METHOD OF FORMING COOLING HOLES AND TURBINE AIRFOIL WITH HYBRID-FORMED COOLING HOLES

• US 20090169394A1
• Filed: 12/28/2007
• Published: 07/02/2009
• Est. Priority Date: 12/28/2007
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Danowski, Michael, Zurawka, John, Perez, Carlos Walberto, Crow, John
• Application Number:
  US11/965,859
• Publication Number:
  US 20090169394A1
• Time in Patent Office: Days
• US Class Current: 416/96.R
• CPC Class Codes: B23H 9/10 Working turbine blades or nozzles
• CPC Class Codes: B23K 2101/001 Turbines
• CPC Class Codes: B23K 26/0093 combined with mechanical machining or metal-working covered by other subclasses than B23K combined welding or cutting procedures or apparatus B23K28/02
• CPC Class Codes: B23K 26/389 of fluid openings, e.g. nozzles, jets laser machining of inkjet nozzles B41J2/1634
• CPC Class Codes: B23P 2700/06 Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F05D 2230/12 by spark erosion methods
• CPC Class Codes: F05D 2230/13 using lasers
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F23R 2900/00018 Manufacturing combustion chamber liners or subparts
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes

Abstract

A method of forming a cooling hole in a workpiece that includes the steps of laser-forming a blind, inwardly-tapering transition opening into a first side of the workpiece, and EDM-forming a generally cylindrical through hole to a second, opposing side of the workpiece communicating with the inwardly-tapering transition opening to form a through cooling hole communicating with the first and second sides of the workpiece. An airfoil having cooling holes formed by use of both laser and EDM is also disclosed.

Claims

1. A method of forming a cooling hole in a workpiece, comprising the steps of laser-forming a blind, inwardly-tapering transition opening into a first side of the workpiece, and EDM-forming a generally cylindrical through hole to a second, opposing side of the workpiece communicating with the inwardly-tapering transition opening to form a through cooling hole communicating with the first and second sides of the workpiece.

2. A method according to claim 1, wherein the workpiece comprises an airfoil, and the step of forming the transition opening comprises the step of forming a diffuser section of the cooling hole, and the step of forming the generally cylindrical through hole comprises the step of forming a metering section of the cooling hole.

3. A method according to claim 1, wherein the method of forming the diffuser section includes the step of forming the diffuser section with a conical configuration.

4. A method according to claim 1, and including the step of using an inner end of the transition opening as a guide for EDM formation of the cylindrical through hole.

5. A method according to claim 1, wherein the step of forming the transition opening is performed before the step of forming the cylindrical through hole.

6. A method according to claim 1, wherein the step of forming the transition opening is performed after the step of forming the cylindrical through hole.

7. A method of forming a plurality of cooling holes in a turbine airfoil of the type having a leading edge and an axially spaced-part trailing edge, the leading edge having an axially-extending aerodynamic external surface curvature, a root and a tip spaced-apart along a radially-extending span axis, a pressure sidewall and a laterally-spaced-apart suction sidewall, a cooling circuit positioned between the pressure sidewall and the suction sidewall for channeling a fluid flow for cooling the airfoil, comprising the steps of laser-forming a plurality of blind, inwardly-tapering diffuser sections into a first side of the workpiece, and EDM-forming a generally cylindrical through metering section to a second, opposing side of the workpiece communicating with the inwardly-tapering transition opening to form a through cooling hole communicating with the first and second sides of the workpiece.

8. A method according to claim 7, and including the step of using an inner end of the diffuser secton as a guide for EDM formation of the metering section.

9. A method according to claim 7, wherein the step of forming the diffuser section is performed before the step of forming the metering section.

10. A method according to claim 7, wherein the step of forming the diffuser section is performed after the step of forming the metering section.

11. An airfoil, comprising:

(a) a leading edge and an axially spaced-part trailing edge, the leading edge having an axially-extending external surface curvature;

(b) a root and a tip spaced-apart along a radially-extending span axis;

(c) a pressure sidewall and a laterally-spaced-apart suction sidewall;

(d) a cooling circuit positioned between the pressure sidewall and the suction sidewall for channeling a fluid flow for cooling the airfoil;

(e) a plurality of cooling holes formed in the leading edge along the span axis of the airfoil in fluid communication with the cooling circuit, at least some of the cooling holes having a diffuser section communicating with the leading edge surface, the diffuser section having opposed walls defining an exit opening on the surface of the leading edge and a respective cylindrical metering section positioned between and communicating with the interior of the airfoil and the diffuser section, wherein the diffuser section is formed by laser and the cylindrical metering section is formed by EDM.

12. An airfoil according to claim 11, wherein the airfoil is a gas turbine airfoil.

13. An airfoil according to claim 11, wherein at least some of the diffuser sections have opposed walls defining a generally quadralinear exit opening on the external surface, and at least some of the diffuser walls have a convex curvature that approximately matches the external surface curvature of the airfoil local to the cooling hole whereby fluid flow from the fan hole exit is evenly dispersed and spread along land portions of the external surface of the airfoil adjacent to the cooling holes, and the diffuser section has opposed walls defining an exit opening on the surface of the leading edge and a respective cylindrical metering section positioned between and communicating with the interior of the airfoil and the diffuser section and defining a longitudinal axis that diverges from a radius of the leading edge, wherein the diffuser section is formed by laser and the cylindrical metering section is formed by EDM.