CN101581235A - Turbine blade compound cooling structure with sunken internal pin - Google Patents
Turbine blade compound cooling structure with sunken internal pin Download PDFInfo
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- CN101581235A CN101581235A CNA2009100537491A CN200910053749A CN101581235A CN 101581235 A CN101581235 A CN 101581235A CN A2009100537491 A CNA2009100537491 A CN A2009100537491A CN 200910053749 A CN200910053749 A CN 200910053749A CN 101581235 A CN101581235 A CN 101581235A
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- pin
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- sunken
- cooling structure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
- F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
- F28F3/022—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being wires or pins
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- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a turbine blade compound cooling structure with sunken internal pins, comprising a blade passage and a pin; the cooling structure is characterized by further comprising a sunken part, pins are arranged in the blade passage, the blade passage has at least one internal wall surface provided with sunken parts; the sunken parts are arranged in the blade passage in a dislocation way; the sunken parts are of semisphere or part of the semisphere or cone with top part cut off. In the invention, the pins are respectively connected with two wall surfaces in the blade passage, thus on one hand increasing heat exchange area of cooling fluid and on the other hand consolidating the passage; the sunken parts cause the flowing through to generate vortex, thus improving convection and heat exchange effect between the air stream and wall surface of the blade passage and pin surface; meanwhile, when the air stream flows through the sunken parts, direct impact on the pins by the lower reaches of the fluid body is reduced, thus avoiding increase of flow losses while increasing heat exchange area.
Description
Technical field
The present invention relates to the inner cooling unit of a kind of turbine blade of gas turbine, specifically is a kind of turbine blade compound cooling structure with sunken internal pin.
Background technique
Improve the preceding fuel gas temperature of turbine, and then the total efficiency of raising gas turbine energy conversion is a main trend of modern gas turbines development.The temperature of combustion gas has surpassed the melting point of material therefor before the modern gas turbines turbine, therefore be accompanied by the raising again of Turbine Inlet Gas Temperature, press for more efficiently, advanced more cooling technology to be to guarantee the temperature levels in the high temperature parts such as turbine blade of gas turbine, and the control temperature gradient guarantees proper functioning and has enough life cycles in reasonable range.In addition, the cooling technology of enhancing means the use amount that can reduce cooling fluid, therefore makes more air-flow participate in the gas turbine acting, has improved the whole work efficiency of gas turbine.
Existing turbine blade is generally hollow structure, and has a plurality of inner coolant flow channels, and these runners are limited by the wall on the pressure side of blade and suction side wall and each discrete wall respectively.Cooling fluid flows in inner coolant flow channel, with cooling turbine bucket.On the wall on the pressure side of inner flow passage and suction side wall, be provided with turbulator, to improve the heat exchange between each outer wall and the cooling fluid.But these turbulators only are used for strengthening heat exchange, and the load on the turbine blade that takes place in the working procedure is almost all born by each outer wall, so each outer wall must have thicker structure relatively.When the load increase, the wall thickness of each outer wall also must further increase.But because the increase of wall thickness, the cooling effectiveness of blade reduces, and the overall efficiency of gas turbine also reduces thus.
On the other hand, the inner pin rib array structure that adopts usually of existing turbine blade tail is strengthened the heat transfer by convection performance, though the pin rib can significantly improve the heat transfer by convection performance of fluid, can give flows brings very big resistance.Designing requirement for turbine blade inside coolant flow channel is when improving the heat transfer by convection performance, to keep low flow resistance as far as possible.
Find by prior art documents, (U.S.) Han Jieqin, mulberry ground is general. Du Da, Si Ruinasi. Ai Kade, in " gas turbine conduct heat and cooling technology " (Cheng Daijing etc. translate, publishing house of Xi'an Communications University, 2005) readme: at present, the snakelike cooling working medium passage of band flow-disturbing fin is used in the string zone in the blade on inwall, and regional because the integrity of the restriction in space and structure requires to use the passage (the 15th page) of band hour hand rib at trailing edge; The pin rib mostly is used in narrow trailing edge, and there owing to the restriction on making, impact and dress fin passage all can hold any more, and the pin rib can use (the 254th page) better in low Aspect Ratio passage.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art, a kind of turbine blade compound cooling structure with sunken internal pin is proposed, this structure is cooled off turbine blade with high convection current cooling effectiveness, and this blade has advantages of high bearing capacity and need not increase the thickness of blade outer wall simultaneously.This pin compound cooling structure with sunken mainly adopts in the runner that a cooling fluid that is provided with the pin rib flows through, on at least one wall depression is set, and depression and pin rib are arranged in certain sequence, has better cooling performance, therefore may be under identical cooling load condition, reduce the number that the pin rib is arranged, reducing the weight of turbine blade, and reduce the flow resistance of cooling fluid.This pin compound cooling structure with sunken is particularly suitable for the inside cooling at blade trailing edge and middle part.
The present invention is achieved by the following technical solutions, the present invention includes: blade passage, pin rib, depression, be provided with the pin rib in the blade passage, at least one internal face of blade passage is provided with depression, the described blade passage interpolation that is recessed in is arranged and is put, and concave shape is a hemisphere or a hemispheric part or clips the taper shape at top.
Described blade passage comprises on the pressure side wall and suction side wall, on the pressure side is provided with pin rib array between wall and the suction side wall.
Described wall on the pressure side and suction side wall a side wall surface at least therein are provided with array of depressions.
One end of described pin rib links to each other with wall on the pressure side, and the other end of pin rib links to each other with the suction side wall.
The sectional shape of described pin rib is circle, rhombus, square, ellipse or water droplet shape.
Described pin rib is arranged at the blade passage interpolation and is put, and depression is positioned between every hand-manipulating of needle rib and between per two hand-manipulating of needle ribs.
Blade interior passage of the present invention can all adopt the pin compound cooling structure with sunken; Also can be in the part passage, as at middle string and trailing edge internal implementation pin compound cooling structure with sunken, and in other inner passages, implement existing flow-disturbing fin cooling structure.
The pin rib is arranged at blade interior runner interpolation and is put, and depression is positioned between the pin rib of every row
When the present invention flows into when cooling blast, when the pin rib is arrived in gas shock, because the pin rib constantly destroys flow boundary layer, and in the highly disorderly separation wake zone of each pin rib trailing edge generation, and after interacting, produce horse shoe shaped vortex etc. with wall, all of these factors taken together will improve mobile mixed consumingly, significantly improve the heat exchange effect on pin rib surface; Simultaneously, when cooling fluid flows through depression, also produce eddy current, the horseshoe vortex that this eddy current and pin rib produce interacts, and produces stronger eddy current, and the blending that further improves fluid improves the convection heat exchange effect on air-flow and wall, pin rib surface.On the other hand, fluid flows through when depression, can produce left and departs from the eddy current that the flow direction miter angle flows to the right, and the heat transfer of pin rib wake zone is strengthened in so mobile disturbance that helps to strengthen pin rib wake zone fluid.Because be recessed in when improving flow turbulence intensity not hinder fluid flow, and the fluid that flows through depression is deflected, this has reduced the direct bump of fluid to the downstream needle rib, thereby has avoided the increase of flow losses,
Owing to adopted such scheme, the present invention to have following characteristics: the pin rib among the present invention is connected respectively with interior two walls of blade passage, has improved the heat exchange area of cooling fluid on the one hand; Reinforced passage on the other hand.Depression makes chilled fluid flow out-of-date, produces eddy current, has improved the convection heat exchange effect on air-flow and blade passage wall and pin rib surface; Simultaneously, when air flow stream is crossed depression, reduced the direct bump of downstream fluid, thereby avoided the increase of flow losses, also increased the area of heat exchange simultaneously the pin rib.
Description of drawings
Fig. 1 is the cross sectional representation of one embodiment of the present of invention turbine blade of gas turbine.
Fig. 2 is the longitudinal cross-section schematic representation of the inner cooling structure of one embodiment of the present of invention turbine blade of gas turbine.
Fig. 3 is the cross-sectional view of one embodiment of the present of invention blade trailing edge inside.
Fig. 4 is the transverse sectional view along the pin rib-depression compound cooling structure of Fig. 2 center line A-A intercepting.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are elaborated: present embodiment is being to implement under the prerequisite with the technical solution of the present invention, provided detailed mode of execution and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
Present embodiment is that the pin compound cooling structure with sunken with turbine blade tail inside is that example illustrates the present invention.
As shown in Figure 1, present embodiment comprises: turbine blade 10, blade passage 22, on the pressure side wall 14, suction side wall 12.The upper wall surface of blade passage 22 is a suction side wall 12, and the lower wall surface of blade passage 22 is wall 14 on the pressure side.
As shown in Figure 3 and Figure 4, pin rib 18 is formed on the pressure side between the wall 14 and suction side wall 12 by investment casting, and pin rib 18 has improved the heat exchange area of cooling fluid on the one hand, has reinforced blade passage 22 on the other hand.Pin rib 18 is circular column (the pin rib in the present embodiment can make into the structure that sectional shape is rhombus, square, ellipse or water droplet shape equally) for sectional shape.Pin rib 18 is arranged by difference row mode in blade passage 22.Arrow 11 is represented the direction of air-flow among the figure.
(depression in the present embodiment also can be according to actual conditions on the pressure side to be equipped with depression 20 on wall 14 and the suction side wall 12, only on the pressure side on wall and one of them face of suction side wall depression is being set), depression 20 is shaped as hemisphere, or a hemispheric part (also can make the taper shape that becomes to clip the top).Depression 20 makes chilled fluid flow out-of-date, produces eddy current, has improved the convection heat exchange effect on air-flow and blade passage wall and pin rib 18 surfaces; Simultaneously, air flow stream is crossed depression 20 o'clock, has reduced the direct bump of downstream fluid to pin rib 18, thereby has avoided the increase of flow losses, has also increased the area of heat exchange simultaneously.Pin rib 18 is arranged at blade passage 22 interpolations and is put, and depression 20 is positioned between every hand-manipulating of needle rib 18.Depression 20 is arranged at the blade passage interpolation and to be put.
When present embodiment flows into when cooling blast, when pin rib 18 is arrived in gas shock, will significantly improve the heat exchange effect on pin rib 18 surfaces, produce horseshoe vortex near the cooling fluid pin rib 18 simultaneously; Simultaneously, cooling fluid flows through depression 20 o'clock, also produces eddy current, the horseshoe vortex that this eddy current and pin rib 18 produce interacts, produce stronger eddy current, the blending that further improves fluid improves the convection heat exchange effect on air-flow and blade passage internal face, pin rib surface.
Pin rib in the present embodiment is connected respectively with interior two walls of blade passage, has improved the heat exchange area of cooling fluid on the one hand; Reinforced passage on the other hand.Depression makes chilled fluid flow out-of-date, produces eddy current, has improved the convection heat exchange effect on air-flow and blade passage wall and pin rib surface; Simultaneously, when air flow stream is crossed depression, reduced the direct bump of fluid, thereby avoided the increase of flow losses, also increased the area of heat exchange simultaneously the downstream needle rib.
Compare with traditional pin rib cooling structure, under identical inlet air flow condition, the pin rib in the present embodiment The overall heat exchange performance of depression compound cooling structure significantly improves, and flow resistance is basic identical, and is not needing Increase substantially blade strength in the situation of increase outer wall thickness, therefore improved the turbine blade tail heat-resisting quantity Energy. For identical cooling load, then can reduce the density that the pin rib is arranged, thereby reduce the weight of blade, This is very significant in the design of gas turbine.
Claims (6)
1, a kind of turbine blade compound cooling structure with sunken internal pin, comprise: blade passage, pin rib, it is characterized in that, also comprise depression, be provided with the pin rib in the blade passage, at least one internal face of blade passage is provided with depression, and the described blade passage interpolation that is recessed in is arranged and put, and concave shape is a hemisphere or a hemispheric part or clips the taper shape at top.
2, turbine blade compound cooling structure with sunken internal pin according to claim 1 is characterized in that, described blade passage comprises on the pressure side wall and suction side wall, on the pressure side is provided with pin rib array between wall and the suction side wall.
3, turbine blade compound cooling structure with sunken internal pin according to claim 1 is characterized in that, described wall on the pressure side and suction side wall a side wall surface at least therein are provided with array of depressions.
4, turbine blade compound cooling structure with sunken internal pin according to claim 1 is characterized in that, an end of described pin rib links to each other with wall on the pressure side, and the other end of pin rib links to each other with the suction side wall.
5, turbine blade compound cooling structure with sunken internal pin according to claim 1 is characterized in that, the sectional shape of described pin rib is circle, rhombus, square, ellipse or water droplet shape.
6, turbine blade compound cooling structure with sunken internal pin according to claim 1 is characterized in that, described pin rib is arranged at the blade passage interpolation and put, and depression is positioned between every hand-manipulating of needle rib and between per two hand-manipulating of needle ribs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2009100537491A CN101581235A (en) | 2009-06-25 | 2009-06-25 | Turbine blade compound cooling structure with sunken internal pin |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2009100537491A CN101581235A (en) | 2009-06-25 | 2009-06-25 | Turbine blade compound cooling structure with sunken internal pin |
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| CN101581235A true CN101581235A (en) | 2009-11-18 |
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| CNA2009100537491A Pending CN101581235A (en) | 2009-06-25 | 2009-06-25 | Turbine blade compound cooling structure with sunken internal pin |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102410687A (en) * | 2011-07-28 | 2012-04-11 | 上海交通大学 | Heat sink with needle rib-recessed composite array and method for arranging needle rib-recessed composite array |
| CN102615781A (en) * | 2012-03-14 | 2012-08-01 | 肇庆理士电源技术有限公司 | Injection mold for manufacturing battery case |
| CN102979583A (en) * | 2012-12-18 | 2013-03-20 | 上海交通大学 | Separate-type column rib cooling structure for turbine blade of gas turbine |
| CN103542748A (en) * | 2011-07-28 | 2014-01-29 | 上海交通大学 | Needle-rib-concave composited array structure of heat sink and arrangement method for needle-rib-concave composited array |
| CN104533538A (en) * | 2014-12-15 | 2015-04-22 | 厦门大学 | Heat exchange channel wall with rib structure |
| WO2015154442A1 (en) * | 2014-04-08 | 2015-10-15 | 上海交通大学 | Cooling device with tiny diagonal rib/recess composite structure |
| CN108757047A (en) * | 2018-05-25 | 2018-11-06 | 哈尔滨工程大学 | Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column |
| CN110700893A (en) * | 2019-10-14 | 2020-01-17 | 哈尔滨工程大学 | Gas turbine blade comprising V-rib-pit composite cooling structure |
-
2009
- 2009-06-25 CN CNA2009100537491A patent/CN101581235A/en active Pending
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102410687A (en) * | 2011-07-28 | 2012-04-11 | 上海交通大学 | Heat sink with needle rib-recessed composite array and method for arranging needle rib-recessed composite array |
| CN103542748A (en) * | 2011-07-28 | 2014-01-29 | 上海交通大学 | Needle-rib-concave composited array structure of heat sink and arrangement method for needle-rib-concave composited array |
| CN102615781A (en) * | 2012-03-14 | 2012-08-01 | 肇庆理士电源技术有限公司 | Injection mold for manufacturing battery case |
| CN102979583A (en) * | 2012-12-18 | 2013-03-20 | 上海交通大学 | Separate-type column rib cooling structure for turbine blade of gas turbine |
| CN102979583B (en) * | 2012-12-18 | 2015-05-20 | 上海交通大学 | Separate-type column rib cooling structure for turbine blade of gas turbine |
| WO2015154442A1 (en) * | 2014-04-08 | 2015-10-15 | 上海交通大学 | Cooling device with tiny diagonal rib/recess composite structure |
| US10584595B2 (en) | 2014-04-08 | 2020-03-10 | Shanghai Jiao Tong University | Cooling device with small structured rib-dimple hybrid structures |
| CN104533538A (en) * | 2014-12-15 | 2015-04-22 | 厦门大学 | Heat exchange channel wall with rib structure |
| CN108757047A (en) * | 2018-05-25 | 2018-11-06 | 哈尔滨工程大学 | Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column |
| CN110700893A (en) * | 2019-10-14 | 2020-01-17 | 哈尔滨工程大学 | Gas turbine blade comprising V-rib-pit composite cooling structure |
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Application publication date: 20091118 |