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A porous film hole exit and method for making same

An outlet area, porous structure technology, applied in the field of hole formation in turbine components, can solve problems such as difficult porous outlets

Inactive Publication Date: 2019-07-30
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

One problem with membrane pores produced by conventional methods is that it is difficult to generate porous outlets with this method

Method used

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  • A porous film hole exit and method for making same
  • A porous film hole exit and method for making same
  • A porous film hole exit and method for making same

Examples

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Embodiment Construction

[0023] Referring to the drawings, wherein like reference numerals designate like elements throughout the several views, figure 1 An exemplary turbine blade 10 is illustrated. The turbine blade 10 includes a conventional tenon 12, which may be of any suitable form, including a tongue that engages a complementary tongue to a groove in a rotor disc (not shown) for radially aligning the tenon as it rotates during operation. The blades 10 are held to the disc. Blade shank 14 extends radially upward from tenon 12 and terminates in a platform 16 that projects laterally outwardly from and surrounds shank 14 . A hollow airfoil 18 extends radially outward from platform 16 and into the hot gas flow. The airfoil has a root 19 at the junction of the platform 16 and the airfoil 18 and a tip 22 at its radially outer end. The airfoil 18 has a concave pressure sidewall 24 and a convex suction sidewall 26 joined together at a leading edge 28 and a trailing edge 31 .

[0024] The airfoil 18 ...

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PUM

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Abstract

A method of forming a cooling hole structure on a turbine component having a component wall with inner and outer surfaces, wherein a cooling hole passes through the component wall and fluidly connectsthe inner surface and the outer surface. The method includes the steps of forming a recess communicating with the hole and the outer surface; and using an additive manufacturing process to form a porous structure in the recess.

Description

technical field [0001] The present invention relates to hole formation in turbine components, and more particularly, to forming porous exit regions at the discharge ends of film cooling holes using an additive manufacturing process. Background technique [0002] Airfoils in turbine engines often include cooling holes for expelling a film of cooling air along the outer surface of the airfoil to effect film cooling. These may be referred to as "film cooling holes" or "film holes". [0003] Typically, cooling holes extend through a wall in the aircraft component from an inlet end to an outlet end. In some cooling holes, the outlet end is configured as a generally conical diffuser and positioned on a surface of the aircraft component having a leading edge and a trailing edge. It is sometimes desirable that the diffuser portion of the cooling hole is not tapered, but instead be configured so that the flow through the cooling hole is distributed into many small flow paths throug...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22F3/105B22F5/04B22F7/00B22F7/08F01D5/18
CPCB22F7/004B22F7/08F01D5/183F01D5/186F05D2230/10F05D2230/22F01D5/187B33Y10/00B33Y80/00B22F5/04F05D2230/31F05D2260/202Y02P10/25Y02T50/60B22F10/28B22F10/62B22F10/25B22F10/64B22F10/68B23P2700/06F01D5/28B28B1/001F05D2220/32
Inventor 罗纳德·斯科特·邦克
Owner GENERAL ELECTRIC CO