 | United Technlogies Corporation | Local indented trailing edge heat transfer devices |
| US8096770B2 (en) * | 2008-09-25 | 2012-01-17 | Siemens Energy, Inc. | Trailing edge cooling for turbine blade airfoil |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1995708A (en) * | 2005-12-05 | 2007-07-11 | 通用电气公司 | Blade with parallel serpentine cooling channels |
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