CN101255800A - Blade tip alula of turbine or steam turbine moving-blade - Google Patents
Blade tip alula of turbine or steam turbine moving-blade Download PDFInfo
- Publication number
- CN101255800A CN101255800A CNA2008100105169A CN200810010516A CN101255800A CN 101255800 A CN101255800 A CN 101255800A CN A2008100105169 A CNA2008100105169 A CN A2008100105169A CN 200810010516 A CN200810010516 A CN 200810010516A CN 101255800 A CN101255800 A CN 101255800A
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- CN
- China
- Prior art keywords
- wing
- vane
- trailing edge
- suction surface
- tip
- 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.)
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Classifications
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- 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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
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- 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
-
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
Abstract
The present invention provides a tip vane of guided vane of turbine or steam turbine related to field of turbomachine. The tip vane comprises a front edge wing, a pressure surface wing, a suction surface wing and a tail edge wing, the pressure surface wing and the suction surface wing are little vanes expended between front edge point A and tail edge point B of leaf along circumference, front edge point D and C of pressure surface wing and suction surface wing are lied on front edge point A or between front edge point A and most thickness part of guided vane; the tail edge point F and E of the pressure surface wing and the suction surface wing are arranged on tail edge point B or between tail edge point B and the most thickness part of guided vane; the front edge wing and tail edge wing are connected smoothly with the pressure surface wing and suction surface wing, and the front edge wing and the tail edge wing are extended parts of pressure surface wing and suction surface wing at front edge and tail edge. The present invention reduces effect of flow field in channel by tip leakage, tip leakage vortex and scraping gyres, improves cascade flow field, and enhances mechanical efficiency of impeller at the same time.
Description
Technical field
The present invention relates to the turbomachine field, be specifically related to be applied to the design of the tip vane of movable vanes such as various turbines or steam turbine.
Background technique
In turbomachine, it is very little that the physical dimension of the tip clearance between position, movable vane top and the casing is compared with whole runner, but it exerts an influence to the mobile of nearly 20% zone in the blade passage, especially the smaller turbine of size or steam turbine etc.Blade tip clearance has following several adverse effect: the 1) existence of tip clearance, can cause the minimizing of working fluid actual flow, and cause near the acting of blade tip to reduce, passage stops up and cascade loss increases; 2) tip leakage can form the tip leakage whirlpool at the movable vane suction surface, and tip leakage whirlpool and passage whirlpool interact, and makes the complexity more that flows in the blade grid passage, and flow losses increase, and have changed the flow outlet angle simultaneously; 3), form and wipe the stream whirlpool because rotor with respect to the motion of casing wall, causes casing wall boundary layer fricting movement.By three kinds of influences that tip clearance is brought, all changed the turbomachine flow field to some extent and distributed, increase flow losses in the turbomachine.The flow loss and the secondary flow losses such as tip leakage whirlpool and blade tip wiping stream whirlpool that are caused by tip clearance generally all occupy suitable proportion in the turbomachine total losses, thereby cause the turbomachine total losses to increase.If use existing integral shroud, then integral shroud needs and outer casing adopt multi-sealed system, and integral shroud is under high speed rotating, and centrifugal force is bigger, can cause the increase of movable vane stress, thereby reduces the reliability of turbomachine to a certain extent.
Summary of the invention
The purpose of this invention is to provide a kind of design that is applied to the tip vane of movable vanes such as various turbines or steam turbine, this design can reduce tip leakage, reduce the tip leakage whirlpool, wipe the influence of stream vortex pair runner flow field, improve cascade flow field simultaneously, improve turbomachine efficient.
In order to achieve the above object, technological scheme of the present invention is as follows:
Turbine or steam turbine movable vane tip vane mainly are made up of the leading edge wing 1, the pressure side wing 3, the suction surface wing 5 and the trailing edge wing 4 or the trailing edge wing 6; Tip vane 7 is mainly used in turbine or steam turbine movable vane 8, it is installed in the movable vane top, Placement can adopt and movable vane one processing generation, also can process tip vane separately, be connected with movable vane by modes such as welding then, be connected transition between tip vane 7 and the movable vane 8, can adopt chamfering transition, round-corner transition or adopt the free form surface smooth transition; The pressure side wing 3 and the suction surface wing 5 all can use separately, also can be used in combination with other winglet, and when being used in combination, each winglet can generate in one processing, also can process separately, couples together by modes such as welding then; The pressure side wing 3 and the suction surface wing 5 are on the basis of movable vane blade profile profile, the little fin that along the circumferential direction expands between blade profile leading edge point A and trailing edge point B; The leading edge point D of the pressure side wing 3 and the suction surface wing 5 and leading edge point C are between movable vane blade profile leading edge point A or leading edge point A and blade profile maximum ga(u)ge, the trailing edge point E of the suction surface wing 5 and the pressure side wing 3 and trailing edge point F are between trailing edge point B or blade profile maximum ga(u)ge and trailing edge point B, and the leading edge point of the suction surface wing or the pressure side wing and the optimum position of trailing edge point need to determine with test as calculated according to the actual requirements; The pressure side wing 3 can be identical along its leading edge to the trailing edge width with the suction surface wing 5, also can be different, and shape can be a regular shape, also can be the irregularly shaped of free form surface structure; The leading edge wing 1 and the trailing edge wing 4 or the trailing edge wing 6 and the suction surface wing 5 and 3 smooth connections of the pressure side wing, the leading edge wing 1 and the trailing edge wing 4 or the trailing edge wing 6 are the extensions at leading edge and trailing edge place of the suction surface wing 5 and the pressure side wing 3, be generally the smooth structure that adopts free form surface, the trailing edge wing also can adopt the dovetail structure.The tip vane top has the curvature identical with outer casing, keeps very little even distance to guarantee tip vane when the work and between the outer casing, and minimizing pressure side air-flow leaks to suction surface; The tip vane top and outside gap control between the casing can adopt initiatively gap control or passive gap control according to the design needs, the inwall of casing is coated with last layer and easily grinds coating outside, the leakage loss outside interpolation high-abrasive material in the top of tip vane is controlled between casing and the tip vane top.
The invention has the beneficial effects as follows: adopt the design of tip vane of the present invention on the movable vane top of the turbine of various gas turbines or steam turbine, has the tip leakage of reducing, the effect in control tip leakage whirlpool and wiping stream whirlpool, can improve simultaneously fluid by blade root to the formed secondary of blade tip crossfire flow field, and the present invention compares integral shroud, has simple in structure, in light weight, reliability advantages of higher.
Description of drawings
Fig. 1 is turbine of the present invention or steam turbine movable vane and the top view with tip vane of the leading edge wing, the smooth structure trailing edge wing.
Fig. 2 is turbine of the present invention or steam turbine movable vane and the top view with tip vane of the leading edge wing, the dovetail structure trailing edge wing.
Fig. 3 is the 3-D view of turbine of the present invention or steam turbine movable vane and tip vane.
Fig. 4 be turbine of the present invention or steam turbine movable vane and tip vane longshore current to sectional view.
Fig. 5 is a blade tip flow field structure schematic representation of not being with tip vane.
Fig. 6 is the blade tip flow field structure schematic representation of band tip vane of the present invention.
Among the figure: 1, the leading edge wing, 2, the blade profile profile line, 3, the pressure side wing, 4, the smooth structure trailing edge wing, 5, the suction surface wing, 6, the dovetail structure trailing edge wing, 7, tip vane, 8, turbine or steam turbine movable vane.
Embodiment
Below in conjunction with accompanying drawing the present invention is done description in further detail:
As shown in Figures 1 to 4, turbine of the present invention or steam turbine movable vane tip vane are mainly by the leading edge wing 1, the pressure side wing 3, the suction surface wing 5 and the smooth structure trailing edge wing 4 or the dovetail structure trailing edge wing 6 are formed, the pressure side wing 3 and the suction surface wing 5 are on the basis of movable vane blade profile profile, the little fin that between blade profile leading edge point A and trailing edge point B, along the circumferential direction expands, the leading edge point D of the pressure side wing 3 and the suction surface wing 5 and leading edge point C are between movable vane blade profile leading edge point A or leading edge point A and blade profile maximum ga(u)ge, and the trailing edge point F of the pressure side wing 3 and the suction surface wing 5 and trailing edge point E are between movable vane blade profile trailing edge point B or trailing edge point B and blade profile maximum ga(u)ge; The leading edge wing 1 and the smooth structure trailing edge wing 4 or the dovetail structure trailing edge wing 6 all with the suction surface wing 5 and 3 smooth connections of the pressure side wing, the leading edge wing 1 and the smooth structure trailing edge wing 4 or the dovetail structure trailing edge wing 6 all are the extensions at leading edge place and trailing edge place of the suction surface wing 5 and the pressure side wing 3.
As shown in Figure 5, in not having the normal blade tip flow field of tip vane, pressure side side high-pressure liquid flows to suction surface side low pressure area, easily form wiping stream whirlpool in the pressure side side, will be in the pointed one-tenth tip leakage of suction surface lateral lobe whirlpool in the suction surface side owing to leaking the high-speed jet fluid that forms by tip clearance, might interact with the end wall boundary layer, form large size and separate.
As shown in Figure 6, in having used the blade tip flow field of tip vane, the pressure side side is because the effect of passage whirlpool, the secondary flow that existence is flowed to blade tip by the movable vane middle part, this fluid is when blade tip runs into tip vane, air-flow is forced to turn to, and is opposite with the leak fluid direction of pressure side side direction suction surface side flow, and both interact, weakened tip leakage, simultaneously, owing to there is tip vane, runner increases in the tip clearance, frictional resistance increases, the leak fluid flow velocity descends a lot, and leakage flow thereby minimizing are a lot, and this has also controlled the leakage vortex influence degree of suction surface side to a certain extent.
Claims (5)
1, turbine or steam turbine movable vane tip vane, it is characterized in that, this tip vane is mainly by the leading edge wing (1), the pressure side wing (3), the suction surface wing (5) and the trailing edge wing are formed, the pressure side wing (3) and the suction surface wing (5) are on the basis of turbine or steam turbine movable vane blade profile profile, the little fin that between blade profile leading edge point A and trailing edge point B, along the circumferential direction expands, the leading edge point D of the pressure side wing (3) and the suction surface wing (5) and leading edge point C are between movable vane blade profile leading edge point A or leading edge point A and blade profile maximum ga(u)ge, and the trailing edge point F of the pressure side wing (3) and the suction surface wing (5) and trailing edge point E are between movable vane blade profile trailing edge point B or trailing edge point B and blade profile maximum ga(u)ge; The leading edge wing (1) and the trailing edge wing all with the suction surface wing (5) and smooth connection of the pressure side wing (3), the leading edge wing (1) and the trailing edge wing all are the extensions at leading edge place and trailing edge place of the suction surface wing (5) and the pressure side wing (3).
2, turbine as claimed in claim 1 or steam turbine movable vane tip vane is characterized in that, the described trailing edge wing is the smooth structure trailing edge wing (4) or the dovetail structure trailing edge wing (6).
3, turbine as claimed in claim 1 or steam turbine movable vane tip vane, it is characterized in that, the described pressure side wing (3) and the suction surface wing (5) width along its leading edge to trailing edge is identical or different, and it is shaped as the irregularly shaped of regular shape or free form surface structure.
4, turbine as claimed in claim 1 or steam turbine movable vane tip vane is characterized in that, the Placement of described tip vane and turbine or steam turbine movable vane adopts chamfering transition, round-corner transition or adopts the free form surface smooth transition.
5, turbine as claimed in claim 1 or steam turbine movable vane tip vane is characterized in that, the described suction surface wing (5) and the pressure side wing (3) use separately or be used in combination with other winglet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008100105169A CN101255800B (en) | 2008-02-28 | 2008-02-28 | Blade tip alula of turbine or steam turbine moving-blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008100105169A CN101255800B (en) | 2008-02-28 | 2008-02-28 | Blade tip alula of turbine or steam turbine moving-blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101255800A true CN101255800A (en) | 2008-09-03 |
| CN101255800B CN101255800B (en) | 2010-06-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008100105169A Active CN101255800B (en) | 2008-02-28 | 2008-02-28 | Blade tip alula of turbine or steam turbine moving-blade |
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| CN (1) | CN101255800B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103806950A (en) * | 2014-01-20 | 2014-05-21 | 北京航空航天大学 | Turbine blade provided with blade tip pressure surface trailing edge cutting structure |
| CN104763477A (en) * | 2015-04-13 | 2015-07-08 | 大连理工大学 | Partial shroud structure of tip of moving blade of turbo machine |
| CN103883361B (en) * | 2012-12-20 | 2016-05-04 | 中航商用航空发动机有限责任公司 | Turbo blade |
| JP2016156377A (en) * | 2015-02-25 | 2016-09-01 | ゼネラル・エレクトリック・カンパニイ | Turbine rotor blade |
| CN106368741A (en) * | 2016-11-09 | 2017-02-01 | 哈尔滨工业大学 | Blade with small wing rib blade tip and turbine utilizing blade |
| US9593584B2 (en) | 2012-10-26 | 2017-03-14 | Rolls-Royce Plc | Turbine rotor blade of a gas turbine |
| CN106762830A (en) * | 2017-02-13 | 2017-05-31 | 王雄彪 | A kind of low noise fan blade and the air-conditioner outdoor unit using the fan blade |
| CN107013248A (en) * | 2015-12-11 | 2017-08-04 | 通用电气公司 | Method and system for improving turbo blade performance |
| US9850764B2 (en) | 2014-02-28 | 2017-12-26 | Rolls-Royce Plc | Blade tip |
| CN112283161A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Axial compressor and compressor rotor blade thereof |
| CN112283162A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9951629B2 (en) | 2012-07-03 | 2018-04-24 | United Technologies Corporation | Tip leakage flow directionality control |
| US9957817B2 (en) * | 2012-07-03 | 2018-05-01 | United Technologies Corporation | Tip leakage flow directionality control |
| US9777582B2 (en) * | 2012-07-03 | 2017-10-03 | United Technologies Corporation | Tip leakage flow directionality control |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6779979B1 (en) * | 2003-04-23 | 2004-08-24 | General Electric Company | Methods and apparatus for structurally supporting airfoil tips |
| US7600977B2 (en) * | 2006-05-08 | 2009-10-13 | General Electric Company | Turbine blade tip cap |
| CN201180564Y (en) * | 2008-02-28 | 2009-01-14 | 大连海事大学 | Blade tip winglet of turbine or steamer movable blade |
-
2008
- 2008-02-28 CN CN2008100105169A patent/CN101255800B/en active Active
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9593584B2 (en) | 2012-10-26 | 2017-03-14 | Rolls-Royce Plc | Turbine rotor blade of a gas turbine |
| US10641107B2 (en) | 2012-10-26 | 2020-05-05 | Rolls-Royce Plc | Turbine blade with tip overhang along suction side |
| CN103883361B (en) * | 2012-12-20 | 2016-05-04 | 中航商用航空发动机有限责任公司 | Turbo blade |
| CN103806950A (en) * | 2014-01-20 | 2014-05-21 | 北京航空航天大学 | Turbine blade provided with blade tip pressure surface trailing edge cutting structure |
| US9850764B2 (en) | 2014-02-28 | 2017-12-26 | Rolls-Royce Plc | Blade tip |
| JP2016156377A (en) * | 2015-02-25 | 2016-09-01 | ゼネラル・エレクトリック・カンパニイ | Turbine rotor blade |
| CN104763477A (en) * | 2015-04-13 | 2015-07-08 | 大连理工大学 | Partial shroud structure of tip of moving blade of turbo machine |
| US10934858B2 (en) | 2015-12-11 | 2021-03-02 | General Electric Company | Method and system for improving turbine blade performance |
| CN107013248A (en) * | 2015-12-11 | 2017-08-04 | 通用电气公司 | Method and system for improving turbo blade performance |
| CN113266426A (en) * | 2015-12-11 | 2021-08-17 | 通用电气公司 | Method and system for improving turbine blade performance |
| CN106368741A (en) * | 2016-11-09 | 2017-02-01 | 哈尔滨工业大学 | Blade with small wing rib blade tip and turbine utilizing blade |
| CN106762830A (en) * | 2017-02-13 | 2017-05-31 | 王雄彪 | A kind of low noise fan blade and the air-conditioner outdoor unit using the fan blade |
| CN112283161A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Axial compressor and compressor rotor blade thereof |
| CN112283162A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
| CN112283161B (en) * | 2020-12-24 | 2021-03-16 | 中国航发上海商用航空发动机制造有限责任公司 | Axial compressor and compressor rotor blade thereof |
| CN112283162B (en) * | 2020-12-24 | 2021-03-26 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101255800B (en) | 2010-06-09 |
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