Gas turbine airfoil film cooling hole

Inactive Publication Date: 2006-04-06
ALSTOM TECH LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0006] It is an object of the invention to provide a cooling construction for the suction side of a gas turbine a

Problems solved by technology

One problem encountered in the design of the gas turbine airfoils is caused by particles entrained in the hot gas flow.
During engine operation small particles remain entrained in the gas flow while larger and heavier particles impinge on the airfoil surface and can cause local impact damage.
This problem is en

Method used

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  • Gas turbine airfoil film cooling hole
  • Gas turbine airfoil film cooling hole
  • Gas turbine airfoil film cooling hole

Examples

Experimental program
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Embodiment Construction

[0023]FIG. 1 shows a typical airfoil 1 of a gas turbine extending from a root 2 to a tip 3 and frown a leading edge 4 to a trailing edge 5. The figure shows the airfoil from its suction side 6. Several film cooling holes 7 are arranged In radially extending rows 8a, 8b, and 8c on the suction side 6. The film cooling holes 7 are realized with diffused sidewalls resulting in an irregularly shaped exit port 9 as shown in an enlarged view in FIG. 1a.

[0024] The film cooling holes extend from internal cooling passages within the airfoil 1 through the suction sidewall 6 to its outer surface 11. They provide convective cooling of the sidewall from within as well as film cooling of the sidewall outer surface 11.

[0025] In one embodiment of the invention the film cooling holes with diffused sidewalls are arranged in one or more radially extending rows on the suction side of the airfoil.

[0026] The number of rows of film cooling holes and their position is determined based on the metal temper...

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Abstract

A gas turbine airfoil (1) with a pressure sidewall and a suction sidewall (6) comprises several internal cooling passages, through which cooling air flows, and several film cooling holes (7) that extend from the internal cooling passages to the outer surface (11) of the suction sidewall (6). According to the invention the film cooling holes (7) are oriented in the radial outward direction as well as toward the trailing edge of the airfoil (1). They each comprise a diffused section with sidewalls that are diffused in the radial outward direction, in the radial inward direction as well as toward downstream direction. Cooling air flowing through the diffused film cooling hole (7) onto the outer surface (6) of the airfoil (1) forms an air curtain preventing plugging of the film cooling hole by particles entrained in the hot gas flow.

Description

FIELD OF INVENTION [0001] This invention pertains to gas turbine airfoils and in particular to a cooling construction with film cooling holes and the prevention of contamination and plugging of the film cooling holes. BACKGROUND ART [0002] The airfoils of gas turbines, turbine rotor blades and stator vanes, require extensive cooling in order to keep the metal temperature below a certain allowable level and prevent damage due to overheating from the hot gas flow. Typically, such airfoils are designed with hollow spaces and a plurality of passages and cavities within the airfoil for cooling fluid to flow through. The cooling fluid is typically air bled from the compressor having a higher pressure and lower temperature compared to the gas traveling through the turbine. The higher pressure forces the air through the cavities and passages as it transports the heat away from the airfoil walls. The cooling construction further comprises film cooling holes leading from the hollow spaces wit...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/186F05D2250/314F05D2250/324
Inventor LIANG, GEORGE
Owner ALSTOM TECH LTD
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