Airfoil showerhead pattern apparatus and system

Patent metadata

Field	Value
Publication number	US-9976423-B2
Application number	US-201514862422-A
Country	US
Kind code	B2
Filing date	Sep 23, 2015
Priority date	Dec 23, 2014
Publication date	May 22, 2018
Grant date	May 22, 2018

Abstract

The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.

First claim

What is claimed is:

1. A gas turbine component having a showerhead cooling hole comprising:
a row of radially disposed showerhead cooling holes,
wherein the row of radially disposed showerhead cooling holes are configured to alter a vector of cooling air to align with a cooling flow streamline towards a leading edge nose of the gas turbine component,
wherein the row of radially disposed showerhead cooling holes is disposed on a high lift airfoil comprising a Zweifel lift coefficient of greater than 1.1.

2. The gas turbine component having the showerhead cooling hole of claim 1 , wherein the showerhead cooling hole is located on at least one of the leading edge, pressure side, or suction side of the gas turbine component.

3. The gas turbine component having the showerhead cooling hole of claim 1 , wherein the row of radially disposed showerhead cooling holes is disposed on a leading edge of at least one component.

4. The gas turbine component having the showerhead cooling hole of claim 1 , wherein the gas turbine component, including the row of radially disposed showerhead cooling holes, is formed through at least one of an additive manufacturing process or and electric discharge machining process.

5. The gas turbine component having the showerhead cooling hole of claim 1 , wherein the row of radially disposed showerhead cooling holes are curved to orient a flow of cooling air out the showerhead cooling hole in a direction closely aligned with the cooling flow streamline.

6. The gas turbine component having the showerhead cooling hole of claim 1 , wherein the row of radially disposed showerhead cooling holes are configured to alter the vector of cooling air to align with the cooling flow streamline towards a suction side.

7. The gas turbine component having the showerhead cooling hole of claim 1 , wherein the gas turbine component is a turbine blade.

8. An airfoil component comprising:
an airfoil portion that bounds void, wherein the void comprises a cooling hole, wherein the cooling hole comprises a diffusion angle, wherein the cooling hole is configured to alter a vector of cooling air to align with a cooling flow streamline towards a leading edge of the airfoil component, and wherein the cooling hole is located in close proximity to the leading edge of the airfoil component,
wherein the airfoil component is a high lift airfoil comprising a Zweifel lift coefficient of greater than 1.1.

9. The airfoil component of claim 8 , wherein the cooling hole is configured to alter the vector of cooling air away from a suction side or pressure side stagnation zone.

10. The airfoil component of claim 8 , wherein a stagnation zone and the leading edge of the high lift airfoil are offset.

11. The airfoil component of claim 8 , wherein the airfoil component is formed through at least one of an additive manufacturing process or and electric discharge machining process.

12. The airfoil component of claim 8 , wherein the airfoil component is a turbine blade.

13. A method of vectoring cooling air flow comprising:
disposing a row of a plurality of cooling holes radially on an airfoil component; and
orienting a breakout of a cooling hole of the plurality of cooling holes at an angle to substantially align the angle with a direction of a cooling flow streamline,
wherein the airfoil component is part of a high lift airfoil, wherein the high lift airfoil comprises a Zweifel lift coefficient of greater than 1.1.

14. The method of claim 13 , wherein the airfoil component is a turbine blade.

15. The method of claim 13 , further comprising altering a vector of a cooling air streamline away from at least one of a suction side or pressure side stagnation zone.

Assignees

• United Technologies Corp

Inventors

• Quach San
• King Christopher
• Gautschi Steven Bruce
• Candelori David J

Classifications

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2240/306

  related to the suction side of a rotor blade · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2240/305

  related to the pressure side of a rotor blade · CPC title