CN203476402U - Second-stage guide blade for turbine of heavy low and medium calorific value gas turbine - Google Patents
Second-stage guide blade for turbine of heavy low and medium calorific value gas turbine Download PDFInfo
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- CN203476402U CN203476402U CN201320614084.9U CN201320614084U CN203476402U CN 203476402 U CN203476402 U CN 203476402U CN 201320614084 U CN201320614084 U CN 201320614084U CN 203476402 U CN203476402 U CN 203476402U
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- 238000002485 combustion reaction Methods 0.000 claims description 14
- 238000009434 installation Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012932 thermodynamic analysis Methods 0.000 description 1
- 238000003325 tomography Methods 0.000 description 1
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Abstract
The utility model discloses a second-stage guide blade for a turbine of a heavy low and medium calorific value gas turbine, relates to a guide blade for the turbine of the heavy low and medium calorific value gas turbine, and aims to solve the problems that an existing second-stage guide blade for the turbine of the heavy low and medium calorific value gas turbine is low in air power efficiency and short in service life and the safe operation of the turbine is affected. According to the second-stage guide blade, the working part, the upper end wall and the lower end wall of the blade are cast into a whole; a molded line of the working part of the blade is a variable cross-section twisted blade; the sectional area from the root to the top of the working part increases gradually; relative twist exists between every two adjacent sections; geometric data of the sections from the root to the top of the working part of the blade are as follows: the heights of the sections of A-A, B-B, C-C, D-D, E-E and F-F range from 0mm to 315.80mm; the axial width ranges from 183.401mm to 256.921mm; the chord length ranges from 264.096mm to 331.916mm; air inlet angles range from 81.284 degrees to 87.281 degrees; installation angles range from 45.573 degrees to 52.587 degrees; the largest thickness of the molded line ranges from 66.707mm to 72.341mm; the thickness of air outlet sides ranges from 4.429mm to 4.787mm; the overall height of the working part of the blade is 315.80mm. The second-stage guide blade is used for the turbine of the heavy low and medium calorific value gas turbine.
Description
Technical field
The utility model relates to a kind of guide vane that is applied to lower calorific value combustion machine turbine in heavy type.
Background technique
In recent years, high efficiency gas turbine improves gradually combustor exit temperature and makes great efforts to improve the cooling of various turbine components.Yet in heavy type, lower calorific value combustion machine turbine second level guide vane aerodynamic efficiency is low at present, working life is short, affect turbine safe operation.
Model utility content
The purpose of this utility model is to provide a kind of turbine second level guide vane that is applied to the combustion of lower calorific value in heavy type machine, and to solve, in current heavy type, lower calorific value combustion machine turbine second level guide vane aerodynamic efficiency is low, working life is short, affect the problem of turbine safe operation.
The utility model is to solve the problems of the technologies described above the technological scheme of taking to be: a kind of turbine second level guide vane that is applied to lower calorific value combustion machine in heavy type 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 into one, the molded line of blade working part is variable cross section twisted blade, the sectional area of working portion is increased to top cross-section is long-pending gradually by root, between adjacent two sections, there is relative torsion, the cross section geometric data of blade working part from root to top: section A-A to the depth of section of cross section F-F is 0～315.80mm, axial width is 183.401～256.921mm, chord length is 264.096～331.916mm, flow inlet angle is 81.284 °～87.281 °, established angle is 45.573 °～52.587 °, molded line maximum ga(u)ge is 66.707～72.341mm, trailing edge thickness is 4.429～4.787mm, the total height of blade working part is 315.80mm.
The utility model compared with prior art has following beneficial effect: guide vane of the present utility model is with one dimension, accurate three-dimensional, full three-dimensional pneumatic, thermodynamic analysis calculates the full three dimensional design of this second level stator, calculation accuracy is high, this Security of carrying out novel guide vane and high efficiency are organically combined, guaranteed energy safe and highly efficient operation under variable working condition, improved the aerodynamic efficiency of blade, extended blade working life, according to statistics, the relative prior art of aerodynamic efficiency of blade improves 2% to 5%, relatively improve 1.5 to 1.8 times the working life of blade.
Accompanying drawing explanation
Fig. 1 is plan view of the present utility model, Fig. 2 is the left view of Fig. 1, and Fig. 3 is the superimposed schematic diagram of blade working each cross section tomography of part, and Fig. 4 is the schematic diagram of blade profile parameters Q, b, β y, T, Fig. 5 is the local enlarged diagram in I place of Fig. 4, and Fig. 6 is the local enlarged diagram in J place of Fig. 4.
Embodiment
Embodiment one: illustrate in conjunction with Fig. 1 to Fig. 6, a kind of turbine second level guide vane that is applied to lower calorific value combustion machine in heavy type 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 into one, the molded line of blade working part 1 is variable cross section twisted blade, the sectional area of working portion 1 is increased to top cross-section is long-pending gradually by root, between adjacent two sections, there is relative torsion, the cross section geometric data of blade working part 1 from root to top: section A-A to the depth of section h of cross section F-F be 0～315.80mm, axial width Q is 183.401～256.921mm, chord length b is 264.096～331.916mm, flow inlet angle α is 81.284 °～87.281 °, established angle β y is 45.573 °～52.587 °, molded line maximum ga(u)ge T is 66.707～72.341mm, trailing edge thickness δ is 4.429～4.787mm, the total height L of blade working part 1 is 315.80mm.
Embodiment two: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 of present embodiment at section A-A place is 0mm, and the axial width Q of the corresponding blade working part 1 in this position is that 183.401mm, chord length b are that 264.096mm, flow inlet angle α are that 87.249 °, established angle β y are that 45.573 °, molded line maximum ga(u)ge T are that 66.707mm, trailing edge thickness δ are 4.712mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment one.
Embodiment three: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 of present embodiment at section B-B place is 63.80mm, and the axial width Q of the corresponding blade working part 1 in this position is that 197.461mm, chord length b are that 276.731mm, flow inlet angle α are that 86.948 °, established angle β y are that 47.151 °, molded line maximum ga(u)ge T are that 67.999mm, trailing edge thickness δ are 4.692mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment one or two.
Embodiment four: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 of present embodiment at C-C place, cross section is 126.80mm, and the axial width Q of the corresponding blade working part 1 in this position is that 211.875mm, chord length b are that 289.634mm, flow inlet angle α are that 83.446 °, established angle β y are that 48.668 °, molded line maximum ga(u)ge T are that 69.384mm, trailing edge thickness δ are 4.705mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment three.
Embodiment five: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 of present embodiment at D-D place, cross section is 189.80mm, and the axial width Q of the corresponding blade working part 1 in this position is that 226.750mm, chord length b are that 302.829mm, flow inlet angle α are that 82.142 °, established angle β y are that 50.104 °, molded line maximum ga(u)ge T are that 70.724mm, trailing edge thickness δ are 4.787mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment four.
Embodiment six: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 of present embodiment at E-E place, cross section is 252.80mm, and the axial width Q of the corresponding blade working part 1 in this position is that 241.641mm, chord length b are that 316.732mm, flow inlet angle α are that 87.281 °, established angle β y are that 51.343 °, molded line maximum ga(u)ge T are that 71.840mm, trailing edge thickness δ are 4.753mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment five.
Embodiment seven: illustrate in conjunction with Fig. 1 to Fig. 6, the depth of section h of the blade working part 1 of present embodiment at F-F place, cross section is 315.80mm, and the axial width Q of the corresponding blade working part 1 in this position is that 256.921mm, chord length b are that 331.916mm, flow inlet angle α are that 81.284 °, established angle β y are that 52.587 °, molded line maximum ga(u)ge T are that 72.341mm, trailing edge thickness δ are 4.429mm.Meet design requirement.In present embodiment, undocumented technical characteristics is identical with embodiment six.
Claims (7)
1. a turbine second level guide vane that is applied to the combustion of lower calorific value in heavy type machine, 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 into one, the molded line of blade working part (1) is variable cross section twisted blade, the sectional area of working portion (1) is increased to top cross-section is long-pending gradually by root, between adjacent two sections, has relative torsion, it is characterized in that: the cross section geometric data of blade working part (1) from root to top: section A-A to the depth of section (h) of cross section F-F is 0～315.80mm, axial width (Q) is 183.401～256.921mm, chord length (b) is 264.096～331.916mm, flow inlet angle (α) is 81.284 °～87.281 °, established angle (β y) is 45.573 °～52.587 °, molded line maximum ga(u)ge (T) is 66.707～72.341mm, trailing edge thickness (δ) is 4.429～4.787mm, the total height (L) of blade working part (1) is 315.80mm.
2. be applied to according to claim 1 the turbine second level guide vane of lower calorific value combustion machine in heavy type, it is characterized in that: blade working part (1) depth of section (h) at section A-A place be 0mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 183.401mm, chord length (b) are that 264.096mm, flow inlet angle (α) are that 87.249 °, established angle (β y) are that 45.573 °, molded line maximum ga(u)ge (T) are that 66.707mm, trailing edge thickness (δ) are 4.712mm.
3. according to the turbine second level guide vane that is applied to lower calorific value combustion machine in heavy type described in claim 1 or 2, it is characterized in that: blade working part (1) depth of section (h) at section B-B place be 63.80mm, the axial width (Q) of the corresponding blade working part in this position (1) be that 197.461mm, chord length (b) are that 276.731mm, flow inlet angle (α) are that 86.948 °, established angle (β y) are that 47.151 °, molded line maximum ga(u)ge (T) are that 67.999mm, trailing edge thickness (δ) are 4.692mm.
4. be applied to according to claim 3 the turbine second level guide vane of lower calorific value combustion machine in heavy type, it is characterized in that: blade working part (1) depth of section (h) at C-C place, cross section be 126.80mm, the axial width (Q) of the corresponding blade working part in this position (1) is that 211.875mm, chord length (b) are that 289.634mm, flow inlet angle (α) are that 83.446 °, established angle (β y) are that 48.668 °, molded line maximum ga(u)ge (T) are that 69.384mm, trailing edge thickness (δ) are 4.705mm.
5. be applied to according to claim 4 the turbine second level guide vane of lower calorific value combustion machine in heavy type, it is characterized in that: blade working part (1) depth of section (h) at D-D place, cross section be 189.80mm, the axial width (Q) of the corresponding blade working part in this position (1) is that 226.750mm, chord length (b) are that 302.829mm, flow inlet angle (α) are that 82.142 °, established angle (β y) are that 50.104 °, molded line maximum ga(u)ge (T) are that 70.724mm, trailing edge thickness (δ) are 4.787mm.
6. be applied to according to claim 5 the turbine second level guide vane of lower calorific value combustion machine in heavy type, it is characterized in that: blade working part (1) depth of section (h) at E-E place, cross section be 252.80mm, the axial width (Q) of the corresponding blade working part in this position (1) is that 241.641mm, chord length (b) are that 316.732mm, flow inlet angle (α) are that 87.281 °, established angle (β y) are that 51.343 °, molded line maximum ga(u)ge (T) are that 71.840mm, trailing edge thickness (δ) are 4.753mm.
7. be applied to according to claim 6 the turbine second level guide vane of lower calorific value combustion machine in heavy type, it is characterized in that: blade working part (1) depth of section (h) at F-F place, cross section be 315.80mm, the axial width (Q) of the corresponding blade working part in this position (1) is that 256.921mm, chord length (b) are that 331.916mm, flow inlet angle (α) are that 81.284 °, established angle (β y) are that 52.587 °, molded line maximum ga(u)ge (T) are that 72.341mm, trailing edge thickness (δ) are 4.429mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320614084.9U CN203476402U (en) | 2013-09-30 | 2013-09-30 | Second-stage guide blade for turbine of heavy low and medium calorific value gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320614084.9U CN203476402U (en) | 2013-09-30 | 2013-09-30 | Second-stage guide blade for turbine of heavy low and medium calorific value gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN203476402U true CN203476402U (en) | 2014-03-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320614084.9U Withdrawn - After Issue CN203476402U (en) | 2013-09-30 | 2013-09-30 | Second-stage guide blade for turbine of heavy low and medium calorific value gas turbine |
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| CN (1) | CN203476402U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103557034A (en) * | 2013-09-30 | 2014-02-05 | 哈尔滨汽轮机厂有限责任公司 | Second stage guide vane applicable to turbine of heavy low calorific value fuel machine |
-
2013
- 2013-09-30 CN CN201320614084.9U patent/CN203476402U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103557034A (en) * | 2013-09-30 | 2014-02-05 | 哈尔滨汽轮机厂有限责任公司 | Second stage guide vane applicable to turbine of heavy low calorific value fuel machine |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140312 Effective date of abandoning: 20150715 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20140312 Effective date of abandoning: 20150715 |
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| RGAV | Abandon patent right to avoid regrant |