CN202900329U - Combustion turbine moving blade - Google Patents
Combustion turbine moving blade Download PDFInfo
- Publication number
- CN202900329U CN202900329U CN 201220644481 CN201220644481U CN202900329U CN 202900329 U CN202900329 U CN 202900329U CN 201220644481 CN201220644481 CN 201220644481 CN 201220644481 U CN201220644481 U CN 201220644481U CN 202900329 U CN202900329 U CN 202900329U
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- cooling circuit
- circuit part
- blade
- ribs
- turbulent
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Abstract
The utility model relates to a combustion turbine moving blade, in particular to a combustion turbine moving blade with a medium-low heat value. The combustion turbine moving blade aims to solve the problem of low cooling efficiency of the existing turbine blade. The combustion turbine moving blade is characterized in that a blade root, an intermediate body and a through-flow radial lower edge plate are arranged in sequence from bottom to top; a blade working part of the combustion turbine moving blade with the medium-low heat value is arranged on the through-flow radial lower edge plate; and the blade working part comprises a first cooling loop part, a second cooling loop part, an intermediate rib and a plurality of intermediate turbulence exciters, wherein the first cooling loop part and the second cooling loop part are arranged on the through-flow radial lower edge plate in sequence from left to right, an upward inclined hole is formed in the upper part of the intermediate rib which is arranged between the first cooling loop part and the second cooling loop part, and the plurality of intermediate turbulence exciters are arranged on the intermediate rib in sequence from top to bottom. The combustion turbine moving blade is used for a combustion turbine system with the medium-low heat value.
Description
Technical field
The utility model relates to a kind of turbine rotor vane, is specifically related to the combustion machine turbine rotor vane in a kind of middle lower calorific value heavy duty gas turbine system.
Background technique
Rising along with the gaseous combustion temperature in the present heavy duty gas turbine, turbine blade in the combustion gas meridional channel directly leaks in higher heat load environment cruelly, especially significantly increase at blade blade and top heat load, cause blade easily to produce oxidation and creep occurs damaging.Although the existing considerable progress of turbine material and technique faces the combustion gas turbine inlet temperature that day by day increases at present, under the condition that the temperature of blade and thermal stress level increase gradually, the low problem of cooling effectiveness has appearred in existing turbine blade.
The model utility content
The purpose of this utility model is the low problem of cooling effectiveness to have occurred in order to solve existing turbine blade.And then provide a kind of combustion machine turbine rotor vane.
The technical solution of the utility model is: a kind of middle lower calorific value combustion machine turbine rotor vane of high efficiency cooling comprises blade root, intermediate and through-flow radially inframarginal, intermediate is hollow intermediate, through-flow radially inframarginal is provided with a plurality of through flow holes, blade root, intermediate and through-flow radially inframarginal set gradually from the bottom to top, described middle lower calorific value combustion machine turbine rotor vane also comprises the blade working part, blade working partly is arranged on the through-flow radially inframarginal, blade working partly comprises the first cooling circuit part, the second cooling circuit part, the turbulent exciter of intermediate rib and a plurality of centre, the first cooling circuit part and the second cooling circuit part are successively set on the through-flow radially inframarginal from left to right, the top of intermediate rib has the hole that is tilted to, intermediate rib is arranged between the first cooling circuit part and the second cooling circuit part, the turbulent exciter in a plurality of centres from top to bottom is successively set in the first cooling circuit part and the second cooling circuit part, the blade air inlet side of the first cooling circuit part is provided with three discharged to the leading edge that the tilts air film hole of giving vent to anger, the blade of the second cooling circuit part side of giving vent to anger is provided with last person's edge air film hole of giving vent to anger, the first cooling circuit part and the second cooling circuit top partly is provided with a plurality of tops that link to each other with inner chamber spiral coil cooling tube road air film hole of giving vent to anger, described the first cooling circuit partly comprises many first ribs and a plurality of first turbulent exciter, many the first rib radial skews are arranged on the through-flow radially inframarginal, and composition spiral coil cooling tube road, and leave the gap between every adjacent two the first ribs, blade pressure side and suction side between every adjacent two the first ribs are provided with a plurality of first turbulent exciter from top to bottom successively, near being provided with successively a plurality of impact openings from top to bottom on the first outside rib, be provided with a plurality of tap holes with described near the first adjacent rib top of the first outside rib; Described the second cooling circuit partly comprises many second ribs and a plurality of second turbulent exciter, many the second rib radial skews are arranged on the through-flow radially inframarginal, and composition spiral coil cooling tube road, and leave the gap between adjacent two the second ribs, the a plurality of second turbulent exciter from top to bottom is successively set on two blade pressure sides and suction side between the second rib, second the second rib top near the intermediate rib place is provided with a plurality of pressure compensation openings, the side sidewall of giving vent to anger of the second cooling circuit part is provided with air collecting chamber, comprises a plurality of flow-disturbing spares and a plurality of projection nail in the air collecting chamber.
The utility model compared with prior art has following effect:
1. the utility model is in the straight passage of the snake pipe that many roots bar forms, blade pressure side and the suction side of rectangular channel are respectively equipped with turbulent exciter, effectively increased stream heat exchange efficiency in the blade, guaranteed that blade surface has preferably temperature field and less thermal stress gradient.
2. the first cooling circuit part of the present utility model is provided with whole row's impact opening, makes cooling fluid flow to blade inlet edge, is finally sprayed by the leading edge air film hole.Simultaneously, also increase tap hole and pressure compensation opening, improved the cooling fluid pressure of blade snake shape pipe end, effectively reduced the temperature at blade end place.
3. in the situation of the overall air conditioning quantity not increasing whole turbine system of the present utility model, by the adjustment of turbine blade structure, effectively reduce blade metallic surface temperature and thermal stress, the problem of having avoided blade easily to be burned.
Description of drawings
Fig. 1 is integral outer structural front view of the present utility model, and Fig. 2 is the axle side structure schematic diagram of Fig. 1, and Fig. 3 is the sectional view of the utility model blade working part.
Embodiment
Embodiment one: present embodiment is described in conjunction with Fig. 1-Fig. 3, the middle lower calorific value combustion machine turbine rotor vane of a kind of high efficiency cooling of present embodiment comprises blade root 1, intermediate 2 and through-flow radially inframarginal 3, intermediate 2 is hollow intermediate, through-flow radially inframarginal 3 is provided with a plurality of through flow holes, blade root 1, intermediate 2 and through-flow radially inframarginal 3 set gradually from the bottom to top, described middle lower calorific value combustion machine turbine rotor vane also comprises blade working part 4, blade working part 4 is arranged on the through-flow radially inframarginal 3, blade working part 4 comprises the first cooling circuit part 23, the second cooling circuit part 24, the turbulent exciter 11 in intermediate rib 6 and a plurality of centre, the first cooling circuit part 23 and the second cooling circuit part 24 are successively set on the through-flow radially inframarginal 3 from left to right, the top of intermediate rib 6 has the hole 18 that is tilted to, intermediate rib 6 is arranged between the first cooling circuit part 23 and the second cooling circuit part 24, the turbulent exciter 11 in a plurality of centres from top to bottom is successively set in the first cooling circuit part 23 and the second cooling circuit part 24, the blade air inlet side of the first cooling circuit part 23 is provided with three discharged to the leading edge that the tilts air film hole 19 of giving vent to anger, the blade of the second cooling circuit part 24 side of giving vent to anger is provided with last person's edge air film hole 20 of giving vent to anger, the top of the first cooling circuit part 23 and the second cooling circuit part 24 is provided with a plurality of tops that link to each other with inner chamber spiral coil cooling tube road air film hole 21 of giving vent to anger, described the first cooling circuit part 23 comprises many first ribs 7 and a plurality of first turbulent exciter 8, many the first rib 7 radial skews are arranged on the through-flow radially inframarginal 3, and composition spiral coil cooling tube road, and leave the gap between every adjacent two the first ribs 7, blade pressure side and suction side between every adjacent two the first ribs 7 are provided with a plurality of first turbulent exciter 8 from top to bottom successively, near being provided with successively a plurality of impact openings 9 from top to bottom on the first outside rib 7, be provided with a plurality of tap holes 10 with described near adjacent the first rib 7 tops of outside the first rib 7; Described the second cooling circuit part 24 comprises many second ribs 12 and a plurality of second turbulent exciter 13, many the second rib 12 radial skews are arranged on the through-flow radially inframarginal 3, and composition spiral coil cooling tube road, and leave the gap between adjacent two the second ribs 12, the a plurality of second turbulent exciter 13 from top to bottom is successively set on two blade pressure sides and suction side between the second rib 12, second the second rib 12 top near intermediate rib 6 places are provided with a plurality of pressure compensation openings 14, the side sidewall of giving vent to anger of the second cooling circuit part 24 is provided with air collecting chamber 15, comprises a plurality of flow-disturbing spares 16 and a plurality of projection nail 17 in the air collecting chamber.
The utility model is a hollow turbine blade in use; put into hot runner; pass into cold air in the blade; cold air is through the blade interior passage; gush out from blade surface, the cold air that gushes out is attached to blade surface, forms one deck air film; the protection blade is not corroded by high-temperature fuel gas, has also improved simultaneously the cooling effectiveness of turbine blade.
The cooling fluid of present embodiment enters blade working part 4 from the bottom of blade root 1, by hole blowing unit shunting body, finally forms cooled blade listrium outer surface by through-flow radially inframarginal 3 ejections when segment fluid flow is flowed through through-flow radially inframarginal 3 place.Most of cooling fluid passes through four inlet hole 5 air inlets of blade root 1 on the one hand, on the other hand by leading edge air film hole 19 air inlets of giving vent to anger, trailing edge air film hole 20 and the top air film hole 21 of giving vent to anger of giving vent to anger is given vent to anger, and has realized blade is carried out multi-faceted cooling, and cooling effectiveness is high.
Embodiment two: in conjunction with Fig. 2 and Fig. 3 present embodiment is described, the gap between every adjacent two first ribs 7 of present embodiment and the gap between adjacent two the second ribs 12 are the from the bottom to top gap of convergent.Good cooling results so is set.Other composition is identical with embodiment one with annexation.
Embodiment three: in conjunction with Fig. 2 and Fig. 3 present embodiment is described, the first turbulent exciter 8 of present embodiment, middle turbulent exciter 11 and the second turbulent exciter 13 are " people " font fin.So arrange, snake pipe can be regarded a rectangular channel pipeline with fillet as separately, near on the pressure side with the passage of suction side in, " people " font fin is set, effectively raise the surface film thermal conductance of blade pressure side and suction side.Other composition is identical with embodiment two with annexation.
Embodiment four: in conjunction with Fig. 2 and Fig. 3 present embodiment is described, the angle of " people " font fin of present embodiment is 110 °-130 °.So arrange, the surface film thermal conductance of blade pressure side and suction side is best, and other composition is identical with embodiment three with annexation.
Claims (4)
1. combustion machine turbine rotor vane, it comprises blade root (1), intermediate (2) and through-flow radially inframarginal (3), intermediate (2) is hollow intermediate, through-flow radially inframarginal (3) is provided with a plurality of through flow holes, blade root (1), intermediate (2) and through-flow radially inframarginal (3) set gradually from the bottom to top, it is characterized in that: described middle lower calorific value combustion machine turbine rotor vane also comprises blade working part (4), blade working part (4) is arranged on the through-flow radially inframarginal (3), blade working part (4) comprises the first cooling circuit part (23), the second cooling circuit part (24), the turbulent exciter of intermediate rib (6) and a plurality of centre (11), the first cooling circuit part (23) and the second cooling circuit part (24) are successively set on the through-flow radially inframarginal (3) from left to right, the top of intermediate rib (6) has the hole (18) that is tilted to, intermediate rib (6) is arranged between the first cooling circuit part (23) and the second cooling circuit part (24), the turbulent exciters in a plurality of centres (11) from top to bottom are successively set in the first cooling circuit part (23) and the second cooling circuit part (24), the blade air inlet side of the first cooling circuit part (23) is provided with three discharged to the leading edge that the tilts air film hole (19) of giving vent to anger, the blade of the second cooling circuit part (24) side of giving vent to anger is provided with last person's edge air film hole (20) of giving vent to anger, the first cooling circuit part (23) and the second cooling circuit partly top of (24) are provided with a plurality of tops that link to each other with inner chamber spiral coil cooling tube road air film hole (21) of giving vent to anger, described the first cooling circuit part (23) comprises many first ribs (7) and a plurality of first turbulent exciter (8), many the first ribs (7) radial skew is arranged on the through-flow radially inframarginal (3), and composition spiral coil cooling tube road, and leave the gap between every adjacent two the first ribs (7), blade pressure side and suction side between every adjacent two the first ribs (7) are provided with a plurality of first turbulent exciter (8) from top to bottom successively, near being provided with successively a plurality of impact openings (9) from top to bottom on outside the first rib (7), be provided with a plurality of tap holes (10) with described near adjacent the first rib (7) top of outside the first rib (7); Described the second cooling circuit part (24) comprises many second ribs (12) and a plurality of second turbulent exciter (13), many the second ribs (12) radial skew is arranged on the through-flow radially inframarginal (3), and composition spiral coil cooling tube road, and leave the gap between adjacent two the second ribs (12), the a plurality of second turbulent exciter (13) from top to bottom is successively set on the blade pressure side and suction side between two the second ribs (12), second the second rib (12) top of locating near intermediate rib (6) is provided with a plurality of pressure compensation openings (14), the side sidewall of giving vent to anger of the second cooling circuit part (24) is provided with air collecting chamber (15), comprises a plurality of flow-disturbing spares (16) and a plurality of projection nail (17) in the air collecting chamber.
2. a kind of combustion machine turbine rotor vane according to claim 1 is characterized in that: the gap between described every adjacent two the first ribs (7) and the gap between adjacent two the second ribs (12) are the from the bottom to top gap of convergent.
3. a kind of combustion machine turbine rotor vane according to claim 2, it is characterized in that: the described first turbulent exciter (8), middle turbulent exciter (11) and the second turbulent exciter (13) are " people " font fin.
4. a kind of combustion machine turbine rotor vane according to claim 3, it is characterized in that: the angle of described " people " font fin is 110 °-130 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220644481 CN202900329U (en) | 2012-11-29 | 2012-11-29 | Combustion turbine moving blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220644481 CN202900329U (en) | 2012-11-29 | 2012-11-29 | Combustion turbine moving blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202900329U true CN202900329U (en) | 2013-04-24 |
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ID=48121012
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220644481 Expired - Lifetime CN202900329U (en) | 2012-11-29 | 2012-11-29 | Combustion turbine moving blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202900329U (en) |
Cited By (2)
| 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 |
| CN107366555A (en) * | 2016-05-12 | 2017-11-21 | 通用电气公司 | Blade and turbine rotor blade |
-
2012
- 2012-11-29 CN CN 201220644481 patent/CN202900329U/en not_active Expired - Lifetime
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 |
| 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 |
| CN107366555A (en) * | 2016-05-12 | 2017-11-21 | 通用电气公司 | Blade and turbine rotor blade |
| CN107366555B (en) * | 2016-05-12 | 2022-03-08 | 通用电气公司 | Blade and turbine rotor blade |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130424 |