CN103075202A - Impingement cooling structure with grid turbulence effect in turbine blade - Google Patents
Impingement cooling structure with grid turbulence effect in turbine blade Download PDFInfo
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- CN103075202A CN103075202A CN2013100151613A CN201310015161A CN103075202A CN 103075202 A CN103075202 A CN 103075202A CN 2013100151613 A CN2013100151613 A CN 2013100151613A CN 201310015161 A CN201310015161 A CN 201310015161A CN 103075202 A CN103075202 A CN 103075202A
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Abstract
The invention relates to an impingement cooling structure with a grid turbulence effect in a turbine blade in the design field of turbomachinery. The structure comprises an impingement plate, an internal cooling cavity, a cooling channel, an impingement target plate, impingement holes and grid fins, wherein the internal cooling cavity is surrounded by the impingement plate, the cooling channel is formed by the space between the impingement plate and the impingement target plate, the impingement holes are arranged in the impingement plate, the impingement holes are sequentially or alternately arranged in the impingement plate, and the grid fins are arranged on the inner wall surface of the impingement target plate. According to the cooling structure disclosed by the invention, the grid fins are arranged on the inner wall surface of the impingement target plate, the heat dissipation area of the impingement target plate can be increased on one hand, impingement cooling airflows are disturbed when diffusing around on the inner wall surface of the target plate, the heat exchange performance is further improved, and at the same time the impingement target plate can also be further enhanced by the grid fins. The impingement cooling structure disclosed by the invention is reasonable in design, is simple and is suitable for an internal cooling system of a gas turbine blade.
Description
Technical field
What the present invention relates to is a kind of turbine blade of gas turbine internal cooling structure, and particularly a kind of turbine blade inside is with the impact cooling structure of grid flow-disturbing.
Background technique
Along with the development of modern gas turbines technology, an important means that promotes the gas turbine overall performance is to improve constantly turbine inlet temperature (TIT), and this also just has higher requirement for the heat resistance of turbine blade.The method that promotes at present turbine inlet temperature (TIT) mainly contains two aspects: 1, novel heat-resisting blade material and the cladding material of research; 2, the more reasonable effectively blade cooling structure of design; First method research cycle is long with respect to second method, R﹠D costs are high, therefore be badly in need of designing more efficiently, more advanced turbine cooling structure, make that the turbine blade surface temperature reduces, temperature gradient is reasonable, thereby turbine blade is had enough working life under higher temperature.Meanwhile, use more effectively cooling structure to strengthen cooling effect and also just mean and to save more cooling medium, thereby also promoted the working efficiency of whole gas turbine engine systems from another aspect.Existing Cooling Technique Based On Thermal Driving mainly is divided into: external refrigeration and internal cooling mode, wherein external refrigeration mainly refers to the air film cooling, and the internal cooling mode mainly comprises: the Compound cooling that impacts cooling, the cooling of fin flow-disturbing, the cooling of pin rib and combined by several types of cooling in front.When the modern gas turbines cooled blade adopts the internal cooling design, generally take to impact cooling or adopt with the impact of fin flow-disturbing and cool off for leaf head, take the cooling of fin flow-disturbing or employing with the impact cooling of fin flow-disturbing at the blade middle part, take the cooling of pin rib at the blade afterbody.For the type of cooling with the fin flow-disturbing, employed fin is generally the in-line arrangement fins such as straight rib, V-type rib, W type rib, and fin integral body is arranged in parallel, and this fin can play the effect of disturbing the cooling blast laminar sublayer well, thereby improves heat exchange efficiency.
Find through the retrieval to the prior art document, China Patent No. application number 201210063251.5, patent name: turbine blade leading edge deep gouge rib inner-cooling structure and method thereof, this patent arranges deep gouge at the impact target plate internal face of blade inlet edge, and at the parallel fin of deep gouge setting perpendicular to the high direction of leaf, this utilization is impacted and the Compound cooling mode of parallel fin flow-disturbing can make impact cooling blast impacting target plate after to around when spreading in the interference that is subject to the in-line arrangement fin perpendicular to the high direction of leaf, thereby impacting further raising heat-exchange performance on the basis of cooling off.Yet the similar this impact type of cooling with the fin flow-disturbing is only arranging difform in-line arrangement fin perpendicular to the high direction of leaf, its Compound cooling meaning is namely carried out further heat exchange reinforcement for impacting the type of cooling on the high direction perpendicular to leaf, can not play same turbulent flow reinforced heat transfer effect for being parallel to the high direction of leaf.
Summary of the invention
The present invention is directed to above-mentioned the deficiencies in the prior art, the impact cooling structure of a kind of turbine blade inside with the grid flow-disturbing is provided, can make impact cooling blast the target plate wall to around all can be subject to the fin flow-disturbing in the diffusion process, thereby further promote cooling effect.
The present invention is achieved through the following technical solutions, the present invention includes striking plate, internal cooling cavity, cooling channel, impact target plate, impact opening and grid fin, internal cooling cavity is surrounded by striking plate, striking plate is similar to impact target plate sectional shape, the cooling channel is formed by the space between striking plate and the impact target plate, impact opening is arranged on the striking plate, and impact opening is in-line arrangement or insert row layout on striking plate, and the grid fin is arranged in and impacts on the target plate internal face.
Further, the grid of grid fin is shaped as rectangle in the present invention, rhombus, trapezoidal or Hexagon, the number of impact opening equates or its integral multiple with the grid number of described grid fin, the center of impact opening is over against the grid center of described grid fin, the diameter of impact opening is between 0.5mm to 2mm, spacing between the impact opening and the diameter of impact opening are than between 2 to 10, impact the target plate internal face to the ratio of the distance of striking plate outer wall and impact opening diameter between 2 to 10, the fin sectional shape of grid fin is rectangle, triangle, trapezoidal or semicircle, the fin cross section height of grid fin and impact opening diameter are than between 0.2 to 1.5.
Working principle of the present invention is: cooling blast enters internal cooling cavity from outside cold air source, flow out at a high speed to impact with shape of plasma jet by the impact opening on the striking plate and impact on the target plate, jet impact on the target plate internal face with laminar flow or low turbulent flow form at a high speed to around diffusion, to around the cooling blast of high speed diffusion be subject to around the flow-disturbing effect meeting of grid fin make laminar flow originally or low turbulent flow convert higher the flowing of turbulivity to, thereby around jet, all produce the effect of further forced heat exchanging.Arranging of grid fin increased heat diffusion area on the impact target plate internal face, also plays the effect of the heat transfer effect of increase, and meanwhile the grid fin also plays reinforcement effect for blade.
Compared with prior art, the present invention has following beneficial effect: the present invention is reasonable in design, simple in structure, can make impact cooling blast impact impact the target plate internal face to around all can be subject to the flow-disturbing of fin in the diffusion process, thereby further promote heat transfer effect with respect to traditional impact cooling structure with fin, meanwhile trellis work also can make blade further be reinforced.
Description of drawings
Fig. 1 is embodiment of the invention assembled sectional view;
Fig. 2 is embodiment of the invention cross-sectional view;
Fig. 3 is Fig. 2 Leaf head zone partial enlarged drawing;
Fig. 4 is grid shape turbine blade head impact plate and impact the schematic representation of target plate generate when dull and stereotyped when being rectangle;
Fig. 5 is grid shape turbine blade head impact plate and impact the schematic representation of target plate generate when dull and stereotyped when being rhombus;
Fig. 6 is grid shape turbine blade head impact plate and impact the schematic representation of target plate generate when dull and stereotyped when being trapezoidal;
Fig. 7 is grid shape turbine blade head impact plate and impact the schematic representation of target plate generate when dull and stereotyped when being regular hexagon;
Wherein: 1, striking plate, 2, the cooling channel, 3, internal cooling cavity, 4, impact target plate, 5, impact opening, 6, the grid fin, 7, impact the target plate internal face, 8, the striking plate outer wall.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are elaborated, present embodiment provided detailed mode of execution and concrete operating process, but protection scope of the present invention is not limited to following embodiment take technical solution of the present invention as prerequisite.
Embodiment
Such as Fig. 1, Fig. 2, Fig. 3 and shown in Figure 4, the present invention includes striking plate 1, internal cooling cavity 2, cooling channel 3, impact target plate 4, impact opening 5 and grid fin 6, internal cooling cavity 2 is surrounded by striking plate 1, striking plate 1 is similar to impact target plate 2 sectional shapes, cooling channel 3 is formed by the space between striking plate 1 and the impact target plate 4, impact opening 5 is arranged on the striking plate 1, impact opening 5 in-line arrangement on striking plate 1 is arranged, grid fin 6 is arranged in and impacts on the target plate internal face 7, the grid of grid fin 6 is shaped as rectangle, the number of impact opening 5 equates with the grid number of grid fin 6, the center of impact opening 5 is over against the grid center of described grid fin 6, the diameter of impact opening 5 is between 0.5mm to 2mm, the diameter of the spacing between the impact opening 5 and impact opening 5 is than between 2 to 10, impact target plate internal face 7 to the ratio of the distance of striking plate outer wall 8 and impact opening diameter between 2 to 10, the fin sectional shape of grid fin 6 is rectangle, and the fin cross section height of grid fin 6 and impact opening diameter are than between 0.2 to 1.5.
In the present invention, after cooling blast enters internal cooling cavity 3, enter cooling channel 2 by impact opening 5 with higher speed, and under effect of inertia, impact at a relatively high speed on the impact target plate internal face 7.On impacting target plate internal face 7 in a scope of impact opening 5 because the high speed impact effect of air-flow, it is regional to form a higher heat exchange.Cooling blast impact impact on the target plate internal face 7 after with laminar flow form or low turbulent flow state to around rapid flow, be provided with grid fin 6 owing to face impact opening 5 at impact target plate internal face 7, the area that grid fin 6 surrounds is greater than the area of impact opening 5, therefore impact on target plate internal face 7 surfaces to around the fluid of rapid flow all can be subject to the flow-disturbing effect of grid fin 6, thereby the fluid turbulent degree that flows through grid fin 6 is increased, improve heat-exchange performance.The setting of grid fin 6 has also increased the area of contact of impacting target plate internal face 7 and fluid simultaneously, also can improve heat-exchange performance, and arranging of grid fin 6 can improve the intensity of impacting target plate 4 simultaneously.In the present invention, the grid shape that grid fin 6 surrounds also can be rhombus, trapezoidal, regular hexagon, such as Fig. 5, Fig. 6 and shown in Figure 7.
Processing technology of the present invention is simple, and is the same with the impact cooling structure of fin with tradition, can adopt the mode of investment casting that grid fin 6 and impact target plate 4 are together cast out; But compare with the impact cooling structure of fin with tradition, can make impact cooling blast impact target plate internal face 7 to around all can be subject to the effect of fin flow-disturbing in the flow process, significant for the inner colded cooling effect of further lifting turbine blade.
Claims (6)
1. a turbine blade inside is with the impact cooling structure of grid flow-disturbing, comprise striking plate (1), internal cooling cavity (2), cooling channel (3) and impact target plate (4), internal cooling cavity (2) is surrounded by striking plate (1), striking plate (1) is similar to impact target plate (2) sectional shape, cooling channel (3) is formed by the space between striking plate (1) and the impact target plate (4), characterized by further comprising impact opening (5) and grid fin (6), impact opening (5) is arranged on the striking plate (1), impact opening (5) arranges that at the upper in-line arrangement of striking plate (1) or insert row grid fin (6) is arranged in and impacts on the target plate internal face (7).
2. turbine blade according to claim 1 inside is characterized in that with the impact cooling structure of grid flow-disturbing the grid of described grid fin (6) is shaped as rectangle, rhombus, trapezoidal or Hexagon.
3. turbine blade according to claim 2 inside is characterized in that with the impact cooling structure of grid flow-disturbing the number of described impact opening (5) equates or its integral multiple with the grid number of described grid fin (6).
4. turbine blade according to claim 3 inside is characterized in that with the impact cooling structure of grid flow-disturbing the center of described impact opening (5) is over against the grid center of described grid fin (6).
5. turbine blade according to claim 4 inside is with the impact cooling structure of grid flow-disturbing, it is characterized in that the diameter of described impact opening (5) is between 0.5mm to 2mm, the diameter of the spacing between the impact opening (5) and impact opening (5) is than between 2 to 10, described impact target plate internal face (7) to the ratio of the distance of striking plate outer wall (8) and impact opening diameter between 2 to 10.
6. turbine blade according to claim 5 inside is with the impact cooling structure of grid flow-disturbing, the fin sectional shape that it is characterized in that described grid fin (6) is rectangle, triangle, trapezoidal or semicircle, and the fin cross section height of described grid fin (6) and impact opening diameter are than between 0.2 to 1.5.
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| CN2013100151613A CN103075202A (en) | 2013-01-15 | 2013-01-15 | Impingement cooling structure with grid turbulence effect in turbine blade |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104712372A (en) * | 2014-12-29 | 2015-06-17 | 上海交通大学 | High-performance impact cooling system |
| CN105804873A (en) * | 2015-01-20 | 2016-07-27 | 通用电器技术有限公司 | Wall for hot gas channel in gas turbine |
| CN108387358A (en) * | 2018-05-07 | 2018-08-10 | 复旦大学 | A kind of wind tunnel experiment part and its wind tunnel system with interchangeability |
| CN110192005A (en) * | 2017-01-18 | 2019-08-30 | 西门子股份公司 | Turbo-element |
| CN110242357A (en) * | 2018-03-09 | 2019-09-17 | 中国联合重型燃气轮机技术有限公司 | The blade of gas turbine |
| EP3816407A1 (en) * | 2019-11-04 | 2021-05-05 | Raytheon Technologies Corporation | Impingement cooling with impingement cells on impinged surface |
| CN112780353A (en) * | 2019-11-06 | 2021-05-11 | 曼恩能源方案有限公司 | Device for cooling components of a gas turbine/turbomachine by means of impingement cooling |
| CN113374536A (en) * | 2021-06-09 | 2021-09-10 | 中国航发湖南动力机械研究所 | Gas turbine guide vane |
| CN114439553A (en) * | 2022-03-04 | 2022-05-06 | 中国航发沈阳发动机研究所 | Low thermal stress turbine cooling guide vane |
| CN114961895A (en) * | 2022-06-16 | 2022-08-30 | 大连理工大学 | Turbine outer ring adopting double-helix cooling structure |
| CN115013075A (en) * | 2022-08-10 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Anti-slip pattern-shaped turbulence rib and turbine blade |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104712372A (en) * | 2014-12-29 | 2015-06-17 | 上海交通大学 | High-performance impact cooling system |
| CN104712372B (en) * | 2014-12-29 | 2016-03-09 | 上海交通大学 | A kind of high-performance impinging cooling system |
| CN105804873A (en) * | 2015-01-20 | 2016-07-27 | 通用电器技术有限公司 | Wall for hot gas channel in gas turbine |
| CN110192005A (en) * | 2017-01-18 | 2019-08-30 | 西门子股份公司 | Turbo-element |
| CN110242357A (en) * | 2018-03-09 | 2019-09-17 | 中国联合重型燃气轮机技术有限公司 | The blade of gas turbine |
| CN108387358A (en) * | 2018-05-07 | 2018-08-10 | 复旦大学 | A kind of wind tunnel experiment part and its wind tunnel system with interchangeability |
| EP3816407A1 (en) * | 2019-11-04 | 2021-05-05 | Raytheon Technologies Corporation | Impingement cooling with impingement cells on impinged surface |
| US11131199B2 (en) | 2019-11-04 | 2021-09-28 | Raytheon Technologies Corporation | Impingement cooling with impingement cells on impinged surface |
| CN112780353A (en) * | 2019-11-06 | 2021-05-11 | 曼恩能源方案有限公司 | Device for cooling components of a gas turbine/turbomachine by means of impingement cooling |
| EP3819470A1 (en) * | 2019-11-06 | 2021-05-12 | MAN Energy Solutions SE | Device for cooling a component of a gas turbine / flow engine with impingement cooling |
| US11280216B2 (en) | 2019-11-06 | 2022-03-22 | Man Energy Solutions Se | Device for cooling a component of a gas turbine/turbo machine by means of impingement cooling |
| CN113374536A (en) * | 2021-06-09 | 2021-09-10 | 中国航发湖南动力机械研究所 | Gas turbine guide vane |
| CN114439553A (en) * | 2022-03-04 | 2022-05-06 | 中国航发沈阳发动机研究所 | Low thermal stress turbine cooling guide vane |
| CN114961895A (en) * | 2022-06-16 | 2022-08-30 | 大连理工大学 | Turbine outer ring adopting double-helix cooling structure |
| CN115013075A (en) * | 2022-08-10 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Anti-slip pattern-shaped turbulence rib and turbine blade |
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Application publication date: 20130501 |