CN102434223A - Low-pressure stage final blade of large-flow air-cooled steam turbine - Google Patents
Low-pressure stage final blade of large-flow air-cooled steam turbine Download PDFInfo
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- CN102434223A CN102434223A CN2011104143424A CN201110414342A CN102434223A CN 102434223 A CN102434223 A CN 102434223A CN 2011104143424 A CN2011104143424 A CN 2011104143424A CN 201110414342 A CN201110414342 A CN 201110414342A CN 102434223 A CN102434223 A CN 102434223A
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Abstract
The invention discloses a low-pressure stage final blade of a large-flow air-cooled steam turbine, which is a variable-cross-section twisted blade used for the large-flow air-cooled steam turbine with a steam discharging area of 3.6m<2>. The blade comprises a blade body, a blade root, and a girdle strip and a rib boss which are used for making the blade form whole circle self-locking. The height Ld of the blade body relative to the blade root is increased from 0% to 100% through one-direction regulation, and the variation rule of the ratio T/b of a pitch from the cross section of the blade root to the cross section of a blade top to the chord length is: 0.4<=T/b<=1.0. The variation rule of the ratio T/B of the pitch from the cross section of the blade root to the cross section of the blade top to the axial width of the cross section of the blade shape is: 0.4<=T/b<=3.0. The variation rule of the ratio T/Dmax of the pitch from the cross section of the blade root to the cross section of the blade top to the maximum thickness of the cross section of the blade shape is: 2.5<=T/Dmax<=22.5. The blade has the advantages of excellent variable working condition running property, excellent strong vibration property, reasonable structure, convenience for assembly and wide market application prospects.
Description
Technical field
The present invention relates to a kind of turbine blade, especially a kind of big flow air cooling turbine low pressure stage group exhaust stage blade.
Background technique
The big flow air cooling turbine demand of power industry at home constantly increases, and its efficient design shows its significance gradually especially.Air-cooled Unit is a kind of typical variable parameter operation unit; With respect to the water-cooled unit; The design back pressure height and the back pressure excursion of Air-cooled Unit are big; The variation of ambient temperature scope of atmosphere is big to be caused exhaust stage blade to satisfy to the air blast operating mode under, to move by blocking operating mode, no matter in low back pressure, block under operating mode or high back pressure, the air blast situation, all ten minutes is badly for the operating conditions of exhaust stage blade.So low pressure stage group exhaust stage blade has become the key link in the design.Have only hold exactly whole unit particularly the through-flow performance of low pressure stage group just can design the big flow air cooling turbine of high-efficiency reliable exhaust stage blade.
Summary of the invention
The objective of the invention is a kind of big flow air cooling turbine low pressure stage group exhaust stage blade that designs for the deficiency that solves above-mentioned technology, this blade has good off design performance and strength character, and is rational in infrastructure, easy to assembly.
The big flow air cooling turbine low pressure stage group exhaust stage blade that the present invention designed, it is that a kind of leaving area that is used for is 3.6m
2The variable cross section twisted blade of big flow air cooling turbine; Comprise blade, blade root and be used to make blade to form the shroud and the lacing wire boss of the self-locking of whole circle; The high Ld of the relative leaf of said blade is added to 100% by 0% monotone increasing, and the pitch to chord length from the blade root cross section to the leaf top section than T/b Changing Pattern is: 0.4≤T/b≤1.0; Pitch from the blade root cross section to the leaf top section with blade profile cross section axial width than T/B Changing Pattern is: 0.4≤T/B≤3.0; Pitch from the blade root cross section to the leaf top section with blade profile cross section maximum ga(u)ge than T/Dmax Changing Pattern is: 2.5≤T/Dmax≤22.5; Pitch from the blade root cross section to the leaf top section with the blade profile section area than T/A Changing Pattern is: 0.01≤T/A≤0.18; Blade profile leading-edge radius R0 Changing Pattern from the blade root cross section to the leaf top section is: 1.0mm≤R0≤3.5mm; Blade profile trailing edge radius R 1 Changing Pattern from the blade root cross section to the leaf top section is: 1.0mm≤R1≤3.5mm.
As preferably:
Said blade height is 600mm;
Said blade root is a fir-tree root, and the blade root axial width is 220mm;
Said boss is an elliptical table, boss centre distance blade bottom 360mm;
Described blade, its lagging edge back of the body arc place is provided with the part of hardening;
The big flow air cooling turbine low pressure stage group exhaust stage blade of gained of the present invention, leaf adopt ternary flow field designing technique to design, and the width in body cross section, thickness and cross sectional area are reduced to the top by root gradually; Dullness seamlessly transits, and has certain distortion rule along the high direction blade of leaf, has promptly taken into account the requirement of blade static strength; Also make blade have good aeroperformance, blade distortion rule designs according to three-dimensional flow theory, and has taken into account along the high equal strength design principle of leaf; Reasonable along each thermal parameter regularity of distribution of blade; Calculating checking through professional computation fluid dynamics software for calculation CFX and Numeca etc., is that 0.1bar exports Mach number under 0.5 o'clock operating mode in back pressure, and the pneumatic efficiency of place low pressure stage group is about 82%; Peak rate of flow and has good off design performance more than 300t/h; Blade is the linear leaf that carries the whole circle of shroud self-locking damping type, and the blade middle and upper part has boss, and there is shroud on the leaf top; The gap that 0.1-0.6mm is all arranged between each blade boss and between shroud is under working speed, because action of centrifugal force; Blade produces certain counter turning round; Make between blade and fit between boss and boss, shroud and shroud, produce positive pressure and frictional force, increased the damping of system; Reach the whole circle of blade self-locking structure simultaneously, improve the vibration performance of blade, reduce the suffered dynamic stress of blade; Blade root is adopted the fir-tree root design, and blade is easy to assembly, can be at back pressure 0.05bar～0.25bar, and safe operation under the rotating speed 3000rpm has wide market application prospect.
Description of drawings
Fig. 1 is a blade front view of the present invention;
Fig. 2 is a blade-side view of the present invention;
Fig. 3 is a blade plan view of the present invention;
Fig. 4 is the long-pending folded schematic representation of vane type line of the present invention;
The adjacent two blade shroud band plan views of Fig. 5;
Fig. 6 is the adjacent two blade boss sectional views of the present invention.
Fig. 7 is that the adjacent three blade self-lockings of the present invention connect schematic representation;
Among the figure: shroud 1, lacing wire boss 2, blade 3, blade root 4.
Embodiment
Combine accompanying drawing that the present invention is done further description through embodiment below.
Embodiment 1:
Like Fig. 1,2, shown in 3, the described big flow air cooling turbine low pressure stage group exhaust stage blade of present embodiment, it is that a kind of leaving area that is used for is 3.6m
2The variable cross section twisted blade of big flow air cooling turbine; Comprise blade 3, blade root 4 and be used to make blade to form the shroud 1 and the lacing wire boss of the self-locking of whole circle; The high Ld of said blade 3 relative leaves is added to 100% by 0% monotone increasing, and the pitch to chord length from blade root 4 cross sections to the leaf top section than T/b Changing Pattern is: 0.4≤T/b≤1.0; Pitch from blade root 4 cross sections to the leaf top section with blade profile cross section axial width than T/B Changing Pattern is: 0.4≤T/B≤3.0; Pitch from blade root 4 cross sections to the leaf top section with blade profile cross section maximum ga(u)ge than T/Dmax Changing Pattern is: 2.5≤T/Dmax≤22.5; Pitch from blade root 4 cross sections to the leaf top section with the blade profile section area than T/A Changing Pattern is: 0.01≤T/A≤0.18; Blade profile leading-edge radius R0 Changing Pattern from blade root 4 cross sections to the leaf top section is: 1.0mm≤R0≤3.5mm; Blade profile trailing edge radius R 1 Changing Pattern from blade root 4 cross sections to the leaf top section is: 1.0mm≤R1≤3.5mm.Wherein, said blade 3 highly is 600mm; Said blade root 4 is a fir-tree root 4, and blade root 4 axial widths are 220mm, and blade pass is crossed fir-tree root 4 and is installed in the impeller groove, axially assembling; Said boss is an elliptical table, boss centre distance blade 3 bottom 360mm; Described blade 3, its lagging edge back of the body arc place is provided with the part of hardening, and the length of hardening is decided as required.
Blade is a monolithic structure when static, and boss and shroud 1 are not all fitted, and under working speed, because action of centrifugal force, blade 3 produces certain counter turning round, and makes boss and boss, shroud 1 and 1 of shroud produce positive pressure and frictional force, has increased the damping of system; Make the whole circle of blade (like Fig. 7) in groups simultaneously, improve the vibration performance of blade.
The big flow air cooling turbine low pressure stage group exhaust stage blade of gained of the present invention, leaf adopt ternary flow field designing technique to design, and the width in body cross section, thickness and cross sectional area are reduced to the top by root gradually; Dullness seamlessly transits, and has certain distortion rule along the high direction blade of leaf, has promptly taken into account the requirement of blade static strength; Also make blade have good aeroperformance, blade 3 distortion rules design according to three-dimensional flow theory, and have taken into account along the high equal strength design principle of leaf; Reasonable along blade 3 each thermal parameter regularity of distribution; Calculating checking through professional computation fluid dynamics software for calculation CFX and Numeca etc., is that 0.1bar exports Mach number under 0.5 o'clock operating mode in back pressure, and the pneumatic efficiency of place low pressure stage group is about 82%; Peak rate of flow and has good off design performance more than 300t/h; Blade is the linear leaf that carries shroud 1 whole circle self-locking damping type, and blade 3 middle and upper parts have boss, and there is shroud 1 on the leaf top; Between each blade boss and 1 gap that 0.1-0.6mm is all arranged of shroud is under working speed, because action of centrifugal force; Blade 3 produces certain counter turning round; Make boss and boss, shroud 1 and 1 applying of shroud between blade, produce positive pressure and frictional force, increased the damping of system; Reach the whole circle of blade self-locking structure simultaneously, improve the vibration performance of blade, reduce the suffered dynamic stress of blade; Blade root 4 is adopted fir-tree root 4 designs, and blade is easy to assembly, can be at back pressure 0.05bar～0.25bar, and safe operation under the rotating speed 3000rpm has wide market application prospect.
Claims (5)
1. one kind big flow air cooling turbine low pressure stage group exhaust stage blade, it is that a kind of leaving area that is used for is 3.6m
2The variable cross section twisted blade of big flow air cooling turbine; Comprise blade, blade root and be used to make blade to form the shroud and the lacing wire boss of the self-locking of whole circle; It is characterized in that the high Ld of the relative leaf of said blade is added to 100% by 0% monotone increasing, the pitch to chord length from the blade root cross section to the leaf top section than T/b Changing Pattern is: 0.4≤T/b≤1.0; Pitch from the blade root cross section to the leaf top section with blade profile cross section axial width than T/B Changing Pattern is: 0.4≤T/B≤3.0; Pitch from the blade root cross section to the leaf top section with blade profile cross section maximum ga(u)ge than T/Dmax Changing Pattern is: 2.5≤T/Dmax≤22.5; Pitch from the blade root cross section to the leaf top section with the blade profile section area than T/A Changing Pattern is: 0.01≤T/A≤0.18; Blade profile leading-edge radius R0 Changing Pattern from the blade root cross section to the leaf top section is: 1.0mm≤R0≤3.5mm; Blade profile trailing edge radius R 1 Changing Pattern from the blade root cross section to the leaf top section is: 1.0mm≤R1≤3.5mm.
2. big flow air cooling turbine low pressure stage group exhaust stage blade according to claim 1 is characterized in that said blade height is 600mm.
3. big flow air cooling turbine low pressure stage group exhaust stage blade according to claim 2 is characterized in that said blade root is a fir-tree root, and the blade root axial width is 220mm.
4. according to claim 2 or 3 described big flow air cooling turbine low pressure stage group exhaust stage blades, it is characterized in that said boss is an elliptical table, boss centre distance blade bottom 360mm.
5. big flow air cooling turbine low pressure stage group exhaust stage blade according to claim 4 is characterized in that described blade, and its lagging edge back of the body arc place is provided with the part of hardening.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110414342.4A CN102434223B (en) | 2011-12-13 | 2011-12-13 | Low-pressure stage final blade of large-flow air-cooled steam turbine |
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| CN201110414342.4A CN102434223B (en) | 2011-12-13 | 2011-12-13 | Low-pressure stage final blade of large-flow air-cooled steam turbine |
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| CN102434223A true CN102434223A (en) | 2012-05-02 |
| CN102434223B CN102434223B (en) | 2014-08-20 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103628926A (en) * | 2013-10-30 | 2014-03-12 | 杭州汽轮机股份有限公司 | 3m<2>-steam-exhaust-area low-pressure stage set last stage blade of variable speed industrial steam turbine |
| CN103806946A (en) * | 2013-10-30 | 2014-05-21 | 杭州汽轮机股份有限公司 | Variable speed industrial steam turbine low-pressure stage group last stage blade with steam exhaust area of 2.1 m<2> |
| CN104196573A (en) * | 2014-07-28 | 2014-12-10 | 杭州汽轮机股份有限公司 | Low-pressure last stage blade of rotating speed-variable air cooling industrial steam turbine with steam exhaust area of 3.6 m2 |
| CN104948236A (en) * | 2014-03-27 | 2015-09-30 | 通用电气公司 | Bucket airfoil for a turbomachine |
| CN106089314A (en) * | 2016-07-29 | 2016-11-09 | 杭州汽轮机股份有限公司 | Leaving area 3.2m2the efficiently low-pressure stage group final stage moving blade of industrial steam turbine |
| CN109611158A (en) * | 2018-11-02 | 2019-04-12 | 杭州汽轮机股份有限公司 | A kind of industrial steam turbine 3600rpm high load capacity low-pressure stage movable vane piece |
| CN109695479A (en) * | 2018-08-22 | 2019-04-30 | 杭州汽轮机股份有限公司 | A kind of high revolving speed high load capacity low-pressure stage movable vane piece of industrial steam turbine |
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| CN201539279U (en) * | 2009-11-25 | 2010-08-04 | 北京全四维动力科技有限公司 | Large-scale air cooled steam turbine last-stage blade |
| EP2236755A2 (en) * | 2009-03-25 | 2010-10-06 | General Electric Company | Steam turbine rotating blade with mid-span shroud for low pressure application |
| CN202360152U (en) * | 2011-12-13 | 2012-08-01 | 杭州汽轮机股份有限公司 | Final blade in low-pressure-stage group of high-flow air cooling steam turbine |
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2011
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Patent Citations (5)
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| US20040126235A1 (en) * | 2002-12-30 | 2004-07-01 | Barb Kevin Joseph | Method and apparatus for bucket natural frequency tuning |
| CN101117895A (en) * | 2007-09-06 | 2008-02-06 | 东方电气集团东方汽轮机有限公司 | Variable-speed turbine final stage moving vane |
| EP2236755A2 (en) * | 2009-03-25 | 2010-10-06 | General Electric Company | Steam turbine rotating blade with mid-span shroud for low pressure application |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103628926A (en) * | 2013-10-30 | 2014-03-12 | 杭州汽轮机股份有限公司 | 3m<2>-steam-exhaust-area low-pressure stage set last stage blade of variable speed industrial steam turbine |
| CN103806946A (en) * | 2013-10-30 | 2014-05-21 | 杭州汽轮机股份有限公司 | Variable speed industrial steam turbine low-pressure stage group last stage blade with steam exhaust area of 2.1 m<2> |
| CN103628926B (en) * | 2013-10-30 | 2015-12-02 | 杭州汽轮机股份有限公司 | Leaving area 3.0m2Variable rotating speed industrial steam turbine low-pressure stage group exhaust stage blade |
| CN103806946B (en) * | 2013-10-30 | 2016-08-17 | 杭州汽轮机股份有限公司 | Leaving area 2.1m2variable rotating speed industrial steam turbine low-pressure stage group exhaust stage blade |
| CN104948236A (en) * | 2014-03-27 | 2015-09-30 | 通用电气公司 | Bucket airfoil for a turbomachine |
| CN104196573A (en) * | 2014-07-28 | 2014-12-10 | 杭州汽轮机股份有限公司 | Low-pressure last stage blade of rotating speed-variable air cooling industrial steam turbine with steam exhaust area of 3.6 m2 |
| CN104196573B (en) * | 2014-07-28 | 2017-02-22 | 杭州汽轮机股份有限公司 | Low-pressure last stage blade of rotating speed-variable air cooling industrial steam turbine with steam exhaust area of 3.6 m2 |
| CN106089314A (en) * | 2016-07-29 | 2016-11-09 | 杭州汽轮机股份有限公司 | Leaving area 3.2m2the efficiently low-pressure stage group final stage moving blade of industrial steam turbine |
| CN106089314B (en) * | 2016-07-29 | 2017-10-31 | 杭州汽轮机股份有限公司 | Leaving area 3.2m2The low-pressure stage group final stage moving blade of efficient industrial steam turbine |
| CN109695479A (en) * | 2018-08-22 | 2019-04-30 | 杭州汽轮机股份有限公司 | A kind of high revolving speed high load capacity low-pressure stage movable vane piece of industrial steam turbine |
| CN109695479B (en) * | 2018-08-22 | 2023-12-29 | 杭州汽轮动力集团股份有限公司 | High-rotating-speed high-load low-pressure-stage moving blade for industrial steam turbine |
| CN109611158A (en) * | 2018-11-02 | 2019-04-12 | 杭州汽轮机股份有限公司 | A kind of industrial steam turbine 3600rpm high load capacity low-pressure stage movable vane piece |
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| CN102434223B (en) | 2014-08-20 |
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Address after: 310022 Building 1, No. 608, Kangxin Road, Linping District, Hangzhou, Zhejiang Patentee after: Hangzhou Turbine Power Group Co.,Ltd. Address before: 357 Shiqiao Road, Xiacheng District, Hangzhou City, Zhejiang Province Patentee before: HANGZHOU STEAM TURBINE Co.,Ltd. |
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