CN104791020B - Gas turbine blade with longitudinal crossed rib cooling structure - Google Patents
Gas turbine blade with longitudinal crossed rib cooling structure Download PDFInfo
- Publication number
- CN104791020B CN104791020B CN201510198054.8A CN201510198054A CN104791020B CN 104791020 B CN104791020 B CN 104791020B CN 201510198054 A CN201510198054 A CN 201510198054A CN 104791020 B CN104791020 B CN 104791020B
- Authority
- CN
- China
- Prior art keywords
- rib
- blade
- flow
- dividing plate
- disturbing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 69
- 238000000926 separation method Methods 0.000 claims description 6
- 238000005266 casting Methods 0.000 claims description 3
- 238000000465 moulding Methods 0.000 claims description 3
- 238000005192 partition Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 claims description 2
- 238000012546 transfer Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 11
- 239000000112 cooling gas Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 230000036760 body temperature Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a gas turbine blade with a longitudinal crossed rib cooling structure, which comprises a blade body, a blade root platform, an internal cooling cavity, forced convection heat exchange fins, a blade top gas film cooling hole and the like; the longitudinal crossed rib cooling structure comprises a plurality of turbulence ribs which are arranged on the surface of the inner wall of the blade at equal intervals and an enhanced convection heat exchange loop of longitudinal crossed ribs crossed with the turbulence ribs, and at least one longitudinal crossed rib is arranged along the transverse direction of the enhanced convection heat exchange loop. The gas turbine blade adopts a cooling structure of the turbulence fins which are arranged at equal intervals and the longitudinal intersecting fins which are intersected with the turbulence fins, changes the internal vortex system structure of a cooling channel, improves the heat transfer coefficient of the blade body, improves the heat exchange characteristic of the turbine cooling blade, and prolongs the service life of the blade.
Description
Technical field:
The present invention relates to a kind of gas turbine, be specifically related to a kind of gas turbine blade having and longitudinally intersecting rib cooling structure.
Background technology:
Along with modern gas turbines improving constantly efficiency and demanded power output, the inlet temperature of turbine also improves therewith, and this can make turbine part thermic load be greatly increased, and development of new high-efficient cooling structure concerns combustion gas turbine so that the performance of whole gas turbine.
The flow-disturbing rib of column of leading edge many employings impact-gaseous film control during current turbine cooling structural design, the design of blade high-performance fin and blade trailing edge designs. The rotating channel cooling structure of blade occupies extremely important status in the current turbine type of cooling, is a kind of typical high effect forced heat convection technology. Cooling air-flow turns round flowing inside blade cavity, extend the air-flow time of staying at internal cooling chamber, under the flow-disturbing effect of pressure face side and suction surface side rib sheet, produce the Secondary Flow outmatched on main flow, strengthen the turbulivity of main flow to reach the purpose of enhanced heat exchange.
Cooling air-flow flows in the channel, is internally formed certain thickness thermal boundary layer at rotating channel, and this, by weakening the heat transfer effect of cooling air-flow and blade body, causes blade body temperature too high on the one hand, enhance the life consumption of turbine blade; Cooling gas effciency is relatively low on the other hand, and the cooling gas flow temperature flowed out from trailing edge and air film hole is relatively low, blends with high-temperature fuel gas, will produce bigger mixing loss.
Summary of the invention:
It is an object of the invention to provide a kind of gas turbine blade having and longitudinally intersecting rib cooling structure, this gas turbine blade is effectively broken and is attached to inner flow passage wall thermal boundary layer, improve cooling gas effciency, and reduce gas turbine blade surface thermal load.
For reaching above-mentioned purpose, the present invention adopts following technical scheme to realize:
A kind of have the gas turbine blade longitudinally intersecting rib cooling structure, blade and blade root platform including integrated molding, blade be internally provided with cooling chamber, cooling chamber is by the pressure face of blade and suction surface, and leading edge and trailing edge enclose to set and form, and in leading edge, offer some leading edge film cooling holes, trailing edge offers some trailing edge ventholes, the top of blade is provided with top board, offering some leaf tops film cooling holes on top board, the center of blade root platform offers the air inlet being connected with cooling chamber;
The dividing plate arranged by some longitudinal separations between inner surface and the inner surface of suction surface of blade pressure face is connected, and the air inlet of blade root platform center is divided into two parts by the first dividing plate being arranged on cooling chamber center; The dividing plate one end of the first dividing plate left and right sides being arranged on cooling chamber center is connected with blade root platform, the other end is external part, or one end is connected with top board, the other end is external part, and the dividing plate being connected with blade root platform and the baffle interval being connected with top board are arranged;
The inner surface of blade pressure face between adjacent two dividing plates and between rightmost side dividing plate and trailing edge and be provided with some flow-disturbing ribs being arranged in parallel on the inner surface of suction surface, and intersect rib by longitudinally disposed longitudinal direction between some flow-disturbing ribs being arranged in parallel and run through.
The present invention is further improved by: is arranged on the left of the first dividing plate of cooling chamber center and is followed successively by the second partition being connected with blade root platform, the 3rd dividing plate being connected with top board and the 4th dividing plate being all connected with blade root platform and top board, and offers some impact openings on the 4th dividing plate; It is arranged on the right side of the first dividing plate of cooling chamber center and is followed successively by the 5th dividing plate being connected with blade root platform and the 6th dividing plate being connected with top board.
The present invention is further improved by: trailing edge place forms some trailing edge ventholes by some turbulence columns that longitudinal separation is arranged.
The present invention is further improved by: at least offer a passage exchanged up and down for air-flow in each turbulence columns.
The present invention is further improved by: flow-disturbing rib and longitudinally crossing rib are rectangular fins.
The present invention is further improved by: flow-disturbing rib is oblique rib, V-arrangement rib or separate type V-arrangement rib.
The present invention is further improved by: longitudinally intersects rib and at least arranges one on some flow-disturbing ribs being arranged in parallel, and each longitudinally intersects rib and extends to the last item flow-disturbing rib from Article 1 flow-disturbing rib on some flow-disturbing ribs being arranged in parallel.
The present invention is further improved by: flow-disturbing rib is have the fin of certain angle with air current flow direction, this angle range for 30 °～45 °.
The present invention is further improved by: flow-disturbing rib and longitudinally crossing rib are each through casting.
The present invention is further improved by: flow-disturbing rib height is 0.5mm～1mm, and the width of flow-disturbing rib is consistent with highly maintenance.
Relative to prior art, it is an advantage of the current invention that the longitudinal direction intersected with flow-disturbing rib that blade cooling chamber arranges intersects rib, longitudinally intersect rib and change the vortex structures of cooling air-flow in passage, destroy the thermal boundary layer that cooling air current flow produces, increase turbulivity in passage, strengthen turbine interior heat exchange, be effectively improved cooling gas effciency, reduce blade surface thermic load, make described turbo blade have overall cooling performance preferably. The structure of the present invention is relatively easy simultaneously, has good processability.
Therefore, cooling air-flow, by changing original passage flow-disturbing rib structure, is realized passive control, reduces turbine blade surface temperature by the present invention, improves blade service life.
Accompanying drawing illustrates:
Fig. 1 is the longitdinal cross-section diagram of gas turbine blade of the present invention;
A kind of flow-disturbing rib that Fig. 2 (a) is turbine blade of the present invention and longitudinally crossing rib arrangement form, longitudinally intersect rib and run through from the middle part of oblique rib;
A kind of flow-disturbing rib that Fig. 2 (b) is turbine blade of the present invention and longitudinally crossing rib arrangement form, longitudinally intersect rib and run through from the angle, middle part of V-arrangement rib;
A kind of flow-disturbing rib that Fig. 2 (c) is turbine blade of the present invention and longitudinally crossing rib arrangement form, longitudinally intersect rib and run through from the midline of separate type V-arrangement rib;
A kind of flow-disturbing rib that Fig. 2 (d) is turbine blade of the present invention and longitudinally crossing rib arrangement form, two longitudinal directions intersect ribs and are distributed on oblique rib passage;
A kind of flow-disturbing rib that Fig. 2 (e) is turbine blade of the present invention and longitudinally crossing rib arrangement form, two longitudinal directions intersect ribs and are distributed on the midline of two row V-arrangement ribs.
Detailed description of the invention:
Below in conjunction with accompanying drawing, the present invention is described in further detail:
As shown in Figure 1, the present invention is a kind of has the gas turbine blade longitudinally intersecting rib cooling structure, blade 1 and blade root platform 2 including integrated molding, blade 1 be internally provided with cooling chamber 3, cooling chamber 3 is by the pressure face of blade 1 and suction surface, and leading edge 4 and trailing edge 5 enclose to set and form, and in leading edge 4, offer some leading edge film cooling holes 401, trailing edge 5 offers some trailing edge ventholes 501, the top of blade 1 is provided with top board 6, top board 6 offers some leaf tops film cooling holes 601, the center of blade root platform 2 offers and the air inlet being connected,
The dividing plate arranged by some longitudinal separations between inner surface and the inner surface of suction surface of blade 1 pressure face is connected, and the air inlet of blade root platform 2 center is divided into two parts by the first dividing plate 9 being arranged on cooling chamber 3 center; Being arranged on dividing plate one end of first dividing plate 9 left and right sides of cooling chamber 3 center other end that is connected with blade root platform 2 is external part, or one end other end that is connected with top board 6 is external part, and the dividing plate being connected with blade root platform 2 and the baffle interval being connected with top board 6 are arranged;
The inner surface of blade 1 pressure face between adjacent two dividing plates and between rightmost side dividing plate and trailing edge 5 and be provided with some flow-disturbing ribs 7 being arranged in parallel on the inner surface of suction surface, and intersect rib 8 by longitudinally disposed longitudinal direction between some flow-disturbing ribs 7 being arranged in parallel and run through. Wherein, flow-disturbing rib 7 and longitudinal rib 8 that intersects are rectangular fins. Preferably, flow-disturbing rib 7 is oblique rib, V-arrangement rib or separate type V-arrangement rib. Preferably, flow-disturbing rib 7 is have the fin of certain angle with air current flow direction, this angle range for 30 °～45 °, flow-disturbing rib 7 is highly 0.5mm～1mm, and the width of flow-disturbing rib 7 with highly keep consistent.
Preferably, longitudinally intersect rib 8 and at least arrange one on some flow-disturbing ribs 7 being arranged in parallel, and each longitudinally intersects rib 8 and extends to the last item flow-disturbing rib 7 from Article 1 flow-disturbing rib 7 on some flow-disturbing ribs 7 being arranged in parallel.
Wherein, the 3rd dividing plate 11 be arranged on the left of the first dividing plate 9 of cooling chamber 3 center and be followed successively by the second partition 10 being connected with blade root platform 2, being connected with top board 6 and the 4th dividing plate 12 being all connected with blade root platform 2 and top board 6, and on the 4th dividing plate 12, offer some impact openings 121; It is arranged on the right side of the first dividing plate 9 of cooling chamber 3 center and is followed successively by the 5th dividing plate 13 being connected with blade root platform 2 and the 6th dividing plate 14 being connected with top board 6.
Preferably, trailing edge 5 place forms some trailing edge ventholes 501 by some turbulence columns 15 that longitudinal separation is arranged, and at least offers a passage 151 exchanged up and down for air-flow in each turbulence columns 15.
In order to the present invention is further understood, now its operation principle is done an explanation.
Cooling chamber 3 provided by the invention is rotating channel, cooling air-flow enters blade 1 from blade root platform 2 bottom air inlet, respectively forwardly edge 4 and the flowing of trailing edge 5 direction after central dividing plate, the air-flow of forward edge 4 flowing sprays into leading edge impinging cooling chamber after three fin flow-disturbing chambers, enter main flow combustion gas through leading edge film cooling holes 401 and form air film, cover blade and intercept high-temperature fuel gas;Air-flow to tail source 5 flowing crosses three fin flow-disturbing chambers, flows through the turbulence columns 15 at trailing edge 5 place, enters main flow combustion gas from trailing edge venthole 501. The turbulence columns 15 of blade trailing edge 5 is provided with and is available for air-flow and exchanges the passage 151 of flowing up and down, increase the heat exchange area of cooling air-flow on the one hand, reduce gas-flow resistance on the other hand. Flow-disturbing rib 7 cross section of blade body is rectangle, and becomes 30 °～45 ° angles with air current flow direction, is provided with the top-down longitudinal direction intersected with flow-disturbing rib in each channel interior simultaneously and intersects rib 8, and the height longitudinally intersecting rib 8 is identical with flow-disturbing rib 7. Turbine cooling blade, adds in cooling duct and strengthens cooling air stream turbulence degree after longitudinally intersecting rib 8, weaken the thermal boundary layer adhesion to blade inwall, improve turbine blade cooling performance.
The present invention adds induction can produce new whirlpool in the channel longitudinally through after rib, it is distributed in the both sides of rib, the thermal boundary of channel surface is produced Involving velocity, and the superposition between newly generated whirlpool simultaneously can improve turbulivity in passage further, and blade plays the effect of enhanced heat exchange.
Longitudinal direction proposed by the invention intersects rib and flow-disturbing rib and is integrated casting, and simple in construction is easy to process.
Given by accompanying drawing 1 is only a kind of form of involved internal structure, under not necessarily departing from the premise that the invention is intended to, also can having other and longitudinally intersect the flow-disturbing rib structure that rib intersects, Fig. 2 (a)-2 (e) gives the multiple flow-disturbing rib structure of applicable the object of the invention. Fig. 2 (a) flow-disturbing rib structure is oblique rib, and Fig. 2 (b) is V-arrangement rib, and Fig. 2 (c) intersects rib for separate type V-arrangement rib, Fig. 2 (d) and Fig. 2 (e) for arranging multiple longitudinal direction along single cooling chamber.
The heretofore described case that is embodied as is only several cases that the invention is intended to, it is impossible to be used for limiting the practical range of the present invention, and other equivalence changes done according to the present invention all fall within protection scope of the present invention.
Claims (7)
1. one kind has the gas turbine blade longitudinally intersecting rib cooling structure, it is characterized in that: include blade (1) and the blade root platform (2) of integrated molding, blade (1) be internally provided with cooling chamber (3), cooling chamber (3) is by the pressure face of blade (1) and suction surface, and leading edge (4) and trailing edge (5) enclose to set and form, and in leading edge (4), offer some leading edge film cooling holes (401), trailing edge (5) offers some trailing edge ventholes (501), the top of blade (1) is provided with top board (6), top board (6) offers some leaf tops film cooling holes (601), the center of blade root platform (2) offers the air inlet being connected with cooling chamber (3),
The dividing plate arranged by some longitudinal separations between inner surface and the inner surface of suction surface of blade (1) pressure face is connected, and the air inlet of blade root platform (2) center is divided into two parts by the first dividing plate (9) being arranged on cooling chamber (3) center; The dividing plate one end of the first dividing plate (9) left and right sides being arranged on cooling chamber (3) center is connected with blade root platform (2), the other end is external part, or one end is connected with top board (6), the other end is external part, and the dividing plate being connected with blade root platform (2) and the baffle interval being connected with top board (6) are arranged;
The inner surface of blade (1) pressure face between adjacent two dividing plates and between rightmost side dividing plate and trailing edge (5) and be provided with some flow-disturbing ribs (7) being arranged in parallel on the inner surface of suction surface, and intersect rib (8) by longitudinally disposed longitudinal direction between some flow-disturbing ribs (7) being arranged in parallel and run through;
The first dividing plate (9) left side being arranged on cooling chamber (3) center is followed successively by the 3rd dividing plate (11) that the second partition (10) being connected with blade root platform (2) is connected and the 4th dividing plate (12) being all connected with blade root platform (2) and top board (6) with top board (6), and offers some impact openings (121) on the 4th dividing plate (12); The first dividing plate (9) right side being arranged on cooling chamber (3) center is followed successively by the 5th dividing plate (13) being connected with blade root platform (2) and the 6th dividing plate (14) being connected with top board (6);
Flow-disturbing rib (7) and longitudinally crossing rib (8) are rectangular fins; Flow-disturbing rib (7) is oblique rib, V-arrangement rib or separate type V-arrangement rib.
2. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 1, it is characterised in that: trailing edge (5) place forms some trailing edge ventholes (501) by some turbulence columns (15) that longitudinal separation is arranged.
3. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 2, it is characterised in that: each turbulence columns (15) at least offers a passage (151) exchanged up and down for air-flow.
4. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 1, it is characterized in that: longitudinally intersect rib (8) and at least arrange one on some flow-disturbing ribs (7) being arranged in parallel, and each longitudinally intersects rib (8) and extends to the last item flow-disturbing rib (7) from Article 1 flow-disturbing rib (7) on some flow-disturbing ribs (7) being arranged in parallel.
5. according to claim 1 a kind of have the gas turbine blade longitudinally intersecting rib cooling structure, it is characterised in that: flow-disturbing rib (7) is have the fin of certain angle with air current flow direction, this angle range for 30 °～45 °.
6. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 1, it is characterised in that: flow-disturbing rib (7) and longitudinally crossing rib (8) are each through casting.
7. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 1, it is characterised in that: flow-disturbing rib (7) is highly 0.5mm～1mm, and the width of flow-disturbing rib (7) is consistent with highly maintenance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510198054.8A CN104791020B (en) | 2015-04-23 | 2015-04-23 | Gas turbine blade with longitudinal crossed rib cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510198054.8A CN104791020B (en) | 2015-04-23 | 2015-04-23 | Gas turbine blade with longitudinal crossed rib cooling structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104791020A CN104791020A (en) | 2015-07-22 |
| CN104791020B true CN104791020B (en) | 2016-06-15 |
Family
ID=53556149
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510198054.8A Expired - Fee Related CN104791020B (en) | 2015-04-23 | 2015-04-23 | Gas turbine blade with longitudinal crossed rib cooling structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104791020B (en) |
Families Citing this family (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105888737A (en) * | 2016-06-21 | 2016-08-24 | 中国船舶重工集团公司第七�三研究所 | Novel high-pressure turbine moving blade air cooling structure |
| CN106014488A (en) * | 2016-07-07 | 2016-10-12 | 周丽玲 | Gas turbine blade with longitudinal intersection rib cooling structure |
| CN106706204B (en) * | 2017-02-20 | 2022-06-21 | 华能国际电力股份有限公司 | Pressure sensor cooling device suitable for high temperature environment test |
| CN106870015A (en) * | 2017-04-26 | 2017-06-20 | 哈尔滨工业大学 | A kind of labyrinth type internal cooling structure for high-temperature turbine movable vane trailing edge |
| US10590778B2 (en) * | 2017-08-03 | 2020-03-17 | General Electric Company | Engine component with non-uniform chevron pins |
| CN109307577B (en) * | 2018-08-24 | 2021-09-28 | 北京航空航天大学 | Air cooling device for high-temperature vibration test |
| CN109441555A (en) * | 2018-12-26 | 2019-03-08 | 哈尔滨广瀚动力技术发展有限公司 | A kind of marine gas turbine turbine rotor blade cooling structure |
| US10822987B1 (en) | 2019-04-16 | 2020-11-03 | Pratt & Whitney Canada Corp. | Turbine stator outer shroud cooling fins |
| CN111927562A (en) * | 2020-07-16 | 2020-11-13 | 中国航发湖南动力机械研究所 | Turbine rotor blade and aircraft engine |
| CN113107607B (en) * | 2021-04-13 | 2023-05-26 | 西北工业大学 | Turbine guide vane structure with through-slit on rib at tail edge |
| CN113107609A (en) * | 2021-04-13 | 2021-07-13 | 西北工业大学 | Turbine guide vane structure with rib upper cooling holes at tail edge |
| CN113266436B (en) * | 2021-05-14 | 2022-10-25 | 西安交通大学 | Channel structure for cooling inside of gas turbine stationary blade and gas turbine stationary blade |
| CN113623011B (en) * | 2021-07-13 | 2022-11-29 | 哈尔滨工业大学 | Turbine blade |
| CN113623010B (en) * | 2021-07-13 | 2022-11-29 | 哈尔滨工业大学 | Turbine blade |
| CN113605992B (en) * | 2021-08-26 | 2024-08-27 | 华能国际电力股份有限公司 | Gas turbine cooling blade with internal micro-channels |
| CN114198155B (en) * | 2021-12-15 | 2023-08-01 | 中国科学院工程热物理研究所 | Cooling structure |
| CN114607469A (en) * | 2022-03-16 | 2022-06-10 | 中国联合重型燃气轮机技术有限公司 | Blade of gas turbine and gas turbine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11257004A (en) * | 1998-03-13 | 1999-09-21 | Mitsubishi Heavy Ind Ltd | Film cooling hole structure of gas turbine moving blade |
| EP1132575A1 (en) * | 1999-09-16 | 2001-09-12 | Mitsubishi Heavy Industries, Ltd. | Film cooling hole construction in gas turbine moving-vanes |
| CN202900329U (en) * | 2012-11-29 | 2013-04-24 | 哈尔滨汽轮机厂有限责任公司 | Combustion turbine moving blade |
| CN103437831A (en) * | 2013-08-28 | 2013-12-11 | 国家电网公司 | Steam turbine stator with serpentine channel and steam turbine stator heating and dehumidifying device |
| US8864467B1 (en) * | 2012-01-26 | 2014-10-21 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine flow cooling |
| CN104196574A (en) * | 2014-07-15 | 2014-12-10 | 西北工业大学 | Gas turbine cooling blade |
| CN204609950U (en) * | 2015-04-23 | 2015-09-02 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
-
2015
- 2015-04-23 CN CN201510198054.8A patent/CN104791020B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11257004A (en) * | 1998-03-13 | 1999-09-21 | Mitsubishi Heavy Ind Ltd | Film cooling hole structure of gas turbine moving blade |
| EP1132575A1 (en) * | 1999-09-16 | 2001-09-12 | Mitsubishi Heavy Industries, Ltd. | Film cooling hole construction in gas turbine moving-vanes |
| US8864467B1 (en) * | 2012-01-26 | 2014-10-21 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine flow cooling |
| CN202900329U (en) * | 2012-11-29 | 2013-04-24 | 哈尔滨汽轮机厂有限责任公司 | Combustion turbine moving blade |
| CN103437831A (en) * | 2013-08-28 | 2013-12-11 | 国家电网公司 | Steam turbine stator with serpentine channel and steam turbine stator heating and dehumidifying device |
| CN104196574A (en) * | 2014-07-15 | 2014-12-10 | 西北工业大学 | Gas turbine cooling blade |
| CN204609950U (en) * | 2015-04-23 | 2015-09-02 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104791020A (en) | 2015-07-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104791020B (en) | Gas turbine blade with longitudinal crossed rib cooling structure | |
| CN100557199C (en) | A kind ofly be applicable to the gradually wide type slot staggered rib passage in the cold parts in the turbine blade etc. | |
| CN103089335A (en) | W-shaped rib channel cooling structure suitable for turbine blade backside cooling cavity | |
| JP6001696B2 (en) | Turbine blade with swirling cooling channel and cooling method thereof | |
| CN102425459B (en) | Heavy-type combustion engine high-temperature turbine double-medium cooling blade | |
| CN103437889B (en) | A kind of branch's film hole structure for gas turbine engine cooling | |
| CN102128055A (en) | Gas turbine cooling blade with crown | |
| CN107060892B (en) | A kind of turbine blade cooling unit of gas-liquid coupling | |
| CN105874168A (en) | Gas turbine engine component comprising a trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements | |
| CN103967621A (en) | Cooling device with small inclined rib-dimple composite structure | |
| CN204609950U (en) | Gas turbine blade with longitudinal crossed rib cooling structure | |
| CN112746871B (en) | Continuous wave rib cooling structure with trapezoidal cross section | |
| CN202023597U (en) | Shrouded cooling blade of gas turbine | |
| CN102588000A (en) | Internal cooling structure with grooves and ribs on front edge of turbine blade and method of internal cooling structure | |
| CN103470313B (en) | Turbine blade and turbine with same, and engine | |
| CN101158292A (en) | Ladder type interleaving rib cooling blade suitable for gas-turbine unit | |
| CN208380634U (en) | Gas turbine blade with large and small rib alternative cooling structure | |
| CN114109515B (en) | Turbine blade suction side cooling structure | |
| CN114109514B (en) | Turbine blade pressure surface cooling structure | |
| CN103930742A (en) | Heat exchanger and corresponding flat tube and plate | |
| CN113123832B (en) | Double-wall herringbone turbulence column structure for impact turbulence air film composite cooling | |
| CN113565573A (en) | Turbine blade with internal cooling channels arranged in honeycomb-like manner and gas turbine | |
| CN111271133B (en) | Turbine guider blade with complex fin structure inner cooling channel | |
| CN209129675U (en) | A kind of turbine cooling blade trailing edge structures | |
| CN105649681A (en) | Crossed rib of guide blade of gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160615 Termination date: 20180423 |