CN114876581A - Turbine blade trailing edge enhanced heat exchange semi-split seam cooling structure - Google Patents
Turbine blade trailing edge enhanced heat exchange semi-split seam cooling structure Download PDFInfo
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- CN114876581A CN114876581A CN202210517665.4A CN202210517665A CN114876581A CN 114876581 A CN114876581 A CN 114876581A CN 202210517665 A CN202210517665 A CN 202210517665A CN 114876581 A CN114876581 A CN 114876581A
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- 238000001816 cooling Methods 0.000 title claims abstract description 100
- 238000005192 partition Methods 0.000 claims abstract description 23
- 239000000112 cooling gas Substances 0.000 claims description 21
- 238000005452 bending Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 10
- 238000005728 strengthening Methods 0.000 abstract description 4
- 101100334009 Caenorhabditis elegans rib-2 gene Proteins 0.000 description 17
- 238000004378 air conditioning Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- 125000006850 spacer group Chemical group 0.000 description 4
- 230000008602 contraction Effects 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to the field of design of turbine blades, and relates to a turbine blade trailing edge heat exchange strengthening half-split seam cooling structure which comprises a blade back side, a blade basin side and partition ribs, wherein the outer surface of the blade back side is a blade suction surface, and the outer surface of the blade basin side is a blade pressure surface; when the cooling air flows out from the outlet, the cooling air reaches the W-shaped rib and then needs to bypass the W-shaped rib to continuously flow backwards, and the cooling air stays at the W-shaped rib to a certain extent, so that the cooling area and the cooling capacity of the suction surface of the blade are increased; meanwhile, the opening of the W-shaped rib faces the cold air cavity, the flow path of cooling air is changed when the cooling air enters the opening of the W-shaped rib, one part of the cooling air continuously flows out along the direction of the blade, and the other part of the cooling air flows out along the directions of the two sides along the inclined edge of the W-shaped rib and respectively flows into the partition ribs on the two sides, so that the full coverage of the cooling of the tail edge of the blade is realized, the cooling effect on the suction surface of the blade is enhanced, and the convection heat transfer coefficient of the wall surface of the half-splitting seam is improved.
Description
Technical Field
The utility model belongs to turbine blade design field, in particular to turbine blade trailing edge strengthens half crack cooling structure of heat transfer.
Background
The turbine rotor blade works in a high-temperature and high-pressure severe environment for a long time, the borne load is large, particularly the trailing edge position is one of areas with the highest thermal load of the blade, the thickness of the trailing edge area is small, an inner cooling channel is narrow, and efficient heat exchange strengthening measures are difficult to take. When designing an air-cooled turbine rotor blade, because the trailing edge needs to be cooled, a trailing seam structure is usually designed at the trailing edge of the blade, as shown in fig. 1, cold air is discharged from an inner cavity 1 into a main channel 2 through a trailing seam channel, so as to cool the trailing edge region.
In prior designs, the blade tail slot is typically designed as a half-split slot cooling configuration, as shown in FIG. 1. The cooling airflow of the half-split structure flows out along the tangential direction of the pressure surface, the adherence is good, the air film protection is realized on the pressure surface of the trailing edge of the blade, and the air film cooling efficiency almost reaches the limit. However, for the suction surface, the temperature is still reduced by means of heat conduction of the wall surface, and the temperature reduction range is far inferior to the effect of convection cooling, so that generally, the temperature of the wall of the suction surface at the tail edge of the blade is higher than that of the wall of the split seam, and the conventional half-split seam cooling structure is difficult to realize effective reduction of the temperature of the wall surface at one side of the suction surface.
Therefore, how to improve the overall cooling effect at the trailing edge of the turbine blade is a problem to be solved.
Disclosure of Invention
The utility model aims at providing a turbine blade trailing edge strengthens half crack cooling structure of heat transfer to solve among the prior art problem that suction surface cooling efficiency is low, turbine blade trailing edge comprehensive cooling effect is poor.
The technical scheme of the application is as follows: a turbine blade trailing edge enhanced heat exchange half-split seam cooling structure comprises a blade back side and a blade basin side, wherein the blade back side is a blade suction surface, the blade basin side is a blade pressure surface, a cold air cavity is arranged on the inner side of a blade, and partition ribs are arranged at the outlet of the cold air cavity at intervals; a half-split seam wall surface is arranged between the partition ribs, a W-shaped rib is arranged on the half-split seam wall surface, the opening of the W-shaped rib faces the cold air cavity, the opening end of the W-shaped rib is positioned at the higher width part of the partition rib, the tail end of the W-shaped rib is positioned at the lower width part of the partition rib, and the thickness of the W-shaped rib is smaller than the height of the cooling air outlet; and the cooling air enters the wall surface of the half-splitting seam from the cold air cavity and then flows out from the upper part of the W-shaped rib to form a cooling air film.
Preferably, the W-shaped rib is provided with cooling holes arranged along the radial direction of the blade, the inlets and outlets of the cooling holes are both in the span direction of the blade, and after the cooling gas reaches the wall surface of the half-splitting seam, a part of the cooling gas flows out from the cooling holes to cool the wall surface of the half-splitting seam.
Preferably, the W-shaped rib comprises two groups of outer folding plates positioned at the outer side and two groups of inner folding plates positioned at the inner side, the outer folding plates and the adjacent inner folding plates form a V-shaped structure, the outer folding plates and the adjacent inner folding plates form an inverted triangular inner folding area at the opening side of the W-shaped rib, the adjacent inner folding plates form a triangular outer expanding area at the W-shaped tail end, and the outer folding plates and the partition ribs form a right-angled triangular backflow area at the W-shaped tail end.
Preferably, the included angle between the outer folding plate and the spanwise direction of the blade is 45 degrees, and the included angle between the inner folding plate and the spanwise direction of the blade is 135 degrees.
Preferably, at least two groups of W-shaped ribs are arranged side by side along the spanwise direction of the blade, the cooling holes of the W-shaped ribs in the same row are correspondingly arranged, a gap is reserved between any two adjacent groups of W-shaped ribs and a baffling area is formed, and the cooling air flows along the bending direction of the baffling area after entering the baffling area.
Preferably, both ends of the W-shaped rib are respectively and integrally and fixedly matched with the side walls of the partition ribs on both sides.
Preferably, the thickness of the W-shaped rib is 1/2 to 1/3 of the cooling air outlet height.
Preferably, the radial height of the W-shaped rib is 2 times of the radial height of the barrier rib.
The turbine blade trailing edge heat exchange strengthening half-split cooling structure comprises a blade back side, a blade basin side and partition ribs, wherein the outer surface of the blade back side is a blade suction surface, the outer surface of the blade basin side is a blade pressure surface, and a cold air cavity is formed between the blade back side and the blade basin side; the suction surface of the blade and the W-shaped rib are respectively positioned on two sides of the back side of the blade at the tail edge, when cooling air flows out of the cold air cavity and reaches the W-shaped rib, on one hand, the heat exchange area is increased due to the existence of the rib, so that the heat exchange of the wall surface of the half-slit is strengthened, on the other hand, the cooling hole in the rib can enable the cooling air to flow through the cooling hole, a layer of air film is formed at the downstream of the rib, the wall surface of the half-slit with the rib is effectively cooled, and the problem that the cooling air cannot well cover the downstream area of the rib due to the fact that the rib is added is solved, so that the cooling effect is poor. Through the arrangement of the W-shaped ribs with the cooling holes, the full coverage of the cooling at the tail edge of the blade is realized, the convective heat transfer coefficient at the wall surface of the half-splitting seam is improved, and the comprehensive cooling effect of the tail edge half-splitting seam structure is effectively improved.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic view showing the structure of the trailing edge of a blade in the prior art;
FIG. 2 is a schematic diagram of a two-dimensional heat transfer model of a conventional half-split structure;
FIG. 3 is a schematic view of the trailing edge structure of the salient blade of the present application;
FIG. 4 is a schematic view of the overall structure of the present application;
FIG. 5 is an isometric illustration of the present application highlighting a half-split cooling configuration;
FIG. 6 is a schematic view of the W-shaped rib and rib structure of the present application.
1. A cold air chamber; 2. a W-shaped rib; 3. partition ribs; 4. a half-split slit wall surface; 5. a cooling hole; 6. a blade suction surface; 7. a blade pressure face; 8. an outer folded plate; 9. an inner folded plate; 10. an adduction zone; 11. an outward expansion region; 12. a back flow area; 13. a baffling area; 14. and a cold air cavity outlet.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A turbine blade trailing edge heat exchange strengthening half-split slit cooling structure is shown in figure 2 as a conventional half-splitTwo-dimensional heat transfer model schematic diagram of slot structure. Under the condition of unchanged cooling gas consumption of the gas film, the wall surface temperature T of the tail edge split seam is caused by the fact that the adherence of the cooling gas film of the half split seam is very high and the cooling efficiency of the gas film basically reaches the upper limit of the cooling efficiency w1 The possibility of continuous reduction is less, and the comprehensive cooling effect of the tail edge is mainly determined by the wall temperature T of the suction surface of the tail edge of the blade w2 。
Assuming that the gas temperature is T g The convective heat transfer coefficient of the gas and the suction surface of the trailing edge of the blade is h g (ii) a The cold air flows out of the cold air cavity and has a temperature T c The convective heat transfer coefficient of the cold air and the wall surface of the tail edge cleft is h c (ii) a The wall thickness of the tail edge of the blade is delta, the heat conductivity coefficient is k, and the wall surface temperature of the tail edge cleft joint is T w1 The wall temperature of the suction surface at the trailing edge of the blade is T w2 。
According to the assumption of the one-dimensional heat transfer process, the following heat transfer equilibrium equation is provided:
wherein, T aw Is the adiabatic wall temperature. According to the formula of film cooling efficiency
Formula (1) can be changed to
From this, the wall temperature relation of the suction surface at the trailing edge of the blade can be obtained as
As can be seen from the formula (3), the wall temperature T of the suction surface at the trailing edge of the blade is constant under the condition that other variables are kept constant w2 Along with the air film cooling efficiency eta and the convective heat transfer coefficient h of the cold air and the wall surface of the tail edge cleft joint c Is increased and is decreased. From the foregoing, the gas filmThe improvement range of the cooling efficiency eta is quite limited, so that the increase of the convective heat transfer coefficient h between the cold air and the wall surface of the tail edge cleft seam is considered c By reducing the wall temperature T of the suction surface at the trailing edge of the blade w2 。
As shown in fig. 3, 4, and 5, the specific design includes: the blade dorsal part, blade basin side and spacer rib 3, the dorsal surface of blade is blade suction surface 6, the surface of blade basin side is blade pressure surface 7, be air conditioning chamber 1 between blade dorsal part and the blade basin side, air conditioning chamber 1 sets up the air conditioning export in trailing edge department, cool off the trailing edge, 1 exit intervals in air conditioning chamber are provided with spacer rib 3, multiunit spacer rib 3 is along the exhibition of blade to even setting, be 1 exports in air conditioning chamber 3 between arbitrary adjacent spacer rib.
A half-split seam wall surface 4 is arranged between the partition ribs 3, the half-split seam wall surface 4 is arranged on the inner wall surface at the back side of the blade, a W-shaped rib 2 is arranged on the half-split seam wall surface 4, the opening of the W-shaped rib 2 faces the cold air cavity 1, the open end of the W-shaped rib 2 is positioned at the position where the width of the partition rib 3 is higher, the tail end of the W-shaped rib 2 is positioned at the position where the width of the partition rib 3 is lower, and the thickness of the W-shaped rib 2 is smaller than the height of the outlet 14 of the cold air cavity; the cooling air enters the half-slit wall surface 4 from the cold air cavity 1 and then flows out from the upper part of the W-shaped rib 2 to form a cooling air film.
The W-shaped ribs 2 are integrally arranged on the wall surface 4 of the half-split seam, namely the inner wall surface of the back side of the blade, the suction surface 6 of the blade and the W-shaped ribs 2 are respectively positioned at two sides of the back side of the blade at the tail edge, and when cooling air flows out from an outlet and reaches the W-shaped ribs 2, the existence of the W-shaped ribs 2 increases the heat exchange area, so that the heat exchange of the wall surface 4 of the half-split seam is strengthened.
Preferably, the W-shaped rib 2 is provided with a cooling hole 5 arranged along the radial direction of the blade, the inlet and the outlet of the cooling hole 5 are both in the span direction of the blade, and after the cooling gas reaches the wall surface 4 of the half-split seam, a part of the cooling gas flows out from the cooling hole 5 to cool the wall surface of the half-split seam.
Through setting up cooling hole 5, the cooling gas can better paste with half crack wall 4 mutually when 2 departments of W type rib flow, alleviates the problem that 4 rib low reaches cold air adherence of half crack wall are poor that lead to after the ribbing, effectively improves the heat transfer homogeneity.
The cooling holes 5 can enable cooling air to flow through the cooling holes, a layer of air film is formed at the downstream of the W-shaped rib 2, the ribbed half-slit wall surface 4 is effectively cooled, and the problem that the cooling air cannot well cover the downstream area of the W-shaped rib 2 due to ribbing, and therefore the cooling effect is poor is solved. Through the arrangement of the W-shaped ribs 2 with the cooling holes 4, the full coverage of the cooling at the tail edge of the blade is realized, the heat convection coefficient at the wall surface 4 of the half-splitting seam is improved, and the comprehensive cooling effect of the tail edge half-splitting seam structure is effectively improved.
As shown in fig. 6, preferably, the W-shaped rib 2 includes two sets of outer folding plates 8 located on the outer side and two sets of inner folding plates 9 located on the inner side, the outer folding plates 8 and the adjacent inner folding plates 9 form a V-shaped structure, the outer folding plates 8 and the adjacent inner folding plates 9 form an inverted triangular inward contraction area 10 on the opening side of the W-shaped rib 2, the adjacent inner folding plates 9 form a triangular outward expansion area 11 on the W-shaped end, the outer folding plates 8 and the partition ribs 3 form a right-angled triangular backflow area 12 on the W-shaped end, and the backflow area 12 is symmetrically arranged on two sides of the outward expansion area 11.
Two groups of cooling holes 5 which are arranged side by side are arranged on each group of the outer folded plate 8 and the inner folded plate 9.
When the cooling gas reaches the inner contraction zone 10 of the W-shaped rib 2, part of the cooling gas is gathered along the shape of the inner contraction zone 10, then the W-shaped rib 2 and the wall surface 4 of the half-cleft seam are cooled along the cooling hole 5, after the cooling gas flows out of the cooling hole 5, one part of the cooling gas enters the outer expansion zone 11, the other part of the cooling gas enters the backflow zone 12, the cooling gas entering the outer expansion zone 11 flows out towards the expanding direction and the expanding direction of the blade, and the part of the cooling gas entering the backflow zone 12 is deflected along the opposite direction of the outflow of the cooling gas and expands with the cooling gas of the outer expansion zone 11 to generate turbulence, so that the cooling uniformity of the cooling gas is improved, and the cooling quality is ensured.
Preferably, the angle between the outer flap 8 and the spanwise direction of the blade in the adjacent set of outer flaps 8 and inner flaps 9 is 45 °, the angle between the inner flap 9 and the spanwise direction of the blade is 135 °, and the angle between the outer flap 8 and the inner flap 9 of the other set of W-shaped ribs 2 is opposite to the above-mentioned angle. The outside folded plate 8 and the interior folded plate 9 through setting up the slope realize the spanwise flow of cooling gas, and the angle of the interior folded plate 9 and the outside folded plate 8 of course is not limited to above-mentioned angle, and this version angle that can reach this effect all is in the protection scope of this application, and interior folded plate 9 under the different angles has certain difference with the flow direction that 8 cooling gas of outside folded plate flowed out, and the homogeneity after the turbulent flow of production has certain difference, and specific angle can be adjusted according to actual need.
Preferably, at least two groups of W-shaped ribs 2 are arranged side by side along the spanwise direction of the blade, the cooling holes 5 of the W-shaped ribs 2 in the same row are correspondingly arranged, a gap is formed between any two adjacent groups of W-shaped ribs 2 to form a baffling area 13, and after the cooling air enters the baffling area 13, a part of the cooling air flows along the bending direction of the baffling area 13, and a part of the cooling air enters the cooling holes 5. The baffling area 13 is W-shaped, and when the cooling air flows in the baffling area 13, the cooling air flows in a more direction under the guidance of the baffling area 13, so that the stable cooling of the partition ribs 3 is realized.
Preferably, both ends of the W-shaped rib 2 are respectively and integrally and fixedly matched with the side walls of the partition ribs 3 at both sides, so that the supporting strength and the stability of the structure at the tail edge of the blade are enhanced.
Preferably, the thickness of the W-shaped rib 2 is 1/2-1/3 of the height of the cold air cavity outlet 14, the split flow of the cooling air at the W-shaped rib 2 under different thicknesses can be different, the spanwise flow can be slightly different, and the fine adjustment can be carried out according to the requirements of different types of blades.
Preferably, the radial height of the W-shaped rib 2 is 2 times of the radial height of the partition rib 3, the flow at the outlet 14 of the cooling air cavity under different spanwise lengths can be different, the flow rate of the cooling air is different, and fine adjustment can be carried out according to different model requirements of the blade.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A turbine blade trailing edge enhanced heat exchange half-split seam cooling structure comprises a blade back side and a blade basin side, wherein the blade back side is a blade suction surface (6), the blade basin side is a blade pressure surface (7), a cold air cavity (1) is arranged on the inner side of a blade, and partition ribs (3) are arranged at the outlet (14) of the cold air cavity at intervals; the method is characterized in that: half-split seam wall surfaces (4) are arranged between the partition ribs (3), W-shaped ribs (2) are arranged on the half-split seam wall surfaces (4), openings of the W-shaped ribs (2) face the cold air cavity (1), the open ends of the W-shaped ribs (2) are located at the positions where the width of the partition ribs (3) is higher, the tail ends of the W-shaped ribs are located at the positions where the width of the partition ribs (3) is lower, and the thickness of the W-shaped ribs (2) is smaller than the height of the cold air cavity outlet (14); the cooling air enters the half-split seam wall surface (4) from the cold air cavity (1) and then flows out from the upper part of the W-shaped rib (2) to form a cooling air film.
2. The turbine blade trailing edge enhanced heat exchange half-slit cooling structure of claim 1, wherein: and cooling holes (5) arranged along the radial direction of the blade are formed in the W-shaped rib (2), the inlet and the outlet of each cooling hole (5) are both in the spreading direction of the blade, and after the cooling gas reaches the half-split seam wall surface (4), a part of the cooling gas flows out of the cooling holes (5) to cool the half-split seam wall surface.
3. The turbine blade trailing edge enhanced heat exchange half-slit cooling structure of claim 1, wherein: w type rib (2) are including two sets of exterior flap (8) that are located the outside and two sets of interior flap (9) that are located the inboard, exterior flap (8) and adjacent interior flap (9) form V type structure, exterior flap (8) and adjacent interior flap (9) form triangle-shaped's adduction district (10) on one side of the opening of W type rib (2), and are adjacent interior flap (9) expand district (11) outward at the end formation triangle-shaped of W type, exterior flap (8) and separate rib (3) form right triangle-shaped's return flow district (12) at the end of W type.
4. The turbine blade trailing edge enhanced heat exchange half-slit cooling structure of claim 3, wherein: the included angle between the outer folded plate (8) and the spanwise direction of the blades is 45 degrees, and the included angle between the inner folded plate (9) and the spanwise direction of the blades is 135 degrees.
5. The turbine blade trailing edge enhanced heat exchange half-slit cooling structure of claim 2, wherein: at least two groups of W-shaped ribs (2) are arranged side by side along the spanwise direction of the blade, cooling holes (5) of the W-shaped ribs (2) in the same row are correspondingly arranged, a gap is reserved between any two adjacent groups of W-shaped ribs (2) to form a flow-bending area (13), and cooling air flows along the bending direction of the flow-bending area (13) after entering the flow-bending area (13).
6. The turbine blade trailing edge enhanced heat exchange half-slit cooling structure of claim 1, wherein: and two ends of the W-shaped rib (2) are respectively and integrally and fixedly matched with the side walls of the partition ribs (3) at two sides.
7. The turbine blade trailing edge enhanced heat exchange half-slit cooling structure of claim 1, wherein: the thickness of the W-shaped rib (2) is 1/2-1/3 of the height of the cold air cavity outlet (14).
8. The turbine blade trailing edge enhanced heat exchange half-slit cooling structure of claim 1, wherein: the radial height of the W-shaped ribs (2) is 2 times of the radial height of the partition ribs (3).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210517665.4A CN114876581B (en) | 2022-05-12 | 2022-05-12 | Turbine blade trailing edge enhanced heat exchange half split joint cooling structure |
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| CN202210517665.4A CN114876581B (en) | 2022-05-12 | 2022-05-12 | Turbine blade trailing edge enhanced heat exchange half split joint cooling structure |
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| CN114876581B CN114876581B (en) | 2024-08-13 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5464322A (en) * | 1994-08-23 | 1995-11-07 | General Electric Company | Cooling circuit for turbine stator vane trailing edge |
| 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 |
| US20180003062A1 (en) * | 2016-07-04 | 2018-01-04 | Doosan Heavy Industries Construction Co., Ltd. | Gas turbine blade |
| CN111502771A (en) * | 2020-04-24 | 2020-08-07 | 哈尔滨工程大学 | Tail edge half-splitting seam cooling structure with slit straight ribs |
| CN112343666A (en) * | 2020-12-14 | 2021-02-09 | 北京航空航天大学 | Be applied to half corrugated rib water conservancy diversion structure of splitting seam of turbine blade trailing edge |
| CN215633158U (en) * | 2021-08-26 | 2022-01-25 | 华能国际电力股份有限公司 | Turbine cooling blade of gas turbine |
-
2022
- 2022-05-12 CN CN202210517665.4A patent/CN114876581B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5464322A (en) * | 1994-08-23 | 1995-11-07 | General Electric Company | Cooling circuit for turbine stator vane trailing edge |
| US20180003062A1 (en) * | 2016-07-04 | 2018-01-04 | Doosan Heavy Industries Construction Co., Ltd. | Gas turbine blade |
| 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 |
| CN111502771A (en) * | 2020-04-24 | 2020-08-07 | 哈尔滨工程大学 | Tail edge half-splitting seam cooling structure with slit straight ribs |
| CN112343666A (en) * | 2020-12-14 | 2021-02-09 | 北京航空航天大学 | Be applied to half corrugated rib water conservancy diversion structure of splitting seam of turbine blade trailing edge |
| CN215633158U (en) * | 2021-08-26 | 2022-01-25 | 华能国际电力股份有限公司 | Turbine cooling blade of gas turbine |
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| CN114876581B (en) | 2024-08-13 |
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