CN109372583B - Turbine rotor blade with streamline boss - Google Patents
Turbine rotor blade with streamline boss Download PDFInfo
- Publication number
- CN109372583B CN109372583B CN201811503003.1A CN201811503003A CN109372583B CN 109372583 B CN109372583 B CN 109372583B CN 201811503003 A CN201811503003 A CN 201811503003A CN 109372583 B CN109372583 B CN 109372583B
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- China
- Prior art keywords
- boss
- blade
- turbine rotor
- rotor blade
- streamline
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- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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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
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a turbine rotor blade with a streamline boss, which is characterized in that the boss 2 is arranged below 10% of the relative blade height of a turbine rotor blade 1 and at the maximum thickness position of the blade, the boss 2 is streamline, the boss 2 is tangent to the outer contour line of the turbine rotor blade 1, the length of the boss 2 in the axial direction of the turbine rotor blade 1 is 15-30% of the axial chord length of the blade, and the thickness of the boss 2 in the radial direction of the turbine rotor blade 1 is 0.2-1% of the relative blade height. The technical scheme of the invention is simple to implement and has little influence on the strength of the blade; the flow loss is low.
Description
The technical field is as follows:
the invention belongs to the technical field of aero-engines and gas turbines, and particularly relates to a turbine rotor blade with a streamline boss.
Background
In a turbine rotor blade channel, due to the existence of a transverse pressure gradient, a strong channel vortex system is formed in the channel by an attachment surface layer, the channel vortex system develops along the radial direction and influences the flow of a large part of blade height at the root of the blade, and when sealing air enters from a rotor inlet, the sealing air flow further strengthens the channel vortex system, so that greater loss is generated and the turbine performance is influenced.
Conventional flow control for turbine rotor blade tip regions has typically taken the form of non-axisymmetric endwalls. But the measure has poor control effect on the condition with the sealing gas. The blade body vane which is used conventionally brings about great flow loss and blade stress while controlling the radial development of the channel vortex, so that the blade body vane is not applied to aeroengines and gas turbines.
The invention content is as follows:
the purpose of the invention is as follows:
in order to solve the problem of flow control of the traditional turbine rotor blade end area, the turbine rotor blade with the streamline boss is provided.
The technical scheme is as follows:
a turbine rotor blade with a streamline boss is characterized in that the boss 2 is arranged below 10% of the relative blade height of a turbine rotor blade 1 and at the position of the maximum thickness of the blade, the boss 2 is streamline, the boss 2 is tangent to the outer contour line of the turbine rotor blade 1, the length of the boss 2 in the axial direction of the turbine rotor blade 1 is 15-30% of the axial chord length of the blade, and the thickness of the boss 2 in the radial direction of the turbine rotor blade 1 is 0.2-1% of the relative blade height.
The boss 2 and the turbine rotor blade 1 are made of the same material and are integrally cast and formed with the turbine rotor blade 1.
The length of the boss 2 is 20% of the axial chord length of the blade.
The boss 2 is 0.8% of the relative leaf height in thickness.
Advantageous effects
The technical scheme of the invention is simple to implement and has little influence on the strength of the blade; the flow loss is low.
Drawings
Fig. 1 is a front view of the structure of the technical solution of the present invention.
Fig. 2 is a schematic perspective view of the structure of the technical solution of the present invention.
Fig. 3 is a schematic view of the flow principle of the prior art.
Fig. 4 is a flow control schematic of the present invention.
Wherein, 1-turbine rotor blade, 2-boss, 3-lower end wall channel vortex; 4-boss circumfluence vortex.
Detailed Description
The technical scheme of the invention is described in detail in the following with the accompanying drawings of the specification.
In a specific embodiment of the present invention, as shown in fig. 1, the height of the turbine rotor blade 1 is 63mm, and the axial chord length of the blade is 37.5mm, so that, at a position 5.04mm from the bottom of the turbine rotor blade 1 (8% of the relative blade height), at the maximum thickness position of the blade, the boss 2 is provided, the boss 2 is tangential to the outer contour line of the turbine rotor blade 1 and is integrally cast with the blade, and the length of the boss 2 is 7.5mm (20% of the axial chord length of the blade), and the thickness is 0.5mm (0.8% of the relative blade height).
Without the technical scheme of the invention, as shown in fig. 3, the lower end wall channel vortex 3 is very strong, the influence range of the lower end wall channel vortex in the section of 0.45 time of axial chord length from the trailing edge of the blade is about 30 percent of the relative blade height, after the streamline boss 2 is arranged, as shown in fig. 4, the radial flow of the lower end wall channel vortex 3 is blocked, meanwhile, a boss vortex 4 is generated behind the boss, the boss vortex 4 further inhibits the radial development of the channel vortex in the blade channel, and the influence range of the lower end wall channel vortex in the section of 0.45 time of axial chord length from the trailing edge of the blade is about 20 percent of the relative blade height, so that the beneficial effect of 10 percent is seen, and the purpose of reducing the flow loss is achieved.
Claims (3)
1. A turbine rotor blade with a streamline boss is characterized in that the boss (2) is arranged below 10% of the relative blade height of the turbine rotor blade (1), the boss (2) is streamline, the boss (2) is tangent to the outer contour line of the turbine rotor blade (1), the length of the boss (2) in the axial direction of the turbine rotor blade (1) is 15-30% of the axial chord length of the blade, and the thickness of the boss (2) in the radial direction of the turbine rotor blade (1) is 0.2% -1% of the relative blade height; the boss (2) and the turbine rotor blade (1) are made of the same material and are integrally cast and molded with the turbine rotor blade (1).
2. The turbine rotor blade with the streamline boss according to claim 1 is characterized in that the length of the boss (2) is 20% of the axial chord length of the blade.
3. A turbine rotor blade with a streamlined boss according to claim 1, wherein the boss (2) has a thickness of 0.8% relative blade height.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811503003.1A CN109372583B (en) | 2018-12-10 | 2018-12-10 | Turbine rotor blade with streamline boss |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811503003.1A CN109372583B (en) | 2018-12-10 | 2018-12-10 | Turbine rotor blade with streamline boss |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109372583A CN109372583A (en) | 2019-02-22 |
| CN109372583B true CN109372583B (en) | 2022-02-01 |
Family
ID=65372892
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811503003.1A Active CN109372583B (en) | 2018-12-10 | 2018-12-10 | Turbine rotor blade with streamline boss |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109372583B (en) |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4346412B2 (en) * | 2003-10-31 | 2009-10-21 | 株式会社東芝 | Turbine cascade |
| EP2031241A1 (en) * | 2007-08-29 | 2009-03-04 | Lm Glasfiber A/S | Blade for a rotor of a wind turbine provided with barrier generating means |
| KR20140028593A (en) * | 2012-08-29 | 2014-03-10 | 삼성중공업 주식회사 | Wind turbine generator |
| RS62876B1 (en) * | 2013-09-02 | 2022-02-28 | Wobben Properties Gmbh | Vortex generator for a wind turbine |
| DE102014203442A1 (en) * | 2013-11-04 | 2015-05-07 | Senvion Se | Rotor blade of a wind turbine and wind turbine |
| DE102014106529B4 (en) * | 2014-05-09 | 2016-02-04 | Senvion Gmbh | Repair procedure for vortex generator and a kit for it |
| US10253637B2 (en) * | 2015-12-11 | 2019-04-09 | General Electric Company | Method and system for improving turbine blade performance |
| CN108105152B (en) * | 2017-12-11 | 2024-05-14 | 珠海格力电器股份有限公司 | Cross-flow fan blade, cross-flow fan blade, indoor unit and air conditioner |
-
2018
- 2018-12-10 CN CN201811503003.1A patent/CN109372583B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109372583A (en) | 2019-02-22 |
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