CN102996187A - Combustion engine turbine first-level guide blade lower end wall cooling system - Google Patents
Combustion engine turbine first-level guide blade lower end wall cooling system Download PDFInfo
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- CN102996187A CN102996187A CN2012105205973A CN201210520597A CN102996187A CN 102996187 A CN102996187 A CN 102996187A CN 2012105205973 A CN2012105205973 A CN 2012105205973A CN 201210520597 A CN201210520597 A CN 201210520597A CN 102996187 A CN102996187 A CN 102996187A
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- end wall
- chopped
- cooling
- trailing edge
- head stator
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Abstract
The invention relates to a combustion engine turbine first-level guide blade lower end wall cooling system, relates to a cooling system of a combustion engine turbine first-level guide blade, and solves the problem that the temperatures of the combustion engine turbine first-level guide blade and the lower end wall metal surface of the first-level guide blade are too high so as to cause oxygenation and creep damage. The combustion engine turbine first-level guide blade lower end wall cooling system also comprises a shunting screen, wherein the upper surface of the front edge side of a first-level guide blade lower end wall is processed with a cooling groove the shape of which is same with that of the shunting screen, the shunting screen is arranged right below the cooling groove so as to cover the cooling groove, and the shunting screen is fixedly connected with the first-level guide blade lower end wall; the shunting screen and the bottom surface of the cooling groove are both provided with through holes the shapes of which are same with that of a front sleeve cross section, and the position of the through hole of the shunting screen is over against the position of the through hole in the bottom surface of the cooling groove; and a front sleeve passes through the through hole in the shunting screen and the through hole in the cooling groove so as to be arranged in a guide blade, and the upper end of the front sleeve is fixedly connected with the shunting screen. The combustion engine turbine first-level guide blade lower end wall cooling system, provided by the invention, is widely applied to cooling the lower end wall of the combustion engine turbine first-level guide blade.
Description
Technical field
The present invention relates to a kind of cooling system that fires machine turbine chopped-off head stator.
Background technique
According to China energy industry structure as can be known, Natural Gas Resources in China is less, and coal resource is abundant.Abundant by the medium and low heat value fuel that coal refines, therefore it is particularly important to improve the heavy combustion engine performance that is applicable to medium and low heat value fuel, present middle lower calorific value heavy duty gas turbine turbine guide vane is directly exposed in the higher heat load environment, especially blade blade and up and down end wall cause blade to produce oxidation and creep occurs damaging easily under the long-term high heat load environment.
Summary of the invention
The problem that the present invention damages for the excess Temperature generation oxidation that solves combustion machine turbine chopped-off head stator and lower end wall metal surface and creep, thus a kind of combustion machine turbine chopped-off head stator lower end wall cooling system is provided.
Combustion machine turbine chopped-off head stator lower end wall cooling system, it comprises chopped-off head stator lower end wall, stator and front sleeve, described stator is fixed between chopped-off head stator upper end wall and the chopped-off head stator lower end wall, be processed with rib on the chopped-off head stator lower end wall, chopped-off head stator lower end wall is divided into front edge side and trailing edge side by rib, and described cooling system also comprises the shunting screen;
Described chopped-off head stator lower end wall front edge side lower surface is processed with the cooling bath consistent with shunting the screen shape, and the shunting screen covers cooling bath under being arranged on cooling bath, and affixed with chopped-off head stator lower end wall (1);
All be processed with the through hole consistent with the front sleeve shape of cross section on the bottom surface of described shunting screen and cooling bath, and the through hole on the shunting screen and the lead to the hole site on the cooling bath bottom surface over against, through hole and the through hole on the cooling bath that front sleeve passes on the shunting screen are arranged in the stator, and the upper end of front sleeve is affixed with the through hole on the shunting screen.
The present invention adopts combustion machine turbine chopped-off head stator lower end wall cooling system to make cold air obtain comprehensive utilization, the temperature of combustion machine turbine chopped-off head stator and lower end wall metal blade is effectively reduced, can reduce temperature 500-600k, effectively avoid producing the high heat load environment and then reduced the stator blade producing the problem of oxidation and creep damage.
Description of drawings
Fig. 1 is the worm's eye view of combustion machine turbine chopped-off head stator lower end wall cooling system;
Fig. 2 is the worm's eye view of the lower end wall structure of combustion machine turbine chopped-off head stator lower end wall cooling system;
Fig. 3 is the rear view of Fig. 2;
Fig. 4 is the front view of Fig. 2.
Embodiment
Embodiment one, in conjunction with this embodiment of Fig. 1-4 explanation.Combustion machine turbine chopped-off head stator lower end wall cooling system, it comprises chopped-off head stator lower end wall 1, stator 4 and front sleeve 3, described stator 4 is fixed between chopped-off head stator upper end wall 5 and the chopped-off head stator lower end wall 1, be processed with rib 7 on the chopped-off head stator lower end wall 1, chopped-off head stator lower end wall 1 is divided into front edge side and trailing edge side by rib, and described cooling system also comprises shunting screen 2;
Described chopped-off head stator lower end wall 1 front edge side lower surface is processed with the cooling bath 6 consistent with shunting screen 2 shapes, and shunting screen 2 covers cooling bath 6 under being arranged on cooling bath 6, and affixed with chopped-off head stator lower end wall 1;
All be processed with the through hole consistent with the front sleeve shape of cross section on the bottom surface of described shunting screen 2 and cooling bath 6, and the through hole on the shunting screen 2 and the lead to the hole site on cooling bath 6 bottom surfaces over against, through hole and the through hole on the cooling bath 6 that front sleeve 3 passes on the shunting screen 2 are arranged in the stator 4, and the lower end of front sleeve 3 is affixed with the through hole on the shunting screen 2; Rear sleeve and chopped-off head stator upper end wall 5 are affixed.
The air inlet side of described stator 4 is the front edge side of chopped-off head stator lower end wall 1, and the side of giving vent to anger of stator 4 is the trailing edge side of chopped-off head stator lower end wall 1.
What embodiment two, this embodiment and embodiment one were different is that described shunting screen 2 is provided with several impact openings 8, and described several impact openings 8 are distributed in the axis projection region exterior of stator on shunting screen 2.Other composition is identical with embodiment one with Placement.
Described impact opening 8 distributes along shunting screen 2 leading edges to trailing edge direction, is scattered in 13 row; The first row to the six every trade spacings equate that hole pitch equates in every row; The the 7th to the 13 every trade spacing equates that hole pitch equates in every row; The number of described impact opening 8 is 192-212, and the aperture is between the 1.2-1.5mm.
What embodiment three, this embodiment and embodiment one or embodiment two were different is that described cooling bath 6 bottom surfaces are provided with several stator leading edge air film holes 9, described several stator leading edge air film holes 9 evenly distribute along stator 4 leading edges, and the outgassing direction of several stator leading edge air film holes 9 all is positioned on the leading edge of stator 4 and chopped-off head stator lower end wall 1 joint.Other composition is identical with embodiment one with Placement.
The number of described stator leading edge air film hole 9 is 10-14, and the aperture is 1.2-1.5mm.
What embodiment four, this embodiment and embodiment one were different is that described cooling bath 6 bottom surfaces are provided with several cooling air fenestras 10.Other composition is identical with embodiment one with Placement.
Described cooling air fenestra 1 distributes from turbine chopped-off head stator lower end wall 1 leading edge to the trailing edge direction, is scattered in eight row; The line space of the first row and the second row is for rotating in a circumferential direction 0.365 °, and the angle in hole is identical; The third line and fourth line hole pitch are for rotating in a circumferential direction 0.3 °, and the angle in hole is identical, and the circumferential spacing in fifth line hole is 0.52 °.
Embodiment five, this embodiment and embodiment one, embodiment two or embodiment four are different is that the intrados of described chopped-off head stator lower end wall 1 is provided with several inner arc side openings 11 between cooling bath 6 lower surfaces.Other composition is identical with embodiment one with Placement.
The number of described inner arc side opening 11 is 4-6, and the aperture is 1.5-2mm.
What embodiment six, this embodiment and embodiment one were different is that described front sleeve is by being provided with several back of the body arc side openings 12 between hole 14 internal surfaces and chopped-off head stator lower end wall 1 back of the body arc side external surface.Other composition is identical with embodiment one with Placement.
What embodiment seven, this embodiment and embodiment one or embodiment six were different is also to be processed with the through hole consistent with rear sleeve-shaped on the described cooling bath 6; Be provided with several back arc side openings 13 between described through-hole inner surface and chopped-off head stator lower end wall 1 back of the body arc side external surface.Other composition is identical with embodiment one with Placement.
What embodiment eight, this embodiment and embodiment one were different is that described cooling system also comprises cover plate 14;
Described chopped-off head stator lower end wall 1 trailing edge side upper surface is processed with the trailing edge cooling slot 16 consistent with cover plate 15 shapes, and cover plate 15 covers trailing edge cooling slot 16 under being arranged on trailing edge cooling slot 16, and affixed with chopped-off head stator lower end wall 1.Other composition is identical with embodiment one with Placement.
Embodiment nine, this embodiment and embodiment one and embodiment eight are different is to be provided with several the first trailing edge Cooling Holes 17 between the leading edge face of the inner side surface of described trailing edge cooling slot 16 and rib, be provided with several the second trailing edge Cooling Holes 18 between the lower surface of the inner side surface of trailing edge cooling slot 16 and chopped-off head stator lower end wall 1, trailing edge cooling slot 16 trailing edge sidewalls are provided with several the 3rd trailing edge Cooling Holes 19.Other composition is identical with embodiment eight with embodiment one with Placement.
Embodiment ten, this embodiment and embodiment eight are different is that described cooling system also comprises and is provided with the trailing edge striking plate 20 that several impact plate holes;
Described trailing edge striking plate 20 and cover plate 15, trailing edge cooling slot are provided with the space between 16 bottom surfaces, and trailing edge striking plate 20 upper ends and cover plate 15 are affixed, and lower end and trailing edge cooling slot 16 bottom surfaces are affixed.Other composition is identical with embodiment eight with Placement.
The present invention adopts combustion machine turbine chopped-off head stator lower end wall cooling system, chopped-off head stator lower end wall 1 is cooled off, avoided in the traditional design problem of, chopped-off head stator upper end wall 1 single for combustion machine turbine chopped-off head stator upper end wall cooling system form and the stator easy ablation in 4 blade places and structural failure.
Claims (10)
1. fire machine turbine chopped-off head stator lower end wall cooling system, it comprises chopped-off head stator lower end wall (1), stator (4) and front sleeve (3), described stator (4) is fixed between chopped-off head stator upper end wall (5) and the chopped-off head stator lower end wall (1), be processed with rib (7) on the chopped-off head stator lower end wall (1), chopped-off head stator lower end wall (1) is divided into front edge side and trailing edge side by rib (7), it is characterized in that described cooling system also comprises shunting screen (2);
Described chopped-off head stator lower end wall (1) front edge side lower surface is processed with the cooling bath (6) consistent with shunting screen (2) shape, and shunting screen (2) covers cooling bath (6) under being arranged on cooling bath (6), and affixed with chopped-off head stator lower end wall (1);
All be processed with the through hole consistent with the front sleeve shape of cross section on the bottom surface of described shunting screen (2) and cooling bath (6), and the through hole on the shunting screen (2) and the lead to the hole site on cooling bath (6) bottom surface over against, through hole and the through hole on the cooling bath (6) that front sleeve (3) passes on the shunting screen (2) are arranged in the stator (4), and the lower end of front sleeve (3) is affixed with the through hole on the shunting screen (2).
2. combustion machine turbine chopped-off head stator lower end wall cooling system according to claim 1, it is characterized in that described shunting screen (2) is provided with several impact openings (8), described several impact openings (8) are distributed in the axis projection region exterior of stator on shunting screen (2).
3. combustion machine turbine chopped-off head stator lower end wall cooling system according to claim 1 and 2, it is characterized in that described cooling bath (6) bottom surface is provided with several stator leading edge air film holes (9), described several stator leading edge air film holes (9) evenly distribute along stator (4) leading edge, and the outgassing direction of several stator leading edge air film holes (9) all is positioned at the leading edge of stator (4) and chopped-off head stator lower end wall (1) joint.
4. combustion machine turbine chopped-off head stator lower end wall cooling system according to claim 1 is characterized in that described cooling bath (6) bottom surface is provided with several cooling air fenestras (10).
5. according to claim 1,2 or 4 described combustion machine turbine chopped-off head stator lower end wall cooling systems, it is characterized in that the intrados of described chopped-off head stator lower end wall (1) is provided with several inner arc side openings (11) between cooling bath (6) upper surface.
6. combustion machine turbine chopped-off head stator lower end wall cooling system according to claim 1 is characterized in that described front sleeve is by being provided with several back of the body arc side openings (12) between hole (14) internal surface and chopped-off head stator lower end wall (1) back of the body arc side external surface.
7. according to claim 1 or 6 described combustion machine turbine chopped-off head stator lower end wall cooling systems, it is characterized in that also being processed with on the described cooling bath (6) through hole consistent with rear sleeve-shaped; Be provided with several back arc side openings (13) between described through-hole inner surface and chopped-off head stator lower end wall (1) back of the body arc side external surface.
8. combustion machine turbine chopped-off head stator lower end wall cooling system according to claim 1 is characterized in that described cooling system also comprises cover plate (15);
Described chopped-off head stator lower end wall (1) trailing edge side lower surface is processed with the trailing edge cooling slot (16) consistent with cover plate (15) shape, cover plate (15) covers trailing edge cooling slot (16) under being arranged on trailing edge cooling slot (16), and affixed with chopped-off head stator lower end wall (1).
9. combustion machine turbine chopped-off head stator lower end wall cooling system according to claim 8, it is characterized in that being provided with several the first trailing edge Cooling Holes (17) between the leading edge face of the inner side surface of described trailing edge cooling slot (16) and rib, be provided with several the second trailing edge Cooling Holes (18) between the lower surface of the inner side surface of trailing edge cooling slot (16) and chopped-off head stator lower end wall (1), trailing edge cooling slot (16) trailing edge sidewall is provided with several the 3rd trailing edge Cooling Holes (19).
10. combustion machine turbine chopped-off head stator lower end wall cooling system according to claim 8 is characterized in that described cooling system also comprises the trailing edge striking plate (20) that is provided with several impact plate holes;
Described trailing edge striking plate (20) and cover plate (15), trailing edge cooling slot (16) are provided with the space between the bottom surface, and trailing edge striking plate (20) upper end is affixed with cover plate (15), and lower end and trailing edge cooling slot (16) bottom surface is affixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105205973A CN102996187A (en) | 2012-12-06 | 2012-12-06 | Combustion engine turbine first-level guide blade lower end wall cooling system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105205973A CN102996187A (en) | 2012-12-06 | 2012-12-06 | Combustion engine turbine first-level guide blade lower end wall cooling system |
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| CN102996187A true CN102996187A (en) | 2013-03-27 |
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| CN2012105205973A Pending CN102996187A (en) | 2012-12-06 | 2012-12-06 | Combustion engine turbine first-level guide blade lower end wall cooling system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104632293A (en) * | 2013-11-06 | 2015-05-20 | 三菱日立电力系统株式会社 | Gas turbine airfoil |
| CN109424367A (en) * | 2017-08-31 | 2019-03-05 | 中国航发商用航空发动机有限责任公司 | It is suitable for the cooling structure of the high-pressure turbine of gas turbine |
| CN109551068A (en) * | 2018-12-17 | 2019-04-02 | 中国航发沈阳发动机研究所 | A kind of rotor blade type face dustpan pore structure processing method and dustpan pore structure |
| CN113217113A (en) * | 2021-06-21 | 2021-08-06 | 中国航发沈阳发动机研究所 | Compact type edge plate structure of turbine cooling guide blade and guider with compact type edge plate structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3628880A (en) * | 1969-12-01 | 1971-12-21 | Gen Electric | Vane assembly and temperature control arrangement |
| US6382906B1 (en) * | 2000-06-16 | 2002-05-07 | General Electric Company | Floating spoolie cup impingement baffle |
| CN101328814A (en) * | 2007-06-20 | 2008-12-24 | 通用电气公司 | Reciprocal cooled turbine nozzle |
| CN102200034A (en) * | 2010-03-08 | 2011-09-28 | 通用电气公司 | Preferential cooling of gas turbine nozzles |
| CN202991151U (en) * | 2012-12-06 | 2013-06-12 | 哈尔滨汽轮机厂有限责任公司 | Cooling system for lower end wall of first stage guide vane of gas turbine |
-
2012
- 2012-12-06 CN CN2012105205973A patent/CN102996187A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3628880A (en) * | 1969-12-01 | 1971-12-21 | Gen Electric | Vane assembly and temperature control arrangement |
| US6382906B1 (en) * | 2000-06-16 | 2002-05-07 | General Electric Company | Floating spoolie cup impingement baffle |
| CN101328814A (en) * | 2007-06-20 | 2008-12-24 | 通用电气公司 | Reciprocal cooled turbine nozzle |
| CN102200034A (en) * | 2010-03-08 | 2011-09-28 | 通用电气公司 | Preferential cooling of gas turbine nozzles |
| CN202991151U (en) * | 2012-12-06 | 2013-06-12 | 哈尔滨汽轮机厂有限责任公司 | Cooling system for lower end wall of first stage guide vane of gas turbine |
Non-Patent Citations (1)
| Title |
|---|
| 辛亚楠: "燃气涡轮复合冷却结构改进设计研究", 《中国优秀硕士学位论文全文数据库工程科技II辑》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104632293A (en) * | 2013-11-06 | 2015-05-20 | 三菱日立电力系统株式会社 | Gas turbine airfoil |
| CN109424367A (en) * | 2017-08-31 | 2019-03-05 | 中国航发商用航空发动机有限责任公司 | It is suitable for the cooling structure of the high-pressure turbine of gas turbine |
| CN109424367B (en) * | 2017-08-31 | 2020-12-15 | 中国航发商用航空发动机有限责任公司 | Cooling structure of high-pressure turbine suitable for gas turbine |
| CN109551068A (en) * | 2018-12-17 | 2019-04-02 | 中国航发沈阳发动机研究所 | A kind of rotor blade type face dustpan pore structure processing method and dustpan pore structure |
| CN113217113A (en) * | 2021-06-21 | 2021-08-06 | 中国航发沈阳发动机研究所 | Compact type edge plate structure of turbine cooling guide blade and guider with compact type edge plate structure |
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Application publication date: 20130327 |