CN104033251A - Gas film hole structure capable of improving high-temperature component cooling efficiency of gas turbine - Google Patents
Gas film hole structure capable of improving high-temperature component cooling efficiency of gas turbine Download PDFInfo
- Publication number
- CN104033251A CN104033251A CN201410259696.XA CN201410259696A CN104033251A CN 104033251 A CN104033251 A CN 104033251A CN 201410259696 A CN201410259696 A CN 201410259696A CN 104033251 A CN104033251 A CN 104033251A
- Authority
- CN
- China
- Prior art keywords
- film hole
- air film
- hole structure
- temperature component
- gas
- 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.)
- Pending
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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Abstract
The invention discloses a gas film hole structure. Two circular gas film holes are connected by virtue of a strip gap to form a gas film hole. The gas film hole structure disclosed by the invention is easy to process and low in cost; the intensity of a high-temperature component structure can be met; meanwhile, high cooling efficiency can be achieved.
Description
Technical field
The present invention proposes a kind of air film hole structure that improves high-temperature component of gas turbine cooling effectiveness, for gas turbine blower, firing chamber, turbine blade and end wall air film cooling technology and research and develop, be arranged in firing chamber, on the wall of turbine blade and end wall, realize the effective cooling to high-temperature component of gas turbine.
Background technique
At present, Gas Turbine inlet temperature reaches 1800～2200K, and far away higher than firing chamber, the fusing point of the parts such as turbine blade and end wall, therefore needs to adopt cooling technology to ensure the operation of gas turbine highly effective and safe.In the past in decades, the cooling gas turbine blower that is widely used in of air film, firing chamber, and on turbine blade.
In order to make air film uniform fold on high-temperature component surface, obtain higher cooling effectiveness, the structure of air film hole is very crucial.What nearly application decades was maximum is circular air film hole, but because circular air film hole exit momentum is higher, can produce reverse vortex pair, makes air film depart from wall, thereby causes mainstream gas to touch high-temperature component, and cooling effectiveness reduces.
Summary of the invention
The object of this invention is to provide a kind of air film hole structure that improves combustion machine high-temperature component cooling effectiveness, to improve the defect existing in known technology.
For achieving the above object, air film hole structure provided by the invention, is that two circular air film holes are stitched to connection by bar, forms an air film hole.
Air film hole structure of the present invention, easily processing, expense is cheap, meets high-temperature component structural strength, can also obtain higher cooling effectiveness simultaneously.
Brief description of the drawings
Fig. 1 is air film hole structural representation of the present invention.
Fig. 2 is the plan view of air film hole structure in Fig. 1.
Fig. 3 is known circular air film hole structure.
What in Fig. 4, A showed is the cooling effectiveness cloud atlas of known circular air film hole structure, and in Fig. 4, B is the cooling effectiveness cloud atlas of air film hole structure of the present invention.
What Fig. 5 showed is that known circular air film hole (▲) and the exhibition of air film hole of the present invention (■) downstream are compared schematic diagram to average gas film cooling efficiency.
Embodiment
The air film hole structure of raising high-temperature component of gas turbine cooling effectiveness provided by the invention, is known two circular air film holes to be stitched to W by bar connect, and forms a new air film hole (as illustrated in fig. 1 and 2).Although still can form reverse vortex pair from two circular ports air-flow out, offset each other, in the middle of adding, there is bar seam to connect, two circular hole air-flows are communicated, this also can weaken reverse vortex pair, thereby improves gas film cooling efficiency.Novel air fenestra is made up of two circular holes and a bar seam, and simple in structure, processing charges is cheap.
In order to investigate the cooling effectiveness of air film hole of the present invention, itself and known circular air film hole are contrasted.
Each circular air film hole diameter D of the present invention is 12.7mm, and air film hole length is 4D, and air film hole incident angle α is 30 °, and the distance of center circle H of two air film holes is 16.7mm, and the bar seam width W that connects two circular holes is 4mm.
As shown in Figure 3, air film hole diameter D is 12.7mm to known circular air film hole structure, and air film hole length is 4D, and air film hole angle [alpha] is 30 °, and air film hole spacing is 3D.
As can be seen from Figure 4, the cooling effectiveness of air film hole of the present invention is far above the cooling effectiveness of circular air film, and can keep in air film hole downstream higher level at a distance; Air film is opened up the situation to area coverage much larger than known circular air film hole.Compared with known circular air film hole, air film hole structure of the present invention more can well be protected blade surface.
What Fig. 5 showed is that open up to average gas film cooling efficiency in air film hole downstream.As can be seen from the figure,, compared with known circular air film hole structure, air film hole structure of the present invention makes cooling effectiveness improve 35.04%～44.96%.
Claims (1)
1. an air film hole structure, is that two circular air film holes are stitched to connection by bar, forms an air film hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410259696.XA CN104033251A (en) | 2014-06-12 | 2014-06-12 | Gas film hole structure capable of improving high-temperature component cooling efficiency of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410259696.XA CN104033251A (en) | 2014-06-12 | 2014-06-12 | Gas film hole structure capable of improving high-temperature component cooling efficiency of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104033251A true CN104033251A (en) | 2014-09-10 |
Family
ID=51464201
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410259696.XA Pending CN104033251A (en) | 2014-06-12 | 2014-06-12 | Gas film hole structure capable of improving high-temperature component cooling efficiency of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104033251A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4529358A (en) * | 1984-02-15 | 1985-07-16 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Vortex generating flow passage design for increased film cooling effectiveness |
| US4669957A (en) * | 1985-12-23 | 1987-06-02 | United Technologies Corporation | Film coolant passage with swirl diffuser |
| US6092982A (en) * | 1996-05-28 | 2000-07-25 | Kabushiki Kaisha Toshiba | Cooling system for a main body used in a gas stream |
| CN201218110Y (en) * | 2008-07-03 | 2009-04-08 | 西北工业大学 | Gas turbine cooling blade |
| EP2343435A1 (en) * | 2009-11-25 | 2011-07-13 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
| CN103806951A (en) * | 2014-01-20 | 2014-05-21 | 北京航空航天大学 | Turbine blade combining cooling seam gas films with turbulence columns |
-
2014
- 2014-06-12 CN CN201410259696.XA patent/CN104033251A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4529358A (en) * | 1984-02-15 | 1985-07-16 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Vortex generating flow passage design for increased film cooling effectiveness |
| US4669957A (en) * | 1985-12-23 | 1987-06-02 | United Technologies Corporation | Film coolant passage with swirl diffuser |
| US6092982A (en) * | 1996-05-28 | 2000-07-25 | Kabushiki Kaisha Toshiba | Cooling system for a main body used in a gas stream |
| CN201218110Y (en) * | 2008-07-03 | 2009-04-08 | 西北工业大学 | Gas turbine cooling blade |
| EP2343435A1 (en) * | 2009-11-25 | 2011-07-13 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
| CN103806951A (en) * | 2014-01-20 | 2014-05-21 | 北京航空航天大学 | Turbine blade combining cooling seam gas films with turbulence columns |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140910 |