CN104295323B - A kind of turbine third level moving vane for heavy type low heat value combustion machine - Google Patents
A kind of turbine third level moving vane for heavy type low heat value combustion machine Download PDFInfo
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- CN104295323B CN104295323B CN201410520310.6A CN201410520310A CN104295323B CN 104295323 B CN104295323 B CN 104295323B CN 201410520310 A CN201410520310 A CN 201410520310A CN 104295323 B CN104295323 B CN 104295323B
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Abstract
For a turbine third level moving vane for heavy type low heat value combustion machine, it relates to a kind of turbine moving blade for heavy type low heat value combustion machine. to solve, the strength decreased that the increase of the combustion of low heat value in current heavy type machine turbine third level moving vane height brings is serious, leaf aerodynamic efficiency is low, service life is short, affect the problem of turbine safe operation, between adjacent two sections, has relative torsion, the geometric data of blade working part from close root to the cross section at top: section A-A, section B-B, cross section C-C, cross section D-D, cross section E-E, cross section F-F, cross section G-G, cross section H-H, cross section I-I, the depth of section of cross section J-J and cross section K-K is 0～550.77mm, axial width Q is 77.610～145.468mm, chord length b is 115.771～148.437mm, flow inlet angle α is 54.911 °～86.683 °, established angle β y is 41.778 °～78.822 °, molded line maximum ga(u)ge T is 5.268～25.468mm, trailing edge thickness δ is 2.623～5.978mm, the total height L of blade working part is 550.77mm. the present invention is for the turbine of heavy type low heat value combustion machine.
Description
Technical field
The present invention relates to a kind of turbine moving blade for heavy type low heat value combustion machine.
Background technology
In recent years, the raising gradually that efficient gas turbine improves combustor exit temperature and turbine power gradually makes turbine leafSheet height improves gradually, causes the impact of the blade physical form that is subject to multiple cross sections blade profile molded line envelope one-tenth, makes in heavy type lowThe turbine third level moving vane aerodynamic efficiency of calorific value fuel gas turbine is low, service life is short, affect turbine safe operation.
Summary of the invention
The object of this invention is to provide a kind of turbine third level moving vane for heavy type low heat value combustion machine, to solve current weightStrength decreased that in type, the increase of low heat value combustion machine turbine third level moving vane height brings is serious, leaf aerodynamic efficiency is low, makeShort with the life-span, to affect turbine safe operation problem.
The present invention addresses the above problem the technical scheme of taking to be: described moving vane of the present invention comprise blade working part,Shroud and petiole, blade working part, shroud and petiole are cast as one, and the molded line of blade working part is that variable cross-section is turned round leafSheet molded line, along blade height cross sectional shape difference, sectional area is increased gradually by root to top, has relatively between adjacent two sectionsReverse; Blade working part near root to the geometric data in the cross section at top: section A-A, section B-B, cross section C-C,Cross section D-D, cross section E-E, cross section F-F, cross section G-G, cross section H-H, cross section I-I, cross section J-J and cross section K-K'sDepth of section is 0～550.77mm, and axial width Q is 77.610～145.468mm, chord length b is 115.771～148.437mm, flow inlet angle α is 54.911 °～86.683 °, established angle β y is 41.778 °～78.822 °, molded lineMaximum ga(u)ge T is 5.268～25.468mm, and trailing edge thickness δ is 2.623～5.978mm, the height overall of blade working partDegree L is 550.77mm,
The depth of section of blade working partial cross section A-A is 0mm, the axial width of the corresponding blade working part in this positionQ be 145.468mm, chord length b be 148.437mm, flow inlet angle α be 57.383 °, established angle β y be 78.822 °,Molded line maximum ga(u)ge T is that 25.468mm, trailing edge thickness δ are 5.978mm,
The depth of section of blade working partial cross section G-G is 334.11mm, the axle of the corresponding blade working part in this positionBe that 103.526mm, chord length b are that 129.414mm, flow inlet angle α are that 77.870 °, established angle β y are 53.293 to width Q°, molded line maximum ga(u)ge T is that 11.630mm, trailing edge thickness δ are 2.819mm,
The depth of section of blade working partial cross section E-E is 219.58mm, the axle of the corresponding blade working part in this positionBe that 117.098mm, chord length b are that 134.826mm, flow inlet angle α are that 70.498 °, established angle β y are 60.779 to width Q°, molded line maximum ga(u)ge T is that 15.965mm, trailing edge thickness δ are 2.690mm.
The present invention compared with prior art has following beneficial effect:
Moving vane of the present invention is to calculate the complete of this chopped-off head moving vane with one dimension, accurate three-dimensional, full three-dimensional pneumatic, thermodynamic analysisThree dimensional design, computational accuracy is high, and moving vane security of the present invention and high efficiency are organically combined, and has ensured in variable working conditionLower can safe and highly efficient operation, improved the aerodynamic efficiency 0.7%-1.2% of blade, extended 1.8 to 2.2 service lifeDoubly.
Brief description of the drawings
Fig. 1 is the front view of moving vane of the present invention, and Fig. 2 is the left view of Fig. 1, and Fig. 3 is that the each cross section of vane type line part is disconnectedThe stacked schematic diagram that closes; Fig. 4 is that moving vane working portion of the present invention shows showing of blade profile parameters Q, b, α, β y, T, δIntention, Fig. 5 is the K place enlarged drawing of Fig. 4, Fig. 6 is the N place enlarged drawing of Fig. 4.
Detailed description of the invention
Detailed description of the invention one: illustrate in conjunction with Fig. 1 to Fig. 6, the described moving vane of present embodiment comprises blade working part1, shroud 2 and petiole 3, blade working part 1, shroud 2 and petiole 3 are cast as one, the type of blade working part 1Line is variable cross-section twisted blade molded line, and along blade height cross sectional shape difference, sectional area is increased gradually by root to top, adjacentBetween two sections, there is relative torsion; The geometric data of blade working part 1 from close root to the cross section at top: section A-A,Section B-B, cross section C-C, cross section D-D, cross section E-E, cross section F-F, cross section G-G, cross section H-H, cross section I-I, cutThe depth of section of face J-J and cross section K-K is 0～550.77mm, and axial width Q is 77.610～145.468mm, chord lengthB is 115.771～148.437mm, and flow inlet angle α is 54.911 °～86.683 °, established angle β y be 41.778 °～78.822 °, molded line maximum ga(u)ge T is 5.268～25.468mm, and trailing edge thickness δ is 2.623～5.978mm, bladeThe total height L of working portion 1 is 550.77mm,
The depth of section of blade working part 1 section A-A is 0mm, the corresponding blade working part 1 in this position axiallyWidth Q is that 145.468mm, chord length b are that 148.437mm, flow inlet angle α are that 57.383 °, established angle β y are 78.822°, molded line maximum ga(u)ge T is that 25.468mm, trailing edge thickness δ are 5.978mm,
The depth of section of blade working part 1 cross section G-G is 334.11mm, the corresponding blade working part 1 in this positionAxial width Q be that 103.526mm, chord length b are that 129.414mm, flow inlet angle α are that 77.870 °, established angle β y are53.293 °, molded line maximum ga(u)ge T are that 11.630mm, trailing edge thickness δ are 2.819mm,
The depth of section of blade working part 1 cross section E-E is 219.58mm, the corresponding blade working part 1 in this positionAxial width Q be that 117.098mm, chord length b are that 134.826mm, flow inlet angle α are that 70.498 °, established angle β y are60.779 °, molded line maximum ga(u)ge T are that 15.965mm, trailing edge thickness δ are 2.690mm.
Detailed description of the invention two: illustrate in conjunction with Fig. 2 to Fig. 6, blade working part 1 section B-B of present embodiment cutFace height is 47.75mm, and the axial width Q of the corresponding blade working part 1 in this position is 139.094mm, chord length bFor 144.625mm, flow inlet angle α be 54.911 °, established angle β y be 74.628 °, molded line maximum ga(u)ge T be 23.051mm,Trailing edge thickness δ is 4.312mm.
In present embodiment, undocumented technical characterictic is identical with detailed description of the invention one.
Detailed description of the invention three: illustrate in conjunction with Fig. 2 to Fig. 6, the blade working part 1 cross section C-C of present embodiment cutsFace height is 105.05mm, and the axial width Q of the corresponding blade working part 1 in this position is 131.605mm, chord length bFor 140.842mm, flow inlet angle α be 56.755 °, established angle β y be 69.752 °, molded line maximum ga(u)ge T be 20.560mm,Trailing edge thickness δ is 3.119mm.
In present embodiment, undocumented technical characterictic is identical with detailed description of the invention one or two.
Detailed description of the invention four: illustrate in conjunction with Fig. 2 to Fig. 6, the blade working part 1 cross section D-D of present embodiment cutsFace height is 162.33mm, and the axial width Q of the corresponding blade working part 1 in this position is 124.267mm, chord length bFor 137.659mm, flow inlet angle α be 60.778 °, established angle β y be 65.118 °, molded line maximum ga(u)ge T be 18.243mm,Trailing edge thickness δ is 2.623mm.
In present embodiment, undocumented technical characterictic is identical with detailed description of the invention three.
Detailed description of the invention five: illustrate in conjunction with Fig. 2 to Fig. 6, the blade working part 1 cross section F-F of present embodiment cutsFace height is 275.18mm, and the axial width Q of the corresponding blade working part 1 in this position is 110.413mm, chord length bFor 132.229mm, flow inlet angle α be 76.679 °, established angle β y be 56.929 °, molded line maximum ga(u)ge T be 13.800mm,Trailing edge thickness δ is 2.727mm.
In present embodiment, undocumented technical characterictic is identical with detailed description of the invention four.
Detailed description of the invention six: illustrate in conjunction with Fig. 2 to Fig. 6, the blade working part 1 cross section H-H of present embodiment cutsFace height is 388.36mm, and the axial width Q of the corresponding blade working part 1 in this position is 97.206mm, chord length bFor 126.607mm, flow inlet angle α be 82.855 °, established angle β y be 50.246 °, molded line maximum ga(u)ge T be 9.819mm,Trailing edge thickness δ is 2.824mm.
In present embodiment, undocumented technical characterictic is identical with detailed description of the invention five.
Detailed description of the invention seven: illustrate in conjunction with Fig. 2 to Fig. 6, the blade working part 1 cross section I-I of present embodiment cutsFace height is 445.64mm, and the axial width Q of the corresponding blade working part 1 in this position is 90.570mm, chord length bFor 123.350mm, flow inlet angle α be 83.710 °, established angle β y be 47.205 °, molded line maximum ga(u)ge T be 8.108mm,Trailing edge thickness δ is 2.800mm.
In present embodiment, undocumented technical characterictic is identical with detailed description of the invention six.
Detailed description of the invention eight: illustrate in conjunction with Fig. 2 to Fig. 6, the blade working part 1 cross section J-J of present embodiment cutsFace height is 502.94mm, and the axial width Q of the corresponding blade working part 1 in this position is 83.708mm, chord length bFor 119.562mm, flow inlet angle α be 85.392 °, established angle β y be 44.258 °, molded line maximum ga(u)ge T be 6.535mm,Trailing edge thickness δ is 2.813mm.
In present embodiment, undocumented technical characterictic is identical with detailed description of the invention seven.
Detailed description of the invention nine: illustrate in conjunction with Fig. 2 to Fig. 6, the blade working part 1 cross section K-K of present embodiment cutsFace height is 550.77mm, and the axial width Q of the corresponding blade working part 1 in this position is 77.610mm, chord length bFor 115.771mm, flow inlet angle α be 86.683 °, established angle β y be 41.778 °, molded line maximum ga(u)ge T be 5.268mm,Trailing edge thickness δ is 2.930mm.
In present embodiment, undocumented technical characterictic is identical with detailed description of the invention eight.
Claims (9)
1. the turbine third level moving vane for heavy type low heat value combustion machine, described moving vane comprises blade working part (1), shroud (2) and petiole (3), blade working part (1), shroud (2) and petiole (3) are cast as one, the molded line of blade working part (1) is variable cross-section twisted blade molded line, along blade height cross sectional shape difference, sectional area is increased gradually by root to top, between adjacent two sections, has relative torsion, it is characterized in that: the geometric data of blade working part (1) from close root to the cross section at top: section A-A, section B-B, cross section C-C, cross section D-D, cross section E-E, cross section F-F, cross section G-G, cross section H-H, cross section I-I, the depth of section of cross section J-J and cross section K-K is 0～550.77mm, axial width (Q) is 77.610～145.468mm, chord length (b) is 115.771～148.437mm, flow inlet angle (α) is 54.911 °～86.683 °, (β is y) 41.778 °～78.822 ° to established angle, molded line maximum ga(u)ge (T) is 5.268～25.468mm, trailing edge thickness (δ) is 2.623～5.978mm, the total height (L) of blade working part (1) is 550.77mm, the depth of section of blade working part (1) section A-A is 0mm, and the axial width (Q) of the corresponding blade working part in this position (1) is 145.468mm, chord length (b) is 148.437mm, flow inlet angle (α) is 57.383 °, (β is y) 78.822 ° to established angle, molded line maximum ga(u)ge (T) is 25.468mm, trailing edge thickness (δ) is 5.978mm, and the depth of section of blade working part (1) cross section G-G is 334.11mm, and the axial width (Q) of the corresponding blade working part in this position (1) is 103.526mm, chord length (b) is 129.414mm, flow inlet angle (α) is 77.870 °, (β is y) 53.293 ° to established angle, molded line maximum ga(u)ge (T) is 11.630mm, trailing edge thickness (δ) is 2.819mm, and the depth of section of blade working part (1) cross section E-E is 219.58mm, and the axial width (Q) of the corresponding blade working part in this position (1) is 117.098mm, chord length (b) is 134.826mm, flow inlet angle (α) is 70.498 °, (β is y) 60.779 ° to established angle, molded line maximum ga(u)ge (T) is 15.965mm, trailing edge thickness (δ) is 2.690mm.
2. the turbine third level moving vane for heavy type low heat value combustion machine according to claim 1, it is characterized in that: the depth of section of blade working part (1) section B-B is 47.75mm, the axial width (Q) of the corresponding blade working part in this position (1) be 139.094mm, chord length (b) for 144.625mm, flow inlet angle (α) be 54.911 °, established angle (β be y) 74.628 °, molded line maximum ga(u)ge (T) for 23.051mm, trailing edge thickness (δ) be 4.312mm.
3. the turbine third level moving vane for heavy type low heat value combustion machine according to claim 1 and 2, it is characterized in that: the depth of section of blade working part (1) cross section C-C is 105.05mm, the axial width (Q) of the corresponding blade working part in this position (1) be 131.605mm, chord length (b) for 140.842mm, flow inlet angle (α) be 56.755 °, established angle (β be y) 69.752 °, molded line maximum ga(u)ge (T) for 20.560mm, trailing edge thickness (δ) be 3.119mm.
4. the turbine third level moving vane for heavy type low heat value combustion machine according to claim 3, it is characterized in that: the depth of section of blade working part (1) cross section D-D is 162.33mm, the axial width (Q) of the corresponding blade working part in this position (1) be 124.267mm, chord length (b) for 137.659mm, flow inlet angle (α) be 60.778 °, established angle (β be y) 65.118 °, molded line maximum ga(u)ge (T) for 18.243mm, trailing edge thickness (δ) be 2.623mm.
5. the turbine third level moving vane for heavy type low heat value combustion machine according to claim 4, it is characterized in that: the depth of section of blade working part (1) cross section F-F is 275.18mm, the axial width (Q) of the corresponding blade working part in this position (1) be 110.413mm, chord length (b) for 132.229mm, flow inlet angle (α) be 76.679 °, established angle (β be y) 56.929 °, molded line maximum ga(u)ge (T) for 13.800mm, trailing edge thickness (δ) be 2.727mm.
6. the turbine third level moving vane for heavy type low heat value combustion machine according to claim 5, it is characterized in that: the depth of section of blade working part (1) cross section H-H is 388.36mm, the axial width (Q) of the corresponding blade working part in this position (1) be 97.206mm, chord length (b) for 126.607mm, flow inlet angle (α) be 82.855 °, established angle (β be y) 50.246 °, molded line maximum ga(u)ge (T) for 9.819mm, trailing edge thickness (δ) be 2.824mm.
7. the turbine third level moving vane for heavy type low heat value combustion machine according to claim 6, it is characterized in that: the depth of section of blade working part (1) cross section I-I is 445.64mm, the axial width (Q) of the corresponding blade working part in this position (1) be 90.570mm, chord length (b) for 123.350mm, flow inlet angle (α) be 83.710 °, established angle (β be y) 47.205 °, molded line maximum ga(u)ge (T) for 8.108mm, trailing edge thickness (δ) be 2.800mm.
8. the turbine third level moving vane for heavy type low heat value combustion machine according to claim 7, it is characterized in that: the depth of section of blade working part (1) cross section J-J is 502.94mm, the axial width (Q) of the corresponding blade working part in this position (1) be 83.708mm, chord length (b) for 119.562mm, flow inlet angle (α) be 85.392 °, established angle (β be y) 44.258 °, molded line maximum ga(u)ge (T) for 6.535mm, trailing edge thickness (δ) be 2.813mm.
9. the turbine third level moving vane for heavy type low heat value combustion machine according to claim 8, it is characterized in that: the depth of section of blade working part (1) cross section K-K is 550.77mm, the axial width (Q) of the corresponding blade working part in this position (1) be 77.610mm, chord length (b) for 115.771mm, flow inlet angle (α) be 86.683 °, established angle (β be y) 41.778 °, molded line maximum ga(u)ge (T) for 5.268mm, trailing edge thickness (δ) be 2.930mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410520310.6A CN104295323B (en) | 2014-09-30 | 2014-09-30 | A kind of turbine third level moving vane for heavy type low heat value combustion machine |
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| CN201410520310.6A CN104295323B (en) | 2014-09-30 | 2014-09-30 | A kind of turbine third level moving vane for heavy type low heat value combustion machine |
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| CN104295323A CN104295323A (en) | 2015-01-21 |
| CN104295323B true CN104295323B (en) | 2016-05-11 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6722852B1 (en) * | 2002-11-22 | 2004-04-20 | General Electric Company | Third stage turbine bucket airfoil |
| US6857855B1 (en) * | 2003-08-04 | 2005-02-22 | General Electric Company | Airfoil shape for a turbine bucket |
| US6910868B2 (en) * | 2003-07-23 | 2005-06-28 | General Electric Company | Airfoil shape for a turbine bucket |
| CN103510999A (en) * | 2013-09-29 | 2014-01-15 | 哈尔滨汽轮机厂有限责任公司 | Turbine secondary moving blade applicable to heavy-duty gas turbine |
| CN204060803U (en) * | 2014-09-30 | 2014-12-31 | 哈尔滨汽轮机厂有限责任公司 | A kind of turbine third level moving vane for lower calorific value combustion engine in heavy type |
-
2014
- 2014-09-30 CN CN201410520310.6A patent/CN104295323B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6722852B1 (en) * | 2002-11-22 | 2004-04-20 | General Electric Company | Third stage turbine bucket airfoil |
| US6910868B2 (en) * | 2003-07-23 | 2005-06-28 | General Electric Company | Airfoil shape for a turbine bucket |
| US6857855B1 (en) * | 2003-08-04 | 2005-02-22 | General Electric Company | Airfoil shape for a turbine bucket |
| CN103510999A (en) * | 2013-09-29 | 2014-01-15 | 哈尔滨汽轮机厂有限责任公司 | Turbine secondary moving blade applicable to heavy-duty gas turbine |
| CN204060803U (en) * | 2014-09-30 | 2014-12-31 | 哈尔滨汽轮机厂有限责任公司 | A kind of turbine third level moving vane for lower calorific value combustion engine in heavy type |
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Effective date of registration: 20221230 Address after: 150000 building 3, high tech production base, Nangang District, Harbin City, Heilongjiang Province Patentee after: HARBIN TURBINE Co.,Ltd. Patentee after: HADIAN POWER EQUIPMENT NATIONAL ENGINEERING RESEARCH CENTER CO.,LTD. Address before: 150046 No. three power road 345, Xiangfang District, Heilongjiang, Harbin Patentee before: HARBIN TURBINE Co.,Ltd. |
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