Process for cooling a turbine blade trailing edge

• US 8,052,392 B1
• Filed: 07/07/2011
• Issued: 11/08/2011
• Est. Priority Date: 12/15/2008
• Status: Expired due to Fees

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Liang, George
• Primary Examiner(s): Bryant; Kiesha
• Assistant Examiner(s): TORNOW, MARK W
• Application Number:
  US13/177,847
• Time in Patent Office: 124 Days
• Field of Search: 416/1, 416/96.R, 416/97.R, 415/115
• US Class Current: 416/97.R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: F05D 2240/127 Vortex generators, turbulators, or the like, for mixing by creating turbulence F05D2260/2212
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127

Abstract

A turbine airfoil with a trailing edge cooling circuit that includes a row of pressure side bleed channels connected to a metering and impingement cooling circuit that discharges a layer of film cooling air out through a row of exit slots that open onto a pressure side wall of the trailing edge to provide cooling for the trailing edge region of the airfoil. Formed within the trailing edge tip is a vortex flow chamber extending the length of the airfoil and connected to the bleed channels by a row of inlet holes to draw a portion of the film cooling air into the vortex chamber to provide cooling for the trailing edge tip and to prevent the film cooling layer from breaking off from the pressure side wall. The vortex chamber is connected to a row of exit holes offset from the inlet holes to form the vortex flow and to discharge the vortex flowing cooling air out the trailing edge in a direction parallel to the suction side wall.

Claims

1. A process for cooling a trailing edge of a turbine airfoil comprising the steps of:

passing cooling air through a mid-chord region of the airfoil;

metering cooling air from the mid-chord region through the trailing edge region;

discharging a layer of film cooling air onto a pressure side surface of the trailing edge of the airfoil;

drawing in a portion of the film cooling air inside the airfoil to cool a trailing edge tip of the airfoil; and

,

discharging the drawn in cooling air out the trailing edge of the airfoil.

2. The process for cooling a trailing edge of a turbine airfoil of claim 1, and further comprising the step of:

forming a vortex flow with the drawn in air to increase the heat transfer from the metal to the cooling air.

3. The process for cooling a trailing edge of a turbine airfoil of claim 2, and further comprising the step of:

discharging the vortex flowing cooling air out the trailing edge in a direction parallel to the suction side wall of the airfoil.

4. The process for cooling a trailing edge of a turbine airfoil of claim 1, and further comprising the step of:

the step of drawing in the cooling air includes sucking in a boundary layer to prevent the film layer from breaking away from the pressure side wall of the airfoil at the trailing edge.

5. The process for cooling a trailing edge of a turbine airfoil of claim 2, and further comprising the step of:

discharging the layer of film cooling air at a high enough pressure to cause a portion of the cooling air to be drawn into the trailing edge vortex flow.