CN102434223B - 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
- Publication number
- CN102434223B CN102434223B CN201110414342.4A CN201110414342A CN102434223B CN 102434223 B CN102434223 B CN 102434223B CN 201110414342 A CN201110414342 A CN 201110414342A CN 102434223 B CN102434223 B CN 102434223B
- Authority
- CN
- China
- Prior art keywords
- blade
- section
- cross
- flow air
- root
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
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 large flow air cooling turbine low pressure stage group exhaust stage blade.
Background technique
The large flow air cooling turbine at home demand of power industry 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 water chiller, the design back-pressure of Air-cooled Unit is high and economy scope is large, the variation of ambient temperature scope of atmosphere is big to be caused exhaust stage blade to meet under air blast operating mode, to move by blocking operating mode, no matter in low back pressure, block in operating mode or high back pressure, air blast situation, the operating conditions of exhaust stage blade is all very severe.So low pressure stage group exhaust stage blade has become the key link in design.Only have hold exactly whole unit particularly the through-flow performance of low pressure stage group just can design the large flow air cooling steam turbine last stage of high efficient and reliable.
Summary of the invention
The object of the invention is a kind of large flow air cooling turbine low pressure stage group exhaust stage blade designing in order to solve the deficiency of above-mentioned technology, this blade has good off design performance and strength character, rational in infrastructure, easy to assembly.
The large flow air cooling turbine low pressure stage group exhaust stage blade that the present invention is designed, it be a kind of for leaving area, be 3.6m
2the variable cross section twisted blade of large flow air cooling turbine, comprise blade, blade root and for making blade form shroud and the lacing wire boss of whole circle self-locking, the high Ld of the relative leaf of described blade, by 0% monotone increasing to 100%, from the pitch to chord length of Dao Ye top section, blade root cross section than T/b Changing Pattern is: 0.4≤T/b≤1.0; From the pitch of Dao Ye top section, blade root cross section, with blade profile cross section axial width than T/B Changing Pattern, be: 0.4≤T/B≤3.0; From the pitch of Dao Ye top section, blade root cross section, with blade profile cross section maximum ga(u)ge than T/Dmax Changing Pattern, be: 2.5≤T/Dmax≤22.5; From the pitch of Dao Ye top section, blade root cross section, with blade profile section area than T/A Changing Pattern, be: 0.01≤T/A≤0.18; From the blade profile leading-edge radius R0 Changing Pattern of Dao Ye top section, blade root cross section, be: 1.0mm≤R0≤3.5mm; From blade profile trailing edge radius R 1 Changing Pattern of Dao Ye top section, blade root cross section, be: 1.0mm≤R1≤3.5mm.
As preferably:
Described blade height is 600mm;
Described blade root is fir-tree root, and blade root axial width is 220mm;
Described boss is 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 large flow air cooling turbine low pressure stage group exhaust stage blade of gained of the present invention, leaf adopts ternary flow field designing technique to design, the width in body cross section and thickness and cross sectional area are reduced to top gradually by root, dullness seamlessly transits, along the high direction blade of leaf, there is certain distortion rule, taken into account the requirement of blade static strength, also make blade there is good aeroperformance, blade distortion rule designs according to three-dimensional flow theory, and taken into account along the high equal strength design principle of leaf, reasonable along each thermal parameter regularity of distribution of blade, through professional computation fluid dynamics software for calculation CFX and Numeca etc., calculate checking, in back pressure, be that 0.1bar outlet Mach number is under the operating mode of 0.5 o'clock, the pneumatic efficiency of place low pressure stage group is in 82% left and right, peak rate of flow is more than 300t/h, and there is good off design performance, blade is the linear leaf that carries the whole circle self-locking damping of shroud type, blade middle and upper part has boss, there is shroud on leaf top, between each blade boss and all have the gap of 0.1-0.6mm between shroud, under working speed, due to the effect of centrifugal force, blade produces certain anti-twisted, make between boss and boss, shroud and shroud, to fit between blade, produce positive pressure and frictional force, increased the damping of system, reach the whole circle self-locking structure of blade simultaneously, improve the vibration performance of blade, reduce the suffered dynamic stress of blade, blade root adopts fir-tree root design, and blade is easy to assembly, can be at back pressure 0.05bar～0.25bar, and safe operation under rotating speed 3000rpm, has wide market application foreground.
Accompanying drawing explanation
Fig. 1 is blade front view of the present invention;
Fig. 2 is blade-side view of the present invention;
Fig. 3 is blade plan view of the present invention;
Fig. 4 is the long-pending folded schematic diagram 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 the adjacent three blade self-locking connection diagrams of the present invention;
In figure: shroud 1, lacing wire boss 2, blade 3, blade root 4.
Embodiment
Below by embodiment, the invention will be further described by reference to the accompanying drawings.
Embodiment 1:
As shown in Figure 1, 2, 3, the described large flow air cooling turbine low pressure stage group exhaust stage blade of the present embodiment, it be a kind of for leaving area, be 3.6m
2the variable cross section twisted blade of large flow air cooling turbine, comprise blade 3, blade root 4 and for making blade form shroud 1 and the lacing wire boss of whole circle self-locking, the high Ld of described blade 3 relative leaf, by 0% monotone increasing to 100%, from the pitch to chord length of blade root 4 Dao Ye top sections, cross section than T/b Changing Pattern is: 0.4≤T/b≤1.0; From the pitch of blade root 4 Dao Ye top sections, cross section, with blade profile cross section axial width than T/B Changing Pattern, be: 0.4≤T/B≤3.0; From the pitch of blade root 4 Dao Ye top sections, cross section, with blade profile cross section maximum ga(u)ge than T/Dmax Changing Pattern, be: 2.5≤T/Dmax≤22.5; From the pitch of blade root 4 Dao Ye top sections, cross section, with blade profile section area than T/A Changing Pattern, be: 0.01≤T/A≤0.18; From the blade profile leading-edge radius R0 Changing Pattern of blade root 4 Dao Ye top sections, cross section, be: 1.0mm≤R0≤3.5mm; From blade profile trailing edge radius R 1 Changing Pattern of blade root 4 Dao Ye top sections, cross section, be: 1.0mm≤R1≤3.5mm.Wherein, described blade 3 is highly 600mm; Described blade root 4 is fir-tree root 4, and blade root 4 axial widths are 220mm, and blade pass is crossed fir-tree root 4 and is arranged in impeller groove, axially assembling; Described boss is 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 determined as required.
When static, blade is monolithic structure, and boss and shroud 1 are not all fitted, and under working speed, due to the effect of centrifugal force, blade 3 produces certain anti-twisted, makes boss and boss, shroud 1 and 1 generation positive pressure of shroud and frictional force, has increased the damping of system; Make the whole circle of blade (as Fig. 7) in groups simultaneously, improve the vibration performance of blade.
The large flow air cooling turbine low pressure stage group exhaust stage blade of gained of the present invention, leaf adopts ternary flow field designing technique to design, the width in body cross section and thickness and cross sectional area are reduced to top gradually by root, dullness seamlessly transits, along the high direction blade of leaf, there is certain distortion rule, taken into account the requirement of blade static strength, also make blade there is good aeroperformance, blade 3 distortion rules design according to three-dimensional flow theory, and taken into account along the high equal strength design principle of leaf, reasonable along blade 3 each thermal parameter regularities of distribution, through professional computation fluid dynamics software for calculation CFX and Numeca etc., calculate checking, in back pressure, be that 0.1bar outlet Mach number is under the operating mode of 0.5 o'clock, the pneumatic efficiency of place low pressure stage group is in 82% left and right, peak rate of flow is more than 300t/h, and there is good off design performance, blade is the linear leaf that carries the whole circle self-locking damping of shroud 1 type, blade 3 middle and upper parts have boss, there is shroud 1 on leaf top, between each blade boss and 1 gap that all has 0.1-0.6mm of shroud, under working speed, due to the effect of centrifugal force, blade 3 produces certain anti-twisted, make boss and boss, shroud 1 and 1 laminating of shroud between blade, produce positive pressure and frictional force, increased the damping of system, reach the whole circle self-locking structure of blade simultaneously, improve the vibration performance of blade, reduce the suffered dynamic stress of blade, blade root 4 adopts fir-tree root 4 designs, and blade is easy to assembly, can be at back pressure 0.05bar～0.25bar, and safe operation under rotating speed 3000rpm, has wide market application foreground.
Claims (5)
1. a large flow air cooling turbine low pressure stage group exhaust stage blade, it be a kind of for leaving area, be 3.6m
2the variable cross section twisted blade of large flow air cooling turbine, comprise blade, blade root and for making blade form shroud and the lacing wire boss of whole circle self-locking, it is characterized in that the high Ld of the relative leaf of described blade, by 0% monotone increasing to 100%, from the pitch to chord length of Dao Ye top section, blade root cross section than T/b Changing Pattern is: 0.4≤T/b≤1.0; From the pitch of Dao Ye top section, blade root cross section, with blade profile cross section axial width than T/B Changing Pattern, be: 0.4≤T/B≤3.0; From the pitch of Dao Ye top section, blade root cross section, with blade profile cross section maximum ga(u)ge than T/Dmax Changing Pattern, be: 2.5≤T/Dmax≤22.5; From the pitch of Dao Ye top section, blade root cross section, with blade profile section area than T/A Changing Pattern, be: 0.01≤T/A≤0.18; From the blade profile leading-edge radius R0 Changing Pattern of Dao Ye top section, blade root cross section, be: 1.0mm≤R0≤3.5mm; From blade profile trailing edge radius R 1 Changing Pattern of Dao Ye top section, blade root cross section, be: 1.0mm≤R1≤3.5mm.
2. large flow air cooling turbine low pressure stage group exhaust stage blade according to claim 1, is characterized in that described blade height is 600mm.
3. large flow air cooling turbine low pressure stage group exhaust stage blade according to claim 2, is characterized in that described blade root is fir-tree root, and blade root axial width is 220mm.
4. according to the large flow air cooling turbine low pressure stage group exhaust stage blade described in claim 2 or 3, it is characterized in that described boss is elliptical table, boss centre distance blade bottom 360mm.
5. large 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110414342.4A CN102434223B (en) | 2011-12-13 | 2011-12-13 | Low-pressure stage final blade of large-flow air-cooled steam turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110414342.4A CN102434223B (en) | 2011-12-13 | 2011-12-13 | Low-pressure stage final blade of large-flow air-cooled steam turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102434223A CN102434223A (en) | 2012-05-02 |
| CN102434223B true CN102434223B (en) | 2014-08-20 |
Family
ID=45982542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110414342.4A Active CN102434223B (en) | 2011-12-13 | 2011-12-13 | Low-pressure stage final blade of large-flow air-cooled steam turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102434223B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| US20150275675A1 (en) * | 2014-03-27 | 2015-10-01 | General Electric Company | Bucket airfoil for a turbomachine |
| 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 |
| 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 |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6814543B2 (en) * | 2002-12-30 | 2004-11-09 | General Electric Company | Method and apparatus for bucket natural frequency tuning |
-
2011
- 2011-12-13 CN CN201110414342.4A patent/CN102434223B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102434223A (en) | 2012-05-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102434223B (en) | Low-pressure stage final blade of large-flow air-cooled steam turbine | |
| CN104196573B (en) | Low-pressure last stage blade of rotating speed-variable air cooling industrial steam turbine with steam exhaust area of 3.6 m2 | |
| JP5988994B2 (en) | Turbine engine blades with improved stacking rules | |
| CA2697121C (en) | Intentionally mistuned integrally bladed rotor | |
| CN101769266B (en) | Centrifugal fan blade | |
| US8992179B2 (en) | Turbine of a turbomachine | |
| CN202360152U (en) | Final blade in low-pressure-stage group of high-flow air cooling steam turbine | |
| CN114718659B (en) | Turbine blade tip clearance flow control method coupling radial ribs and circumferential grooves | |
| CN104632701A (en) | High-bypass-ratio turbo-fan engine fan long-short blade structure | |
| CN103628926B (en) | Leaving area 3.0m2Variable rotating speed industrial steam turbine low-pressure stage group exhaust stage blade | |
| CN106256993A (en) | A kind of final stage moving blade of feed pump industrial steam turbine | |
| CN102536328A (en) | Last-stage blade in low-pressure stage group of variable-rotation-speed air-cooling industrial steam turbine | |
| CN108119187B (en) | Low-pressure-stage moving blade of industrial steam turbine with variable rotation speed and large flow | |
| US11047238B2 (en) | Leading edge profile of vanes | |
| CN103806946B (en) | Leaving area 2.1m2variable rotating speed industrial steam turbine low-pressure stage group exhaust stage blade | |
| CN102678603B (en) | The airfoil core shape of turbine assembly | |
| CN203948136U (en) | The low pressure stage group exhaust stage blade of leaving area 3.6m2 variable speed air cooling industrial steam turbine | |
| CN102889237B (en) | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor | |
| CN104763477B (en) | A kind of turbomachine movable vane tip segment shroud structure | |
| CN202360151U (en) | Low-pressure stage group last stage blade for variable speed air cooling industrial steam turbines | |
| CN108979735B (en) | Blade for a gas turbine and gas turbine comprising said blade | |
| CN206000578U (en) | A kind of final stage moving blade of feed pump industrial steam turbine | |
| CN104583604B (en) | Turbomachine vane having an airfoil to provide improved aerodynamic and mechanical properties | |
| CN115169032A (en) | Design method of gas turbine working blade with blade tip groove and winglet composite structure | |
| CN204851335U (en) | Integration impeller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
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. |
|
| CP03 | Change of name, title or address |