CN104755704A - Last stage turbine blade including a plurality of leading edge indentations, corresponding rotor assembly and steam turbine - Google Patents
Last stage turbine blade including a plurality of leading edge indentations, corresponding rotor assembly and steam turbine Download PDFInfo
- Publication number
- CN104755704A CN104755704A CN201380042146.6A CN201380042146A CN104755704A CN 104755704 A CN104755704 A CN 104755704A CN 201380042146 A CN201380042146 A CN 201380042146A CN 104755704 A CN104755704 A CN 104755704A
- Authority
- CN
- China
- Prior art keywords
- steam turbine
- blade
- turbine blade
- rotor
- flow
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/31—Application in turbines in steam turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Abstract
Aspects of the invention provide for a last stage blade of a steam turbine. In one embodiment, the last stage blade of a steam turbine includes: a blade leading edge for receiving a through flow, the blade leading edge including a plurality of indentations at a top portion of the steam turbine blade; and a blade trailing edge for exhausting the through flow. A corresponding rotor assembly and a steam turbine are also provided.
Description
Technical field
The present invention relates generally to turbo machine, such as steamturbine, and more specifically, relate to the steamturbine exhaust stage blade of the multiple indentures comprising leading edge place.
Background technique
Under the normal running (operation) conditions of steamturbine, the through-flow whole length along final stage steam turbine blade extends.But, under the condition of extremely turning down with low discharge and/or high exhaust pressure, through-flow the tip part flowing through final stage steam turbine blade.
When the distal tip timesharing of the final stage steam turbine blade that through-flow flows through, blade experience supersonic inlets condition, and shock wave will be formed in blade row ingress.Stride across impact, pressure reduces suddenly.The aerodynamic force educational level caused by supersonic inlets condition and shock wave transient effect can affect the reliability of exhaust stage blade negatively due to potential damaging vibration.The side of rising and flowing that the tip part of the through-flow final stage steam turbine blade flow through also experiences temperature upwards pressure rising.
Summary of the invention
Aspect of the present invention provides a kind of exhaust stage blade of steamturbine.In one embodiment, the exhaust stage blade of steamturbine comprises: for receiving through-flow blade inlet edge, and this blade inlet edge comprises multiple indentures of the top office of steam turbine blade; With for discharging through-flow trailing edge.
A first aspect of the present invention provides a kind of steam turbine blade, comprising: for receiving through-flow blade inlet edge, and this blade inlet edge comprises multiple indentures of the top office of steam turbine blade; With for discharging through-flow trailing edge.
A second aspect of the present invention provides a kind of rotor assembly, comprising: rotor body, and it comprises multiple groove; Multiple steam turbine blades in multiple grooves of rotor body, wherein, at least one in steam turbine blade comprises: for receiving through-flow blade inlet edge, and this blade inlet edge comprises multiple indentures of the top office of steam turbine blade; With for discharging through-flow trailing edge.
A third aspect of the present invention provides a kind of steamturbine, comprising: stator; With the multiple impeller of rotor around stator, each impeller of rotor comprises: multiple steam turbine blade, wherein, the steam turbine blade of at least one impeller of rotor comprises: for receiving through-flow blade inlet edge, and this blade inlet edge comprises multiple indentures of the top office of steam turbine blade; With for discharging through-flow trailing edge.
The following detailed description made from the appended accompanying drawing of combination is become obvious by these and other aspect of the present invention, advantage and notable feature, wherein runs through the identical parts of accompanying drawing and is marked by identical reference number, open embodiments of the present invention.
Accompanying drawing explanation
Fig. 1 represents the phantom of the low pressure section of steamturbine.
Fig. 2 represents the perspective view of the steam turbine blade according to embodiment of the present invention.
It should be noted that accompanying drawing of the present disclosure is not necessarily drawn in proportion.Accompanying drawing intention only describes typical pattern of the present disclosure, and therefore should not be considered to limit the scope of the present disclosure.In the accompanying drawings, identical numbering represents element identical between accompanying drawing.
Embodiment
As mentioned above, the present invention relates generally to turbo machine, such as steamturbine, and more specifically, relates to the steamturbine exhaust stage blade of the multiple indentures comprising leading edge place.
Under the condition of the normal operation of steamturbine, the through-flow whole length along final stage steam turbine blade extends.But, under the condition of extremely turning down with low discharge and/or high exhaust pressure, through-flow the tip part flowing through final stage steam turbine blade.
When the distal tip timesharing of the final stage steam turbine blade that through-flow flows through, blade experience supersonic inlets condition, and shock wave will enter interruption-forming at blade row.Stride across impact, pressure reduces suddenly.The aerodynamic force educational level caused by supersonic inlets condition and shock wave transient effect can affect the reliability of exhaust stage blade negatively due to potential damaging vibration.The aerodynamic force educational level caused by supersonic inlets condition and shock wave transient effect can affect the reliability of exhaust stage blade negatively due to potential damaging vibration.The tip part of the through-flow final stage steam turbine blade flow through also experiences the rising of temperature, and the side of flowing upwards pressure rising.
With reference to accompanying drawing, Fig. 1 represents the partial sectional view of steamturbine 10.Steamturbine 10 comprises rotor 12, and rotor 12 comprises axle 14 and multiple axially isolated impeller of rotor 18.In some embodiments, each impeller of rotor 18 can be made of metal, such as steel.Multiple rotation blade 20 is mechanically connected to each impeller of rotor 18.More specifically, blade 20 is arranged in the row circumferentially extended around each impeller of rotor 18.Multiple fixed guide vane 22 circumferentially extends around axle 14 and is axially positioned between the adjacent row of blade 20.Fixed guide vane 22 cooperates with blade 20, to form turbine stage and to be defined through the part of the vapor flow path of turbine 10.
In operation, working fluid 24 enters the import 26 of steamturbine 10, and is conducted through fixed guide vane 22.Stator 22 guides fluid 24 in face of blade 20 to downstream.Fluid 24 travels across remaining level, thus applies power on blade 20, thus causes the axle 14 being connected to rotor 12 rigidly to rotate.At least one end of steamturbine 10 axially can extend away from rotor 12, and is attachable to load or machine (not shown), such as but not limited to, generator, and/or another turbine.Therefore, in fact large turbine unit can comprise the some turbines being all connected to same axis 14 coaxially.Such unit can such as comprise the high-pressure turbine being connected to middle pressure turbine, and this middle-pressure turbine is connected to low-pressure turbine again.
As shown in Figure 1, turbine 10 comprises and is called L0, five levels of L1, L2, L3 and L4.L4 level is the first order and is minimum (in radial directions) in five levels.L3 level is the second level and is the next stage on axial direction.L2 level is the third level and is presented at the centre of five levels.L1 level is the fourth stage and is penultimate stage.L0 level is final stage and is maximum (in radial directions).Should be understood that, five levels only illustrate as an example; Some turbine mode of executions can have greater or less than five levels.As indicated, to be at different levelsly made up of impeller of rotor 18, the stator 22 of blade 20 and correspondence that is connected to this impeller of rotor 18.
The aspect of invention as herein described is applicable to the final stage L0 of steamturbine 10.In one embodiment, the exhaust stage blade of steamturbine comprises: for receiving through-flow blade inlet edge, and this blade inlet edge is included in multiple indentures of the top office of steam turbine blade; With for discharging through-flow trailing edge.Due to supersonic inlets condition and shock wave transient effect, the plurality of indenture of steam turbine blade top section will be reduced to the level of aerodynamic force educational level.
Turn to Fig. 2 now, represent the perspective view be used for according to the exhaust stage blade 100 of the steamturbine 10 (Fig. 1) of embodiment of the present invention.Although only illustrate single exhaust stage blade 100 in Fig. 2, be understandable that, the impeller of rotor 18 at final stage L0 (Fig. 1) place comprises the multiple exhaust stage blades 100 around rotor subject 12 (Fig. 1) circumference.
Blade 100 comprises for receiving through-flow leading edge 110 and for discharging through-flow trailing edge 120.As mentioned above, extremely turning down under condition, when there is low through-flow and/or high exhaust pressure (this is that high ambient temperature and underload demand are necessary), through-flow the top section 130 flowing through blade 110.This causes can the unexpected aerodynamic force educational level of damaged blade.
In order to reduce aerodynamic force educational level during extremely turning down condition, blade inlet edge 110 comprises multiple indentures 140 at blade 100 top section 130 place.The top section 130 of blade 100 can be at least about 10 of blade 100, but 20 about percent of no more than blade 100.But should be understood that, these percentages of blade 100 are only for exemplary purposes, and the plurality of indenture 140 can extend along the whole surface of leading edge 110.
As shown in the figure, rotor body 12 comprises for receiving blade 100 and blade 100 being affixed to multiple grooves 150 of rotor body 12.Showing for being in pine tree structure although the dovetail between groove 150 with blade 100 is connected, it should be understood that blade 100 is by T-shaped root pattern structure, or any structure that is known or exploitation later is now connected to rotor subject 12.
As used herein, term " first ", " second " etc. do not represent any order, quantity or significance, but for an element and another are distinguished, and term " " here and " one " do not represent number quantitative limitation, but represent the existence of at least one in REFER object.The modifier " approximately " used in combination with quantity comprises stated value, and has the implication (such as, comprising the degree of error relevant to the measurement of specific quantity) specified by context.Prefix as used herein " (multiple) " is intended to the odd number and the plural number that comprise the term that it is modified, thus comprises one or more this term (such as, (multiple) metal comprises one or more metal).Scope disclosed herein be comprise and can combine independently (such as, " up to about 25 millimeters, or more specifically, about 5 millimeters to about 20 millimeters; " scope comprise all intermediate values of the scope of end points and " about 5 millimeters to about 25 millimeters ", etc.).
Although the description of various mode of execution, but it is evident that from specification, the various combinations of the element can made by those skilled in the art, modification wherein or improvement, within the scope of the present invention.In addition, according to instruction of the present invention, many amendments can be carried out to adapt to special circumstances or material, and not depart from its base region.Therefore, intention the invention is not restricted to as design for performing optimal mode of the present invention and disclosed particular implementation, but the present invention includes all mode of executions fallen within the scope of claims.
Claims (20)
1. a steam turbine blade, comprising:
For receiving through-flow blade inlet edge, described blade inlet edge comprises multiple indentures of the top office of described steam turbine blade; With
For discharging described through-flow trailing edge.
2. steam turbine blade according to claim 1, is characterized in that, the top section of described steam turbine blade comprises ten at least percent of described blade.
3. steam turbine blade according to claim 1, is characterized in that, the top section of described steam turbine blade comprises no more than 20 percent of described blade.
4. steam turbine blade according to claim 1, is characterized in that, in the normal operation period, described current flow strides across the whole length of described steam turbine blade.
5. steam turbine blade according to claim 1, is characterized in that, in low through-flow period, and the described through-flow top section only flowing across described steam turbine blade.
6. steam turbine blade according to claim 1, is characterized in that, described steam turbine blade is exhaust stage blade.
7. a rotor assembly, comprising:
Rotor body, it comprises multiple groove;
Multiple steam turbine blade, it is in described multiple groove of described rotor body, and wherein, at least one in described steam turbine blade comprises:
For receiving through-flow blade inlet edge, described blade inlet edge comprises multiple indentures of the top office of described steam turbine blade; With
For discharging described through-flow trailing edge.
8. rotor assembly according to claim 7, is characterized in that, the top section of at least one steam turbine blade comprises ten at least percent of described blade.
9. rotor assembly according to claim 7, is characterized in that, the top section of at least one steam turbine blade comprises no more than 20 percent of described blade.
10. rotor assembly according to claim 7, is characterized in that, in the normal operation period, described current flow strides across the whole length of at least one steam turbine blade.
11. rotor assembly according to claim 7, is characterized in that, in low through-flow period, and through-flow at least one the top section described only flowed across in described steam turbine blade.
12. rotor assembly according to claim 7, is characterized in that, at least one steam turbine blade is exhaust stage blade.
13. rotor assembly according to claim 7, is characterized in that, described multiple steam turbine blade forms multiple impeller of rotor along the axial length of described rotor body.
14. rotor assembly according to claim 13, is characterized in that, each in the steam turbine blade of final stage impeller of rotor comprises multiple indentures of the top office of blade inlet edge.
15. 1 kinds of steamturbines, comprising:
Stator; With
Around multiple impeller of rotor of described stator, each impeller of rotor comprises:
Multiple steam turbine blade, wherein, the steam turbine blade of at least one impeller of rotor comprises:
For receiving through-flow blade inlet edge, described blade inlet edge comprises multiple indentures of the top office of described steam turbine blade; With
For discharging described through-flow trailing edge.
16. steamturbines according to claim 15, is characterized in that, the top section of the steam turbine blade of at least one impeller of rotor described comprises ten at least percent of each blade.
17. steamturbines according to claim 15, is characterized in that, the top section of the steam turbine blade of at least one impeller of rotor described comprises no more than 20 percent of each blade.
18. steamturbines according to claim 15, is characterized in that, in the normal operation period, described current flow strides across the whole length of the steam turbine blade of at least one impeller of rotor described.
19. steamturbines according to claim 15, is characterized in that, in low through-flow period, and the described through-flow top section only flowing across multiple steam turbine blades of at least one impeller of rotor described.
20. steamturbines according to claim 15, is characterized in that, the steam turbine blade of at least one impeller of rotor described is exhaust stage blade.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/568,609 US20140044556A1 (en) | 2012-08-07 | 2012-08-07 | Last stage blade including a plurality of leading edge indentations |
| US13/568609 | 2012-08-07 | ||
| PCT/US2013/053713 WO2014025729A1 (en) | 2012-08-07 | 2013-08-06 | Last stage turbine blade including a plurality of leading edge indentations, corresponding rotor assembly and steam turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104755704A true CN104755704A (en) | 2015-07-01 |
| CN104755704B CN104755704B (en) | 2016-12-14 |
Family
ID=49001070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380042146.6A Expired - Fee Related CN104755704B (en) | 2012-08-07 | 2013-08-06 | Including the final stage turbo blade of multiple leading edge indentures, corresponding rotor assembly and steamturbine |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20140044556A1 (en) |
| EP (1) | EP2893144A1 (en) |
| JP (1) | JP2015525854A (en) |
| CN (1) | CN104755704B (en) |
| RU (1) | RU2015103596A (en) |
| WO (1) | WO2014025729A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108035775A (en) * | 2018-01-08 | 2018-05-15 | 翁志远 | Rotor, steam turbine and prime mover equipment of steam turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1862827A (en) * | 1930-01-22 | 1932-06-14 | Parsons | Steam turbine |
| EP1211383A2 (en) * | 2000-12-04 | 2002-06-05 | United Technologies Corporation | A mistuned rotor blade array |
| CN1364975A (en) * | 2001-01-09 | 2002-08-21 | 通用电气公司 | Method and device for reducing the temperature of turbine leaf opex |
| CN101042054A (en) * | 2006-03-24 | 2007-09-26 | 中国科学院工程热物理研究所 | Unshrouded turbine and its blade tip with groove |
| EP2322761A2 (en) * | 2009-11-12 | 2011-05-18 | General Electric Company | Turbine blade and rotor |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3304056A (en) * | 1965-03-19 | 1967-02-14 | Hitachi Ltd | Turbine blades |
| JPS6380003A (en) * | 1986-09-25 | 1988-04-11 | Hitachi Ltd | Exhaust diffuser cascade of axial-flow turbine |
| JPS63179101A (en) * | 1987-01-20 | 1988-07-23 | Mitsubishi Heavy Ind Ltd | Axial flow turbine |
| US6139258A (en) * | 1987-03-30 | 2000-10-31 | United Technologies Corporation | Airfoils with leading edge pockets for reduced heat transfer |
| US5641268A (en) * | 1991-09-17 | 1997-06-24 | Rolls-Royce Plc | Aerofoil members for gas turbine engines |
| JPH07158402A (en) * | 1993-12-10 | 1995-06-20 | Mitsubishi Heavy Ind Ltd | Moving blade for turbomachinery |
| JP3771967B2 (en) * | 1996-05-21 | 2006-05-10 | 株式会社東芝 | Axial flow turbine |
| KR20010005910A (en) * | 1997-04-01 | 2001-01-15 | 칼 하인쯔 호르닝어 | Surface structure for the wall of a flow channel or a turbine blade |
| EP1607573B2 (en) * | 2004-06-02 | 2012-10-03 | Rolls-Royce Deutschland Ltd & Co KG | Compressor blade with reduced aerodynamic vibration induction |
| US7901523B2 (en) * | 2007-11-16 | 2011-03-08 | General Electric Company | Uniform heat treatment process for hardening steel |
| US8056227B2 (en) * | 2009-02-06 | 2011-11-15 | General Electric Company | Turbine blade having material block and related method |
-
2012
- 2012-08-07 US US13/568,609 patent/US20140044556A1/en not_active Abandoned
-
2013
- 2013-08-06 JP JP2015526621A patent/JP2015525854A/en active Pending
- 2013-08-06 RU RU2015103596A patent/RU2015103596A/en not_active Application Discontinuation
- 2013-08-06 CN CN201380042146.6A patent/CN104755704B/en not_active Expired - Fee Related
- 2013-08-06 EP EP13750793.5A patent/EP2893144A1/en not_active Withdrawn
- 2013-08-06 WO PCT/US2013/053713 patent/WO2014025729A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1862827A (en) * | 1930-01-22 | 1932-06-14 | Parsons | Steam turbine |
| EP1211383A2 (en) * | 2000-12-04 | 2002-06-05 | United Technologies Corporation | A mistuned rotor blade array |
| CN1364975A (en) * | 2001-01-09 | 2002-08-21 | 通用电气公司 | Method and device for reducing the temperature of turbine leaf opex |
| CN101042054A (en) * | 2006-03-24 | 2007-09-26 | 中国科学院工程热物理研究所 | Unshrouded turbine and its blade tip with groove |
| EP2322761A2 (en) * | 2009-11-12 | 2011-05-18 | General Electric Company | Turbine blade and rotor |
Also Published As
| Publication number | Publication date |
|---|---|
| US20140044556A1 (en) | 2014-02-13 |
| JP2015525854A (en) | 2015-09-07 |
| CN104755704B (en) | 2016-12-14 |
| WO2014025729A8 (en) | 2015-03-05 |
| EP2893144A1 (en) | 2015-07-15 |
| RU2015103596A (en) | 2016-09-27 |
| WO2014025729A1 (en) | 2014-02-13 |
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