CN204609950U - Gas turbine blade with longitudinal crossed rib cooling structure - Google Patents
Gas turbine blade with longitudinal crossed rib cooling structure Download PDFInfo
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- CN204609950U CN204609950U CN201520252656.2U CN201520252656U CN204609950U CN 204609950 U CN204609950 U CN 204609950U CN 201520252656 U CN201520252656 U CN 201520252656U CN 204609950 U CN204609950 U CN 204609950U
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- 238000001816 cooling Methods 0.000 title claims abstract description 72
- 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
- 239000007789 gas Substances 0.000 description 14
- 230000000694 effects Effects 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- OFCNXPDARWKPPY-UHFFFAOYSA-N allopurinol Chemical compound OC1=NC=NC2=C1C=NN2 OFCNXPDARWKPPY-UHFFFAOYSA-N 0.000 description 1
- 230000036760 body temperature Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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Abstract
The utility model discloses a gas turbine blade with a longitudinal intersecting rib cooling structure, which comprises a blade body, a blade root platform, an internal cooling cavity, forced convection heat transfer 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 utility model discloses a gas turbine blade adopts the vortex fin that the equidistance was arranged and the cooling structure of the vertically crossing fin that intersects with it, changes the inside vortex of cooling channel and is the structure, improves blade heat transfer coefficient, improves turbine cooling blade heat transfer characteristic, extension blade life.
Description
Technical field:
The utility model relates to a kind of gas turbine, is specifically related to a kind of gas turbine blade with longitudinally crossing rib cooling structure.
Background technique:
Along with modern gas turbines improving constantly efficiency and demanded power output, the inlet temperature of turbine also improves thereupon, and this can make turbine part heat load greatly increase, and development of new high-efficient cooling structure concerns the performance of combustion gas turbine so that whole gas turbine.
Leading edge many employings impact-gaseous film control during current turbine cooling structural design, the flow-disturbing rib of column design of the design of blade high-performance fin and blade trailing edge.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 convection heat exchange technology.Cooling blast is in blade cavity inside revolution flowing, extend the waiting time of air-flow at internal cooling chamber, under the flow-disturbing effect of pressure side side and suction surface side rib sheet, produce the Secondary Flow outmatched on main flow, strengthen the turbulivity of main flow to reach the object of forced heat exchanging.
Cooling blast flows in the channel, forms certain thickness thermal boundary layer in rotating channel inside, and this will weaken the heat transfer effect of cooling blast and blade body, causes blade body temperature too high on the one hand, enhances the life consumption of turbine blade; Cooled gas utilization ratio is lower on the other hand, and the cooling blast temperature flowed out from trailing edge and air film hole is lower, with high-temperature fuel gas generation blending, will produce larger mixing loss.
Model utility content:
The purpose of this utility model is to provide a kind of gas turbine blade with longitudinally crossing rib cooling structure, this gas turbine blade is effectively broken and is attached to inner flow passage wall thermal boundary layer, improve cooled gas utilization ratio, and reduce gas turbine blade surface thermal load.
For achieving the above object, the utility model adopts following technological scheme to realize:
A kind of have the gas turbine blade longitudinally intersecting rib cooling structure, comprise blade and the blade root platform of integrated molding, the inside of blade is provided with cooling chamber, cooling chamber is by the pressure side of blade and suction surface, and leading edge and trailing edge enclose and form, and in leading edge, offer some leading edge film cooling holes, trailing edge offers some trailing edge air outlet holes, the top of blade is provided with top board, top board offers some leaf tops film cooling holes, the center of blade root platform offers the suction port be connected with cooling chamber;
The dividing plate arranged by some longitudinal separation between the internal surface of blade pressure side and the internal surface of suction surface is connected, and the suction port of blade root platform center is divided into two-part by the first dividing plate being arranged on cooling chamber center; The dividing plate one end being arranged on the first dividing plate left and right sides of 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 be connected with blade root platform and the baffle interval that is connected with top board are arranged;
The internal surface of blade pressure side between adjacent two dividing plates and between rightmost side dividing plate and trailing edge and the internal surface of suction surface are provided with some flow-disturbing ribs be arranged in parallel, and the longitudinal direction by longitudinally arranging between some flow-disturbing ribs be arranged in parallel intersects rib runs through.
The utility model further improves and is: be arranged on the 4th dividing plate being followed successively by the second partition be connected with blade root platform, the 3rd dividing plate be connected with top board and being all connected with blade root platform and top board on the left of the first dividing plate of cooling chamber center, and offer some impact openings on the 4th dividing plate; The 5th dividing plate be connected with blade root platform and the 6th dividing plate be connected with top board is followed successively by the right side of the first dividing plate being arranged on cooling chamber center.
The utility model further improves and is: trailing edge place forms some trailing edge air outlet holes by some turbulence columns that longitudinal separation is arranged.
The utility model further improves and is: each turbulence columns at least offers a vent exchanged up and down for air-flow.
The utility model further improves and is: flow-disturbing rib and longitudinally crossing rib are rectangular fins.
The utility model further improves and is: flow-disturbing rib is oblique rib, V-arrangement rib or separated type V-arrangement rib.
The utility model further improves and is: longitudinally intersect rib and at least arrange one on some flow-disturbing ribs be arranged in parallel, and each longitudinal rib that intersects extends to the last item flow-disturbing rib from Article 1 flow-disturbing rib on some flow-disturbing ribs be arranged in parallel.
The utility model further improves and is: flow-disturbing rib is the fin with air current flow direction with certain angle, and the scope of this angle is 30 ° ~ 45 °.
The utility model further improves and is: flow-disturbing rib and longitudinally crossing rib all pass through casting.
The utility model further improves and is: flow-disturbing rib height is 0.5mm ~ 1mm, and the width of flow-disturbing rib be highly consistent.
Relative to prior art, the utility model has the advantage of that the longitudinal direction crossing with flow-disturbing rib that blade cooling chamber arranges intersects rib, longitudinally intersect the vortex structures that rib changes cooling blast in passage, destroy the thermal boundary layer that cooling blast flowing produces, increase turbulivity in passage, strengthening turbine internal heat, effectively improves cooled gas utilization ratio, reduce blade surface heat load, make described turbine blade have good overall cooling performance.Structure of the present utility model is relatively simple simultaneously, has good processability.
Therefore, the utility model, by changing original passage flow-disturbing rib structure, realizes Passive Control to cooling blast, reduces turbine blade surface temperature, improves blade working life.
Accompanying drawing illustrates:
Fig. 1 is the longitdinal cross-section diagram of the utility model gas turbine blade;
A kind of flow-disturbing rib that Fig. 2 (a) is the utility model turbine blade and longitudinally crossing rib setting type, longitudinally intersect rib and run through from the middle part of oblique rib;
A kind of flow-disturbing rib that Fig. 2 (b) is the utility model turbine blade and longitudinally crossing rib setting type, 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 the utility model turbine blade and longitudinally crossing rib setting type, longitudinally intersect rib and run through from the midline of separated type V-arrangement rib;
A kind of flow-disturbing rib that Fig. 2 (d) is the utility model turbine blade and longitudinally crossing rib setting type, two longitudinal directions intersect rib and are distributed on oblique rib passage;
A kind of flow-disturbing rib that Fig. 2 (e) is the utility model turbine blade and longitudinally crossing rib setting type, two longitudinal directions intersect the midline that rib is distributed on two row V-arrangement ribs.
Embodiment:
Below in conjunction with accompanying drawing, the utility model is described in further detail:
As shown in Figure 1, the utility model is a kind of has the gas turbine blade longitudinally intersecting rib cooling structure, comprise blade 1 and the blade root platform 2 of integrated molding, the inside of blade 1 is provided with cooling chamber 3, cooling chamber 3 is by the pressure side of blade 1 and suction surface, and leading edge 4 and trailing edge 5 enclose and form, and in leading edge 4, offer some leading edge film cooling holes 401, trailing edge 5 offers some trailing edge air outlet holes 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 suction port be connected,
The dividing plate arranged by some longitudinal separation between the internal surface of blade 1 pressure side and the internal surface of suction surface is connected, and the suction port of blade root platform 2 center is divided into two-part by the first dividing plate 9 being arranged on cooling chamber 3 center; The dividing plate one end being arranged on first dividing plate 9 left and right sides of cooling chamber 3 center the other end that is connected with blade root platform 2 is external part, or one end the other end that is connected with top board 6 is external part, and the dividing plate be connected with blade root platform 2 and the baffle interval that is connected with top board 6 are arranged;
The internal surface of blade 1 pressure side between adjacent two dividing plates and between rightmost side dividing plate and trailing edge 5 and the internal surface of suction surface are provided with some flow-disturbing ribs 7 be arranged in parallel, and the longitudinal direction by longitudinally arranging between some flow-disturbing ribs 7 be arranged in parallel intersects rib 8 runs 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 separated type V-arrangement rib.Preferably, flow-disturbing rib 7 is the fin with air current flow direction with certain angle, and the scope of this angle is 30 ° ~ 45 °, and flow-disturbing rib 7 is highly 0.5mm ~ 1mm, and the width of flow-disturbing rib 7 be highly consistent.
Preferably, longitudinally intersect rib 8 and at least arrange one on some flow-disturbing ribs 7 be arranged in parallel, and each longitudinal rib 8 that intersects extends to the last item flow-disturbing rib 7 from Article 1 flow-disturbing rib 7 on some flow-disturbing ribs 7 be arranged in parallel.
Wherein, be arranged on the 4th dividing plate 12 being followed successively by the second partition 10 be connected with blade root platform 2, the 3rd dividing plate 11 be connected with top board 6 and being all connected with blade root platform 2 and top board 6 on the left of the first dividing plate 9 of cooling chamber 3 center, and offer some impact openings 121 on the 4th dividing plate 12; The 5th dividing plate 13 be connected with blade root platform 2 and the 6th dividing plate 14 be connected with top board 6 is followed successively by the right side of the first dividing plate 9 being arranged on cooling chamber 3 center.
Preferably, trailing edge 5 place forms some trailing edge air outlet holes 501 by some turbulence columns 15 that longitudinal separation is arranged, and each turbulence columns 15 at least offers a vent 151 exchanged up and down for air-flow.
In order to further understand the utility model, now an explanation is done to its working principle.
The cooling chamber 3 that the utility model provides is rotating channel, cooling blast enters blade 1 from blade root platform 2 bottom air inlet, respectively to leading edge 4 and the flowing of trailing edge 5 direction after intermediate clapboard, the air-flow flowed to leading edge 4 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; The air-flow flowed to tail source 5 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 air outlet hole 501.The turbulence columns 15 of blade trailing edge 5 is provided with the vent 151 that can exchange flowing for air-flow up and down, increases the heat exchange area of cooling blast 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, and being furnished with the top-down longitudinal direction crossing with flow-disturbing rib in each channel interior intersects rib 8 simultaneously, and the height longitudinally intersecting rib 8 is identical with flow-disturbing rib 7.Turbine cooled blade, adds in cooling channel after longitudinally intersecting rib 8 and strengthens cooling blast turbulivity, weaken the adhesion of thermal boundary layer to blade inwall, improve turbine blade cooling performance.
Induction new whirlpool can be produced in the channel after the longitudinal direction that adds the utility model runs through rib, be distributed in the both sides of rib, Involving velocity is produced to the thermal boundary of channel surface, turbulivity in passage can be improved further with the superposition between stylish generation whirlpool, blade be played to the effect of forced heat exchanging.
The longitudinal direction that the utility model proposes intersects rib and flow-disturbing rib is integrated casting, and structure is simple, easy to process.
Given by accompanying drawing 1 is only a kind of form of involved internal structure, under the prerequisite not departing from the utility model intention, also can have other flow-disturbing rib structures crossing with longitudinally crossing rib, Fig. 2 (a)-2 (e) gives the multiple flow-disturbing rib structure of applicable the utility model object.Fig. 2 (a) flow-disturbing rib structure is oblique rib, and Fig. 2 (b) is V-arrangement rib, and Fig. 2 (c) is separated type V-arrangement rib, and Fig. 2 (d) and Fig. 2 (e) intersects rib for arranging multiple longitudinal direction along single cooling chamber.
Concrete case study on implementation described in the utility model is only several cases of the utility model intention, can not be used for limiting practical range of the present utility model, and other equivalence changes done according to the utility model all drop within protection domain of the present utility model.
Claims (10)
1. one kind has the gas turbine blade longitudinally intersecting rib cooling structure, it is characterized in that: the blade (1) and the blade root platform (2) that comprise integrated molding, the inside of blade (1) is provided with cooling chamber (3), cooling chamber (3) is by the pressure side of blade (1) and suction surface, and leading edge (4) and trailing edge (5) enclose and form, and in leading edge (4), offer some leading edge film cooling holes (401), trailing edge (5) offers some trailing edge air outlet holes (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 suction port be connected with cooling chamber (3),
The dividing plate arranged by some longitudinal separation between the internal surface of blade (1) pressure side and the internal surface of suction surface is connected, and the suction port of blade root platform (2) center is divided into two-part by the first dividing plate (9) being arranged on cooling chamber (3) center; The dividing plate one end being arranged on the first dividing plate (9) left and right sides of 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 be connected with blade root platform (2) and the baffle interval that is connected with top board (6) are arranged;
The internal surface of blade (1) pressure side between adjacent two dividing plates and between rightmost side dividing plate and trailing edge (5) and the internal surface of suction surface are provided with some flow-disturbing ribs (7) be arranged in parallel, and the longitudinal direction by longitudinally arranging between some flow-disturbing ribs (7) be arranged in parallel intersects rib (8) runs through.
2. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 1, it is characterized in that: the 4th dividing plate (12) that the first dividing plate (9) left side being arranged on cooling chamber (3) center is followed successively by the second partition (10) be connected with blade root platform (2), the 3rd dividing plate (11) be connected with top board (6) and is all connected with blade root platform (2) and top board (6), and offer 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) be connected with blade root platform (2) and the 6th dividing plate (14) be connected with top board (6).
3. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 1 and 2, is characterized in that: trailing edge (5) place forms some trailing edge air outlet holes (501) by some turbulence columns (15) that longitudinal separation is arranged.
4. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 3, is characterized in that: each turbulence columns (15) at least offers a vent (151) exchanged up and down for air-flow.
5. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 1 and 2, is characterized in that: flow-disturbing rib (7) and longitudinally crossing rib (8) are rectangular fins.
6. according to claim 1 and 2 a kind ofly have the gas turbine blade longitudinally intersecting rib cooling structure, it is characterized in that: flow-disturbing rib (7) is oblique rib, V-arrangement rib or separated type V-arrangement rib.
7. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 6, it is characterized in that: longitudinally intersect rib (8) and at least arrange one on some flow-disturbing ribs (7) be arranged in parallel, and each longitudinal rib (8) that intersects extends to the last item flow-disturbing rib (7) from Article 1 flow-disturbing rib (7) on some flow-disturbing ribs (7) be arranged in parallel.
8. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 6, is characterized in that: flow-disturbing rib (7) is the fin with air current flow direction with certain angle, and the scope of this angle is 30 ° ~ 45 °.
9. a kind of gas turbine blade with longitudinally crossing rib cooling structure according to claim 6, is characterized in that: flow-disturbing rib (7) and longitudinally crossing rib (8) all pass through casting.
10. according to claim 6 a kind ofly have the gas turbine blade longitudinally intersecting rib cooling structure, it is characterized in that: flow-disturbing rib (7) is highly 0.5mm ~ 1mm, and the width of flow-disturbing rib (7) and being highly consistent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520252656.2U CN204609950U (en) | 2015-04-23 | 2015-04-23 | Gas turbine blade with longitudinal crossed rib cooling structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520252656.2U CN204609950U (en) | 2015-04-23 | 2015-04-23 | Gas turbine blade with longitudinal crossed rib cooling structure |
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| Publication Number | Publication Date |
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| CN204609950U true CN204609950U (en) | 2015-09-02 |
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| CN201520252656.2U Expired - Fee Related CN204609950U (en) | 2015-04-23 | 2015-04-23 | Gas turbine blade with longitudinal crossed rib cooling structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104791020A (en) * | 2015-04-23 | 2015-07-22 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
| CN106812555A (en) * | 2015-11-27 | 2017-06-09 | 中航商用航空发动机有限责任公司 | Turbo blade |
| 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 |
| CN114017133A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Cooled variable-geometry low-pressure turbine guide vane |
-
2015
- 2015-04-23 CN CN201520252656.2U patent/CN204609950U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104791020A (en) * | 2015-04-23 | 2015-07-22 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
| CN104791020B (en) * | 2015-04-23 | 2016-06-15 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
| CN106812555A (en) * | 2015-11-27 | 2017-06-09 | 中航商用航空发动机有限责任公司 | Turbo blade |
| CN106812555B (en) * | 2015-11-27 | 2019-09-17 | 中国航发商用航空发动机有限责任公司 | Turbo blade |
| 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 |
| CN114017133A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Cooled variable-geometry low-pressure turbine guide vane |
| CN114017133B (en) * | 2021-11-12 | 2023-07-07 | 中国航发沈阳发动机研究所 | Cooled variable geometry low pressure turbine guide vane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150902 Termination date: 20170423 |
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| CF01 | Termination of patent right due to non-payment of annual fee |