CN204060805U - A kind of turbine third level guide vane for lower calorific value combustion engine in heavy type - Google Patents
A kind of turbine third level guide vane for lower calorific value combustion engine in heavy type Download PDFInfo
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- CN204060805U CN204060805U CN201420573954.7U CN201420573954U CN204060805U CN 204060805 U CN204060805 U CN 204060805U CN 201420573954 U CN201420573954 U CN 201420573954U CN 204060805 U CN204060805 U CN 204060805U
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Abstract
For a turbine third level guide vane for lower calorific value combustion engine in heavy type, it relates to a kind of turbine guide vane sheet for lower calorific value combustion engine in heavy type.To solve in current heavy type, lower calorific value combustion engine turbine third level guide vane aerodynamic efficiency is low, working life is short, affect the problem of turbine safe operation, blade working part, upper end wall and lower end wall are cast as one, sectional area is increased to top gradually by root, has relative torsion between adjacent two sections; Blade working part near root to the geometric data in the cross section at top: the depth of section h of section A-A, section B-B, cross section C-C, cross section D-D and cross section E-E is 0 ~ 501.64mm, axial width Q is 161.879 ~ 280.805mm, chord length b is 198.440 ~ 329.378mm, flow inlet angle α is 65.491 ° ~ 88.966 °, established angle β y is 56.414 ° ~ 59.611 °, molded line maximum ga(u)ge T is 46.563 ~ 60.059mm, trailing edge thickness δ is 4.000mm, and the total height L of blade working part is 501.64mm.The utility model is used for the turbine of lower calorific value combustion engine in heavy type.
Description
Technical field
The utility model relates to a kind of turbine guide vane sheet for lower calorific value combustion engine in heavy type.
Background technique
In recent years, the raising gradually that efficient gas turbine improves combustor exit temperature and turbine power gradually makes turbine blade height improve gradually, cause the impact of the blade physical form become by multiple cross sections blade profile molded line envelope, make the turbine third level hollow guide vane aerodynamic efficiency of low-calorific-value gas turbine in heavy type low, working life is short, affects turbine safe operation.
Model utility content
The purpose of this utility model is to provide a kind of turbine third level guide vane being applied to lower calorific value combustion engine in heavy type, and to solve in current heavy type, lower calorific value combustion engine turbine third level guide vane aerodynamic efficiency is low, working life is short, affect the problem of turbine safe operation.
The utility model is the technological scheme taked that solves the problem: described blade of the present utility model comprises blade working part, upper end wall and lower end wall, blade working part, upper end wall and lower end wall are cast as one, the molded line of blade working part is variable cross section twisted blade molded line, different along blade height sectional shape, sectional area is increased to top gradually by root, has relative torsion between adjacent two sections; Blade working part near root to the geometric data in the cross section at top: the depth of section h of section A-A, section B-B, cross section C-C, cross section D-D and cross section E-E is 0 ~ 501.64mm, axial width Q is 161.879 ~ 280.805mm, chord length b is 198.440 ~ 329.378mm, flow inlet angle α is 65.491 ° ~ 88.966 °, established angle β y is 56.414 ° ~ 59.611 °, molded line maximum ga(u)ge T is 46.563 ~ 60.059mm, trailing edge thickness δ is 4.000mm, and the total height L of blade working part is 501.64mm.
The utility model compared with prior art has following beneficial effect: blade of the present utility model is in the full three dimensional design calculating this third level guide vane with one dimension, accurate three-dimensional, full three-dimensional pneumatic, thermodynamic analysis, calculation accuracy is high, the Security of blade of the present utility model and high efficiency are organically combined, ensure energy safe and highly efficient operation under variable working condition, the aerodynamic efficiency of third level guide vane improves 0.9%-1.35%, and working life extends 1.6 to 2.1 times.
Accompanying drawing explanation
Fig. 1 is the plan view of the utility model blade, and Fig. 2 is the left view of Fig. 1, and Fig. 3 is the superimposed schematic diagram of vane type line part each cross section tomography; Fig. 4 is the schematic diagram that blade working part 1 shows blade profile parameters Q, b, α, β y, T, δ, and Fig. 5 is the K place enlarged view of Fig. 4, and Fig. 6 is the N place enlarged view of Fig. 4.
Embodiment
Embodiment one: composition graphs 1 to Fig. 4 illustrates, the described blade of present embodiment comprises blade working part 1, upper end wall 2 and lower end wall 3, blade working part 1, upper end wall 2 and lower end wall 3 are cast as one, the molded line of blade working part 1 is variable cross section twisted blade molded line, different along blade height sectional shape, sectional area is increased to top gradually by root, has relative torsion between adjacent two sections; Blade working part 1 near root to the geometric data in the cross section at top: the depth of section h of section A-A, section B-B, cross section C-C, cross section D-D and cross section E-E is 0 ~ 501.64mm, axial width Q is 161.879 ~ 280.805mm, chord length b is 198.440 ~ 329.378mm, flow inlet angle α is 65.491 ° ~ 88.966 °, established angle β y is 56.414 ° ~ 59.611 °, molded line maximum ga(u)ge T is 46.563 ~ 60.059mm, trailing edge thickness δ is 4.000mm, and the total height L of blade working part 1 is 501.64mm.
Embodiment two: composition graphs 2 to Fig. 6 illustrates, the depth of section h 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 161.888mm, chord length b is 198.440mm, flow inlet angle α is 65.491 °, established angle β y is 56.414 °, molded line maximum ga(u)ge T is 46.563mm, trailing edge thickness δ is 4.000mm.
In present embodiment, undocumented technical characteristics is identical with embodiment one.
Embodiment three: composition graphs 2 to Fig. 6 illustrates, the depth of section h of blade working part 1 section B-B of present embodiment is 151.30mm, and the axial width Q of the blade working part 1 corresponding to this position is 197.312mm, chord length b is 237.017mm, flow inlet angle α is 78.391 °, established angle β y is 57.740 °, molded line maximum ga(u)ge T is 50.538mm, trailing edge thickness δ is 4.000mm.
In present embodiment, undocumented technical characteristics is identical with embodiment one or two.
Embodiment four: composition graphs 2 to Fig. 6 illustrates, the depth of section h of the blade working part 1 cross section C-C of present embodiment is 251.60mm, and the axial width Q of the blade working part 1 corresponding to this position is 221.057mm, chord length b is 263.161mm, flow inlet angle α is 80.238 °, established angle β y is 58.432 °, molded line maximum ga(u)ge T is 53.442mm, trailing edge thickness δ is 4.000mm.
In present embodiment, undocumented technical characteristics is identical with embodiment three.
Embodiment five: composition graphs 2 to Fig. 6 illustrates, the depth of section h of the blade working part 1 cross section D-D of present embodiment is 351.94mm, and the axial width Q of the blade working part 1 corresponding to this position is 245.152mm, chord length b is 289.823mm, flow inlet angle α is 81.440 °, established angle β y is 58.982 °, molded line maximum ga(u)ge T is 56.240mm, trailing edge thickness δ is 4.000mm.
In present embodiment, undocumented technical characteristics is identical with embodiment four.
Embodiment six: composition graphs 2 to Fig. 6 illustrates, the depth of section h of the blade working part 1 cross section E-E of present embodiment is 501.64mm, and the axial width Q of the blade working part 1 corresponding to this position is 280.805mm, chord length b is 329.378mm, flow inlet angle α is 88.966 °, established angle β y is 59.611 °, molded line maximum ga(u)ge T is 60.059mm, trailing edge thickness δ is 4.000mm.
In present embodiment, undocumented technical characteristics is identical with embodiment five.
Claims (6)
1. the turbine third level guide vane for lower calorific value combustion engine in heavy type, described blade comprises blade working part (1), upper end wall (2) and lower end wall (3), blade working part (1), upper end wall (2) and lower end wall (3) are cast as one, the molded line of blade working part (1) is variable cross section twisted blade molded line, different along blade height sectional shape, sectional area is increased to top gradually by root, has relative torsion between adjacent two sections, it is characterized in that: blade working part (1) is from close root to the geometric data in the cross section at top: section A-A, section B-B, cross section C-C, the depth of section (h) of cross section D-D and cross section E-E is 0 ~ 501.64mm, axial width (Q) is 161.879 ~ 280.805mm, chord length (b) is 198.440 ~ 329.378mm, flow inlet angle (α) is 65.491 ° ~ 88.966 °, established angle (β y) is 56.414 ° ~ 59.611 °, molded line maximum ga(u)ge (T) is 46.563 ~ 60.059mm, trailing edge thickness (δ) is 4.000mm, the total height (L) of blade working part (1) is 501.64mm.
2. according to claim 1 for the turbine third level guide vane of lower calorific value combustion engine in heavy type, it is characterized in that: the depth of section (h) 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 161.888mm, chord length (b) is 198.440mm, flow inlet angle (α) is 65.491 °, established angle (β y) is 56.414 °, molded line maximum ga(u)ge (T) is 46.563mm, trailing edge thickness (δ) is 4.000mm.
3. according to claim 1 or 2 for the turbine third level guide vane of lower calorific value combustion engine in heavy type, it is characterized in that: the depth of section (h) of blade working part (1) section B-B is 151.30mm, the axial width (Q) of the blade working part (1) corresponding to this position is 197.312mm, chord length (b) is 237.017mm, flow inlet angle (α) is 78.391 °, established angle (β y) is 57.740 °, molded line maximum ga(u)ge (T) is 50.538mm, trailing edge thickness (δ) is 4.000mm.
4. according to claim 3 for the turbine third level guide vane of lower calorific value combustion engine in heavy type, it is characterized in that: the depth of section (h) of blade working part (1) cross section C-C is 251.60mm, the axial width (Q) of the blade working part (1) corresponding to this position is 221.057mm, chord length (b) is 263.161mm, flow inlet angle (α) is 80.238 °, established angle (β y) is 58.432 °, molded line maximum ga(u)ge (T) is 53.442mm, trailing edge thickness (δ) is 4.000mm.
5. according to claim 4 for the turbine third level guide vane of lower calorific value combustion engine in heavy type, it is characterized in that: the depth of section (h) of blade working part (1) cross section D-D is 351.94mm, the axial width (Q) of the blade working part (1) corresponding to this position is 245.152mm, chord length (b) is 289.823mm, flow inlet angle (α) is 81.440 °, established angle (β y) is 58.982 °, molded line maximum ga(u)ge (T) is 56.240mm, trailing edge thickness (δ) is 4.000mm.
6. according to claim 5 for the turbine third level guide vane of lower calorific value combustion engine in heavy type, it is characterized in that: the depth of section (h) of blade working part (1) cross section E-E is 501.64mm, the axial width (Q) of the blade working part (1) corresponding to this position is 280.805mm, chord length (b) is 329.378mm, flow inlet angle (α) is 88.966 °, established angle (β y) is 59.611 °, molded line maximum ga(u)ge (T) is 60.059mm, trailing edge thickness (δ) is 4.000mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420573954.7U CN204060805U (en) | 2014-09-30 | 2014-09-30 | A kind of turbine third level guide vane for lower calorific value combustion engine in heavy type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420573954.7U CN204060805U (en) | 2014-09-30 | 2014-09-30 | A kind of turbine third level guide vane for lower calorific value combustion engine in heavy type |
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| Publication Number | Publication Date |
|---|---|
| CN204060805U true CN204060805U (en) | 2014-12-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420573954.7U Withdrawn - After Issue CN204060805U (en) | 2014-09-30 | 2014-09-30 | A kind of turbine third level guide vane for lower calorific value combustion engine in heavy type |
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| CN (1) | CN204060805U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104295324A (en) * | 2014-09-30 | 2015-01-21 | 哈尔滨汽轮机厂有限责任公司 | Third stage turbine guide vane for heavy type low and middle heat value fuel machine |
| CN111636928A (en) * | 2020-05-29 | 2020-09-08 | 浙江燃创透平机械股份有限公司 | High-efficiency gas turbine last-stage guide vane for controlling reaction degree distribution |
-
2014
- 2014-09-30 CN CN201420573954.7U patent/CN204060805U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104295324A (en) * | 2014-09-30 | 2015-01-21 | 哈尔滨汽轮机厂有限责任公司 | Third stage turbine guide vane for heavy type low and middle heat value fuel machine |
| CN104295324B (en) * | 2014-09-30 | 2016-06-29 | 哈尔滨汽轮机厂有限责任公司 | A kind of for the turbine third level guide vane of low heat value combustion engine in heavy type |
| CN111636928A (en) * | 2020-05-29 | 2020-09-08 | 浙江燃创透平机械股份有限公司 | High-efficiency gas turbine last-stage guide vane for controlling reaction degree distribution |
| CN111636928B (en) * | 2020-05-29 | 2022-06-21 | 浙江燃创透平机械股份有限公司 | High-efficiency gas turbine last-stage guide vane for controlling reaction degree distribution |
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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: 20160629 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |