CN106168143A - A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket - Google Patents
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket Download PDFInfo
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- CN106168143A CN106168143A CN201610546265.0A CN201610546265A CN106168143A CN 106168143 A CN106168143 A CN 106168143A CN 201610546265 A CN201610546265 A CN 201610546265A CN 106168143 A CN106168143 A CN 106168143A
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- cooling
- trailing edge
- socket
- blade
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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 laterally bleed groove and ball-and-socket, this turbine blade has blade interior cooling chamber and cooling fluid flows to pipe, and blade interior cooling chamber hot surface is staggeredly equipped with some blade interior cooling chamber dividing plates, constitute the internal U-shaped cooling duct of turbine blade with blade interior cooling chamber hot surface；It has been evenly arranged internal cooling socket arrangement near blade trailing edge on blade interior cooling chamber hot surface near blade trailing edge, some grooves of laterally bleeding are arranged in side, cooling duct near trailing edge, split at blade trailing edge and at seam, at leaf back, be evenly arranged blade trailing edge cooling socket arrangement, some grooves of laterally bleeding, for being connected with outside cooling duct by internal cooling channel, form the cooling structure of internal cooling and outside cooling integrated formula.The present invention solves the problem that heat transfer structure is difficult of arranging in narrower blade trailing edge internal cooling channel, improves heat transfer structure and brings heat transmission resistance to increase excessive problem.
Description
Technical field:
The present invention relates to a kind of turbine blade internal cooling structure, particularly to a kind of, there is laterally bleed groove and ball-and-socket
Turbine blade trailing edge cooling structure.
Background technology:
Gas turbine/aero-engine is operationally subject to as industrial quarters " jewel on Phaleria macrocarpa ", its turbine blade parts
To great thermic load, in order to ensure its safe operation, need design and build substantial amounts of cooling structure to ensure turbine blade
Temperature be positioned in the range of reasonably, meanwhile can't bring obvious drag losses, in order to avoid being unfavorable for the cooling of blade
Efficiency.Therefore, develop efficient lower resistance augmentation of heat transfer structure and just become the research work needing solution badly.In turbine blade
Cooling structure is often divided into internal cooling and outside cooling two classes, and wherein internal cooling mainly includes impinging cooling, turbulent flow reinforced biography
Heat etc., arrange that internal cooling channel is the modal type of cooling in turbine blade, by cooling down gas in internal cooling channel
Heat transfer with wall is taken away the heat flow from blade exterior conduction and is played the effect of cooling blade 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 is main
Gaseous film control to be included etc., by forming air film isolation high-temperature fuel gas to play the effect of protection blade, turbine at blade surface
The leading edge of blade, middle string region, trailing edge split at seam all frequently with gaseous film control as the mode of protection blade surface.Actual high
In temperature turbine blade, usually couple the various type of cooling, to reach optimal cooling effect.The trailing edge region of high-temperature turbine blade
Being key position during blade cooling structure design, under the contact of high-temperature gas, relatively thin blade trailing edge region generally requires
The multiple type of cooling acts on ensureing its safety jointly.In the trailing edge of high-temperature turbine blade designs, often at trailing edge pressure
Side, face arranges that near " splitting seam " structure, and connection trailing edge, internal cooling channel is bled groove.
Research shows, although turbine trailing edge have employed different methods for cooling, but it is big, along Cheng Wensheng to still suffer from flowing flow resistance
Height, the problem that turbine trailing edge portion temperature is the most of a relatively high；According to the shape of vane type line, the inside of blade trailing edge part is cold
But passage the narrowest (relatively aspect ratio AR), arranges that in this region fin there be difficulties involved when, and in this slype
Arrange that fin often brings more significantly drag losses, unfavorable to blade cooling efficiency.Based on this reason, at turbine blade tail
Edge region frequently with structures such as pin fin, vortex structure generators as cooling structure；Though some cooling structure in turbine trailing edge
So can reach reasonable cooling effect, but structure is complicated.Therefore, exploitation turbine blade trailing edge structures is the lowest
Resistance augmentation of heat transfer structure, is one of further main direction of studying reducing blade working temperature.
Summary of the invention:
It is an object of the invention to for above-mentioned the deficiencies in the prior art, it is provided that one is applicable to turbine blade tail cooling
The turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket.This turbine leaf with laterally bleed groove and ball-and-socket
Sheet trailing edge cooling structure does not produce projection in flow field, is arranged in drag losses in relatively thin trailing edge cooling duct relatively low, and also
Preferable heat-transfer effect can be played.
For reaching above-mentioned purpose, the present invention adopts the following technical scheme that and realizes:
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket, this turbine blade has blade interior
Cooling chamber and be arranged on turbine blade end face the cooling fluid being connected with blade interior cooling chamber and flow to 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, and blade interior cools down
Chamber hot surface and some blade interior cooling chamber dividing plates constitute the internal U-shaped cooling duct of turbine blade；
It has been evenly arranged internal cooling ball near blade trailing edge on blade interior cooling chamber hot surface near blade trailing edge
Nest structure, some grooves of laterally bleeding are arranged in side, cooling duct near trailing edge, and the blade trailing edge near leaf basin lip splits seam
Being evenly arranged blade trailing edge cooling socket arrangement at place's leaf back, some grooves of laterally bleeding will be for being disposed with blade trailing edge
Near internal cooling socket arrangement internal cooling channel and be disposed with blade trailing edge cooling socket arrangement outside cooling duct
It is connected, forms the cold of this turbine blade trailing edge internal cooling with laterally bleed groove and ball-and-socket and outside cooling integrated formula
But structure.
The present invention is further improved by, and near blade trailing edge, internal cooling socket arrangement is that staggered arrangement is arranged or in-line arrangement
Arrange.
The present invention is further improved by, and what near blade trailing edge, internal cooling socket arrangement was arranged flows to spacing Ps/D
Between 0.5 to 2, exhibition is to spacing Pd/ D is between 0.5 to 2, and relative depth δ of ball-and-socket/D is between 0.05 to 0.5.
The present invention is further improved by, and groove of laterally bleeding is rectangular channel or trapezoidal channel.
The present invention is further improved by, and the length of groove of laterally bleeding is between 8mm to 16mm, and height is at 1.5mm extremely
Between 3.5mm, flow to spacing between 15mm to 30mm.
The present invention is further improved by, cooling blast split seam height t/H between 0.5 to 1.5, split seam inclined angle alpha
Between 5 ° to 15 °.
The present invention is further improved by, and cooling gas is blown exist than M from the jet flow groove ejection split near seam, air film
Between 0.2 to 1.5.
The present invention is further improved by, and blade trailing edge cooling socket arrangement is that staggered arrangement is arranged or in-line arrangement is arranged, cloth
The spacing that flows to put is 10～20mm, and opening up to spacing is 7～17mm, flows to comprise 5～9 vollyball nests, exhibition to including 2～4 vollyballs
Nest, relative depth δ of ball-and-socket/D is between 0.05 to 0.5.
Compared with prior art, there is advantages that
1, the present invention is reasonable in design, simple in construction, solves and arranges biography in narrower blade trailing edge internal cooling channel
The problem that heat structure is difficult；
2, this turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket does not produce projection, cloth in flow field
Put drag losses in relatively thin trailing edge cooling duct relatively low, and also can play preferable heat-transfer effect；
3, under arranging this turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket, flow field is the most dry
Relate to, fluid flow through socket arrangement there will be complexity flow separation, the most attached, turn phenomenons such as twisting the most in advance, by logical in cooling
Road being arranged, socket arrangement generally can produce significant augmentation of heat transfer effect, and staggered arrangement arranges that lower ball-and-socket covers internal hot surface
More region, therefore the central area at passage has higher heat transfer coefficient；
4, inside the ball-and-socket that staggered arrangement is arranged in blade trailing edge cooling duct, separate whirlpool and merge with the vortex in main channel,
Cooling blast absorption defines quality preferable air film layer on the surface of ball-and-socket, is just gradually beaten until leaving last ball-and-socket
Break and mix with high temperature main flow rapidly so that gas film cooling efficiency obtains a certain degree of lifting, enhances trailing edge leaf back side
Cooling effect at solid；
5, near blade trailing edge, internal cooling channel and the blade back outer surface that contacts with high temperature main flow are all arranged simply
Ball-and-socket heat transfer structure, and utilize the internal and outside cooling duct of groove connection of laterally bleeding, not only there is good heat-transfer character, and
Have and preferably process integraty, more exploitativeness.
Accompanying drawing illustrates:
Fig. 1 is internal cooling channel and outside cooling duct combination section view near embodiment of the present invention turbine blade 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 groove layout schematic diagram of locally bleeding near blade trailing edge；
Fig. 4 is that the local ball-and-socket of the outside cooling duct of blade trailing edge arranges schematic diagram；
Wherein: 1, cooling fluid flows to pipe, 2, blade interior cooling chamber, 3, blade interior cooling chamber hot surface, 4, blade
Internal cooling cavity dividing plate, 5, internal cooling socket arrangement near blade trailing edge, 6, laterally bleed groove, 7, blade trailing edge split leaf at seam
The back side, 8, leaf basin lip, 9, blade trailing edge cooling socket arrangement.
Detailed description of the invention:
Elaborating embodiments of the invention below in conjunction with the accompanying drawings, the present embodiment is front with technical solution of the present invention
Carry, give detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
As shown in Figures 1 to 4, what the present invention provided has the turbine blade trailing edge cooling knot of laterally bleed groove and ball-and-socket
Structure, including cooling fluid flow to pipe 1, blade interior cooling chamber 2, blade interior cooling chamber hot surface 3, blade interior cooling chamber every
Internal cooling socket arrangement 5 near plate 4, blade trailing edge, laterally bleed groove 6, blade trailing edge split leaf back 7 at seam, leaf basin lip 8
Cooling down socket arrangement 9 with blade trailing edge, wherein, cooling fluid flows to pipe 1 and connects blade interior cooling chamber 2, and blade interior cools down
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
Being evenly arranged internal cooling socket arrangement 5 near blade trailing edge on sheet internal cooling cavity hot surface 3, groove 6 of laterally bleeding is arranged
Side, cooling duct near trailing edge, the blade trailing edge near leaf basin lip 8 is split and has been evenly arranged blade at leaf back 7 at seam
Trailing edge cooling socket arrangement 9, near blade trailing edge, internal cooling socket arrangement 5 is arranged for staggered arrangement and (is specifically alternatively in-line arrangement cloth
Put), layout flow to spacing Ps/ D is between 0.5 to 2, and exhibition is to spacing Pd/ D between 0.5 to 2, relative depth δ of ball-and-socket/D
(the ball-and-socket degree of depth/ball-and-socket diameter) is between 0.05 to 0.5, and groove 6 of laterally bleeding is evenly arranged in side, trailing edge cooling duct, as
Trailing edge splits the cooling blast entrance of air film at seam, and its length is between 8mm to 16mm, and height, between 1.5mm to 3.5mm, flows
To spacing between 15mm to 30mm, cooling blast split seam height t/H between 0.5 to 1.5, split seam inclined angle alpha at 5 ° to 15 °
Between, cooling gas sprays from the groove 6 of laterally bleeding split near seam, and air film is blown than M between 0.2 to 1.5, determines cooling
Gas corresponding inlet velocity value, blade trailing edge cooling socket arrangement 9 arranges (being specifically alternatively in-line arrangement to arrange), cloth for staggered arrangement
The spacing that flows to put is 10～20mm, and opening up to spacing is 7～17mm, flows to comprise 5～9 vollyball nests, exhibition to including 2～4 vollyballs
Nest, relative depth δ of ball-and-socket/D (the ball-and-socket degree of depth/ball-and-socket diameter) is between 0.05 to 0.5.
In the present invention, cooling air-flow flows to pipe 1 from cooling fluid and enters blade interior cooling chamber 2, through blade interior
Behind the U-shaped cooling duct of blade interior that cooling chamber hot surface 3 and multiple blade interior cooling chamber dividing plates 4 form, flow into blade tail
The internal cooling channel of internal cooling socket arrangement 5 near edge, splits seam inflow through trailing edge and arranges the trailing edge cooling of groove 6 of laterally bleeding
Passage, cooling air constantly flows out along flow direction in each laterally bleeds groove 6 road.Split crack structure and connect the leaf basin of trailing edge
With leaf back, splitting the seam blade interior cooling chamber 2 adjacent with trailing edge region and communicate, cooling gas is along splitting blowout at seam, with leaf basin
The high temperature main flow mixing that lip 8 impacts, splits leaf back 7 side surface at seam at corresponding blade trailing edge and forms air film, simultaneously
Taking away the part heat from suction surface side in the way of convection heat transfer' heat-transfer by convection, blade trailing edge regional area is carried out cold by common effect
But, the phenomenon that an outside cooling be combined with each other is formed with internal cooling.Cooling gas flows through and contacts with high temperature main flow
Arranging that the blade trailing edge of blade trailing edge cooling socket arrangement 9 splits leaf back 7 at seam, the little separation whirlpool that ball-and-socket chamber is internally formed is by cold
But jet adsorbs on the surface of ball-and-socket, defines one layer of quality preferable air film layer on the surface of ball-and-socket, isolates with high temperature main flow,
The most relatively low close to the fluid temperature (F.T.) of the trailing edge ball-and-socket near surface of outlet, until leaving last socket arrangement, air film layer
Just gradually broken and mixed with high temperature main flow rapidly, therefore can be predicted that the layout of blade trailing edge cooling socket arrangement 9 can be more
The covering on trailing edge surface of good " protection " the air film layer, and completely cut off with high temperature main flow, thus obtain higher gas film cooling efficiency,
Enhance blade trailing edge and split at seam the cooling effect at the solid of leaf back 7 side.In addition, the cooling air film of socket region occurs
Flow separation is the most attached, also will change the convective heat-transfer coefficient on trailing edge surface.Meanwhile, at staggered arrangement, ball-and-socket arranges that Fluid field is mutual
Interfere, and staggered arrangement arranges that lower ball-and-socket covers the more region of internal cooling cavity hot surface and trailing edge surface, therefore at passage
Central area has higher heat transfer coefficient.
The processing technique of the present invention is simple, as traditional cooling structure, and can be by leaf in the way of using model casting
Internal cooling socket arrangement 5 near sheet trailing edge, blade trailing edge cooling socket arrangement 9 and blade interior cooling chamber dividing plate 4 and leaf
Sheet together casts out；But compared with traditional structure being applicable to trailing edge cooling, the present invention is this has laterally bleed groove 6, leaf
Near sheet trailing edge, the turbine blade trailing edge internal cooling of internal cooling socket arrangement 5 and blade trailing edge cooling socket arrangement 9 is with 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 play effect of preferably conducting heat yet
Really, the problem that heat transfer structure is difficult of arranging in narrower blade trailing edge internal cooling channel is solved；Logical in blade trailing edge cooling
The blade trailing edge cooling socket arrangement 9 that in road, staggered arrangement is arranged is internal, separates whirlpool and merges with the vortex in main channel, and cooling blast is inhaled
The surface being attached to ball-and-socket defines quality preferable air film layer, until leave last ball-and-socket just gradually broken and rapidly with
High temperature main flow mixes so that gas film cooling efficiency obtains a certain degree of lifting, and enhance at the solid of trailing edge leaf back side 7 is cold
But effect；This with internal cooling socket arrangement 5, blade trailing edge cooling near laterally bleed 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 socket arrangement and there will be the stream of complexity
Dynamic separate, the most attached, turn phenomenons such as twisting the most in advance, can produce significant augmentation of heat transfer effect, and staggered arrangement arrange under ball-and-socket covering
Blade interior cooling chamber hot surface 3 and blade trailing edge split the more region of leaf back 7 at seam, therefore in the central area of passage
There is higher heat transfer coefficient.This cooling structure has important for the cooling effect promoting turbine blade trailing edge region further
Meaning.
Claims (8)
1. a turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket, it is characterised in that this turbine blade has
There is blade interior cooling chamber (2) and be arranged on turbine blade end face the cooling stream being connected with blade interior cooling chamber (2)
Blade interior cooling chamber hot surface (3) that body flows to manage in (1), and blade interior cooling chamber (2) is staggeredly equipped with some blades
Internal cooling cavity dividing plate (4), blade interior cooling chamber hot surface (3) and some blade interior cooling chamber dividing plate (4) constitute
The internal U-shaped cooling duct of flat blade；
It has been evenly arranged internal cooling ball-and-socket near blade trailing edge in blade interior cooling chamber hot surface (3) near blade trailing edge
Structure (5), some grooves (6) of laterally bleeding are arranged in side, cooling duct near trailing edge, the blade tail near leaf basin lip (8)
Edge is split leaf back at seam (7) place and has been evenly arranged blade trailing edge cooling socket arrangement (9), and some grooves (6) of laterally bleeding are used for will
It is disposed with the internal cooling channel of internal cooling socket arrangement (5) near blade trailing edge to tie with being disposed with blade trailing edge cooling ball-and-socket
The outside cooling duct of structure (9) is connected.
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket the most according to claim 1, it is special
Levying and be, near blade trailing edge, internal cooling socket arrangement (5) is that staggered arrangement is arranged or in-line arrangement is arranged.
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket the most according to claim 2, it is special
Levying and be, what near blade trailing edge, internal cooling socket arrangement (5) was arranged flows to spacing Ps/ D is between 0.5 to 2, and exhibition is to spacing
Pd/ D is between 0.5 to 2, and relative depth δ of ball-and-socket/D is between 0.05 to 0.5.
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket the most according to claim 1, it is special
Levying and be, groove of laterally bleeding (6) is rectangular channel or trapezoidal channel.
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket the most according to claim 4, it is special
Levying and be, the length of groove of laterally bleeding (6) is between 8mm to 16mm, and height, between 1.5mm to 3.5mm, flows to spacing and exists
Between 15mm to 30mm.
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket the most according to claim 1, it is special
Levy and be, cooling blast split seam height t/H between 0.5 to 1.5, split seam inclined angle alpha between 5 ° to 15 °.
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket the most according to claim 1, it is special
Levying and be, cooling gas is blown than M between 0.2 to 1.5 from the jet flow groove ejection split near seam, air film.
A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket the most according to claim 1, it is special
Levy and be, blade trailing edge cooling socket arrangement (9) be staggered arrangement arrange or in-line arrangement arrange, layout flow to spacing be 10～
20mm, opening up to spacing is 7～17mm, flows to comprise 5～9 vollyball nests, open up to including 2～4 vollyball nests, relative depth δ of ball-and-socket/
D is between 0.05 to 0.5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
|---|---|---|---|
| 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 true CN106168143A (en) | 2016-11-30 |
| CN106168143B CN106168143B (en) | 2017-12-15 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| CN112523810A (en) * | 2020-12-14 | 2021-03-19 | 北京航空航天大学 | Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam |
| FR3102794A1 (en) * | 2019-10-31 | 2021-05-07 | Safran Aircraft Engines | TURBOMACHINE COMPONENT WITH IMPROVED COOLING PORTS |
| CN113356931A (en) * | 2021-06-30 | 2021-09-07 | 西安交通大学 | Modeling micro-pit structure for enhancing cooling performance of blade trailing edge slotting wall surface |
| CN113586165A (en) * | 2021-07-20 | 2021-11-02 | 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 |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| FR3102794A1 (en) * | 2019-10-31 | 2021-05-07 | Safran Aircraft Engines | TURBOMACHINE COMPONENT WITH IMPROVED COOLING PORTS |
| 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 |
| CN112523810A (en) * | 2020-12-14 | 2021-03-19 | 北京航空航天大学 | Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam |
| 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 |
| CN113356931A (en) * | 2021-06-30 | 2021-09-07 | 西安交通大学 | Modeling micro-pit structure for enhancing cooling performance of blade trailing edge slotting wall surface |
| 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 |
| CN113586165A (en) * | 2021-07-20 | 2021-11-02 | 西安交通大学 | Turbine blade with single kerosene cooling channel |
| 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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| CN106168143B (en) | 2017-12-15 |
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