CN204060802U - A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type - Google Patents
A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type Download PDFInfo
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- CN204060802U CN204060802U CN201420564781.2U CN201420564781U CN204060802U CN 204060802 U CN204060802 U CN 204060802U CN 201420564781 U CN201420564781 U CN 201420564781U CN 204060802 U CN204060802 U CN 204060802U
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Abstract
Be applicable to a turbine first order moving vane for low-calorific-value gas turbine in heavy type, the utility model is that in the current heavy type of solution, lower calorific value combustion engine turbine first order movable vane aerodynamic efficiency is low, working life is short, affect the problem of turbine safe operation.The molded line of blade working part is variable cross section twisted blade, blade working part near root to the geometric data in the cross section at top: the section A-A being positioned at root is 0 ~ 190.88mm to the depth of section of cross section G-G, axial width is 99.406 ~ 126.307mm, chord length is 126.029 ~ 134.572mm, flow inlet angle is 27.392 ° ~ 53.649 °, established angle is 52.625 ° ~ 72.415 °, and molded line maximum ga(u)ge is 22.633 ~ 39.910mm, and trailing edge thickness is 5.236 ~ 5.739mm.The turbine of the utility model low-calorific-value gas turbine in heavy type.
Description
Technical field
The utility model relates to a kind of Gas Turbine first order moving vane, is specifically related to a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type.
Background technique
In recent years, efficient gas turbine improves combustor exit temperature gradually and makes great efforts to improve the cooling of various turbine component.But, due to the impact of blade physical form become by multiple cross sections blade profile molded line envelopes, such that the turbine first order moving vane aerodynamic efficiency of low-calorific-value gas turbine in heavy type is low, working life is short, affect turbine safe operation.
Model utility content
The utility model is that lower calorific value combustion engine turbine first order movable vane aerodynamic efficiency is low, working life is short, affect the problem of turbine safe operation in order to solve in current heavy type, and then provides a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type.
The utility model is solve the problems of the technologies described above the technological scheme taked to be:
A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type of the present utility model comprises blade working part and petiole, blade working part and petiole are cast as one from top to bottom, the molded line of blade working part is variable cross section twisted blade, different along blade height sectional shape, sectional area is increased to top gradually by root, relative torsion is had between adjacent two sections, blade working part near root to the geometric data in the cross section at top: the section A-A being positioned at root is 0 ~ 190.88mm to the depth of section of cross section G-G, axial width is 99.406 ~ 126.307mm, chord length is 126.029 ~ 134.572mm, flow inlet angle is 27.392 ° ~ 53.649 °, established angle is 52.625 ° ~ 72.415 °, molded line maximum ga(u)ge is 22.633 ~ 39.910mm, trailing edge thickness is 5.236 ~ 5.739mm, the total height of blade working part is 190.88mm.
The utility model has following beneficial effect: the utility model is in the full three dimensional design calculating this first-level guide blade with one dimension, accurate three-dimensional, full three-dimensional pneumatic, thermodynamic analysis, calculation accuracy is high, Security of the present utility model and high efficiency are organically combined, ensure energy safe and highly efficient operation under variable working condition, improve the aerodynamic efficiency of blade, the aerodynamic efficiency of blade improves 1.9% ~ 2.2%, extends blade working life,, working life extends 1.4 to 1.8 times.
Accompanying drawing explanation
Fig. 1 is a kind of plan view being applicable to the turbine first order moving vane of low-calorific-value gas turbine in heavy type of the present utility model; Fig. 2 is the left view of Fig. 1; Fig. 3 is the superimposed schematic diagram of vane type line part each cross section tomography; Fig. 4 is the schematic diagram of blade working part display blade profile parameters Q, b, α, β y, T, δ; Fig. 5 is the K partial enlarged drawing of Fig. 4, and Fig. 6 is the N partial enlarged drawing of Fig. 4.
Embodiment
Embodiment one: composition graphs 1 ~ Fig. 6 illustrates present embodiment, present embodiment comprises blade working part (1) and petiole 2, blade working part 1 and petiole 2 are cast as one from top to bottom, the molded line of blade working part 1 is variable cross section twisted blade, different along blade height sectional shape, sectional area is increased to top gradually by root, relative torsion is had between adjacent two sections, blade working part 1 near root to the geometric data in the cross section at top: the section A-A being positioned at root is 0 ~ 190.88mm to the depth of section H of cross section G-G, axial width Q is 99.406 ~ 126.307mm, chord length b is 126.029 ~ 134.572mm, flow inlet angle α is 27.392 ° ~ 53.649 °, established angle β y is 52.625 ° ~ 72.415 °, molded line maximum ga(u)ge T is 22.633 ~ 39.910mm, trailing edge thickness δ is 5.236 ~ 5.739mm, the total height L of blade working part 1 is 190.88mm.Such design can ensure the best stress of blade, and avoids occurring peak stress in each tooth root portion of blade root and supporting plane.
Embodiment two: composition graphs 1 ~ Fig. 6 illustrates present embodiment, the depth of section of blade working part 1 section A-A of present embodiment is 0mm, and the axial width Q of the blade working part 1 corresponding to this position is 126.307mm, chord length b is 134.572mm, flow inlet angle α is 27.392 °, established angle β y is 72.415 °, molded line maximum ga(u)ge T is 39.910mm, trailing edge thickness δ is 5.532mm.Adopt said structure parameter, while ensureing that the contour structure size of blade meets design requirement, blade also can be made easily to assemble.Other composition and annexation identical with embodiment one.
Embodiment three: composition graphs 1 ~ Fig. 6 illustrates present embodiment, the depth of section of blade working part 1 section B-B of present embodiment is 30mm, and the axial width Q of the blade working part 1 corresponding to this position is 121.968mm, chord length b is 132.586mm, flow inlet angle α is 30.121 °, established angle β y is 69.032 °, molded line maximum ga(u)ge T is 37.598mm, trailing edge thickness δ is 5.739mm.Adopt said structure parameter, while ensureing that the contour structure size of blade meets design requirement, blade also can be made easily to assemble.Other composition and annexation identical with embodiment one.
Embodiment four: composition graphs 1 ~ Fig. 6 illustrates present embodiment, the depth of section of the blade working part 1 cross section C-C of present embodiment is 60mm, and the axial width Q of the blade working part 1 corresponding to this position is 117.788mm, chord length b is 130.622mm, flow inlet angle α is 32.927 °, established angle β y is 65.991 °, molded line maximum ga(u)ge T is 34.220mm, trailing edge thickness δ is 5.658mm.Adopt said structure parameter, while ensureing that the contour structure size of blade meets design requirement, blade also can be made easily to assemble.Other composition and annexation identical with embodiment one.
Embodiment five: composition graphs 1 ~ Fig. 6 illustrates present embodiment, the depth of section of the blade working part 1 cross section D-D of present embodiment is 90mm, and the axial width Q of the blade working part 1 corresponding to this position is 113.708mm, chord length b is 128.954mm, flow inlet angle α is 39.320 °, established angle β y is 63.100 °, molded line maximum ga(u)ge T is 30.735mm, trailing edge thickness δ is 5.509mm.Adopt said structure parameter, while ensureing that the contour structure size of blade meets design requirement, blade also can be made easily to assemble.Other composition and annexation identical with embodiment one.
Embodiment six: composition graphs 1 ~ Fig. 6 illustrates present embodiment, the depth of section of the blade working part 1 cross section E-E of present embodiment is 125mm, and the axial width Q of the blade working part 1 corresponding to this position is 108.878mm, chord length b is 127.570mm, flow inlet angle α is 48.464 °, established angle β y is 59.539 °, molded line maximum ga(u)ge T is 27.511mm, trailing edge thickness δ is 5.530mm.Adopt said structure parameter, while ensureing that the contour structure size of blade meets design requirement, blade also can be made easily to assemble.Other composition and annexation identical with embodiment one.
Embodiment seven: composition graphs 1 ~ Fig. 6 illustrates present embodiment, the depth of section of the blade working part 1 cross section F-F of present embodiment is 160mm, and the axial width Q of the blade working part 1 corresponding to this position is 103.930mm, chord length b is 126.647mm, flow inlet angle α is 53.242 °, established angle β y is 55.820 °, molded line maximum ga(u)ge T is 24.833mm, trailing edge thickness δ is 5.622mm.Adopt said structure parameter, while ensureing that the contour structure size of blade meets design requirement, blade also can be made easily to assemble.Other composition and annexation identical with embodiment one.
Embodiment eight: composition graphs 1 ~ Fig. 6 illustrates present embodiment, the depth of section of the blade working part 1 cross section G-G of present embodiment is 190.88mm, and the axial width Q of the blade working part 1 corresponding to this position is 99.406mm, chord length b is 126.029mm, flow inlet angle α is 53.649 °, established angle β y is 52.625 °, molded line maximum ga(u)ge T is 22.633mm, trailing edge thickness δ is 5.236mm.Adopt said structure parameter, while ensureing that the contour structure size of blade meets design requirement, blade also can be made easily to assemble.Other composition and annexation identical with embodiment one.
Claims (8)
1. one kind is applicable to the turbine first order moving vane of low-calorific-value gas turbine in heavy type, described moving vane comprises blade working part (1) and petiole (2), blade working part (1) and petiole (2) are cast as one from top to bottom, the molded line of blade working part (1) is variable cross section twisted blade, different along blade height sectional shape, sectional area is increased to top gradually by root, relative torsion is had between adjacent two sections, it is characterized in that: blade working part (1) near root to the geometric data in the cross section at top: the section A-A being positioned at root is 0 ~ 190.88mm to the depth of section (H) of cross section G-G, axial width (Q) is 99.406 ~ 126.307mm, chord length (b) is 126.029 ~ 134.572mm, flow inlet angle (α) is 27.392 ° ~ 53.649 °, established angle (β y) is 52.625 ° ~ 72.415 °, molded line maximum ga(u)ge (T) is 22.633 ~ 39.910mm, trailing edge thickness (δ) is 5.236 ~ 5.739mm, the total height (L) of blade working part (1) is 190.88mm.
2. a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type according to claim 1, it is characterized in that: the depth of section of blade working part (1) section A-A is 0mm, the axial width (Q) of the blade working part (1) corresponding to this position is 126.307mm, chord length (b) is 134.572mm, flow inlet angle (α) is 27.392 °, established angle (β y) is 72.415 °, molded line maximum ga(u)ge (T) is 39.910mm, trailing edge thickness (δ) is 5.532mm.
3. a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type according to claim 1, it is characterized in that: the depth of section of blade working part (1) section B-B is 30mm, the axial width (Q) of the blade working part (1) corresponding to this position is 121.968mm, chord length (b) is 132.586mm, flow inlet angle (α) is 30.121 °, established angle (β y) is 69.032 °, molded line maximum ga(u)ge (T) is 37.598mm, trailing edge thickness (δ) is 5.739mm.
4. a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type according to claim 1, it is characterized in that: the depth of section of blade working part (1) cross section C-C is 60mm, the axial width (Q) of the blade working part (1) corresponding to this position is 117.788mm, chord length (b) is 130.622mm, flow inlet angle (α) is 32.927 °, established angle (β y) is 65.991 °, molded line maximum ga(u)ge (T) is 34.220mm, trailing edge thickness (δ) is 5.658mm.
5. a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type according to claim 1, it is characterized in that: the depth of section of blade working part (1) cross section D-D is 90mm, the axial width (Q) of the blade working part (1) corresponding to this position is 113.708mm, chord length (b) is 128.954mm, flow inlet angle (α) is 39.320 °, established angle (β y) is 63.100 °, molded line maximum ga(u)ge (T) is 30.735mm, trailing edge thickness (δ) is 5.509mm.
6. a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type according to claim 1, it is characterized in that: the depth of section of blade working part (1) cross section E-E is 125mm, the axial width (Q) of the blade working part (1) corresponding to this position is 108.878mm, chord length (b) is 127.570mm, flow inlet angle (α) is 48.464 °, established angle (β y) is 59.539 °, molded line maximum ga(u)ge (T) is 27.511mm, trailing edge thickness (δ) is 5.530mm.
7. a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type according to claim 1, it is characterized in that: the depth of section of blade working part (1) cross section F-F is 160mm, the axial width (Q) of the blade working part (1) corresponding to this position is 103.930mm, chord length (b) is 126.647mm, flow inlet angle (α) is 53.242 °, established angle (β y) is 55.820 °, molded line maximum ga(u)ge (T) is 24.833mm, trailing edge thickness (δ) is 5.622mm.
8. a kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type according to claim 7, it is characterized in that: the depth of section of blade working part (1) cross section G-G is 190.88mm, the axial width (Q) of the blade working part (1) corresponding to this position is 99.406mm, chord length (b) is 126.029mm, flow inlet angle (α) is 53.649 °, established angle (β y) is 52.625 °, molded line maximum ga(u)ge (T) is 22.633mm, trailing edge thickness (δ) is 5.236mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420564781.2U CN204060802U (en) | 2014-09-28 | 2014-09-28 | A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420564781.2U CN204060802U (en) | 2014-09-28 | 2014-09-28 | A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type |
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| CN204060802U true CN204060802U (en) | 2014-12-31 |
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| CN201420564781.2U Withdrawn - After Issue CN204060802U (en) | 2014-09-28 | 2014-09-28 | A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104265375A (en) * | 2014-09-28 | 2015-01-07 | 哈尔滨汽轮机厂有限责任公司 | Turbine first-stage moving blade applicable to heavy low and medium calorific value gas turbine |
-
2014
- 2014-09-28 CN CN201420564781.2U patent/CN204060802U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104265375A (en) * | 2014-09-28 | 2015-01-07 | 哈尔滨汽轮机厂有限责任公司 | Turbine first-stage moving blade applicable to heavy low and medium calorific value gas turbine |
| CN104265375B (en) * | 2014-09-28 | 2016-03-23 | 哈尔滨汽轮机厂有限责任公司 | A kind of turbine first order moving vane being applicable to low-calorific-value gas turbine in heavy type |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141231 Effective date of abandoning: 20160323 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |