Turbine blade with trailing edge cooling

• US 8,043,060 B1
• Filed: 06/07/2011
• Issued: 10/25/2011
• Est. Priority Date: 12/15/2008
• Status: Expired due to Fees

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• 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:
  US13/154,506
• Time in Patent Office: 140 Days
• Field of Search: 416/96.R, 416/97.R
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/2214 by increasing the heat transfer surface

Abstract

A turbine rotor blade with a trailing edge cooling circuit in which cooling air from an impingement cavity located adjacent to the trailing edge region is connected to a plurality of metering channels that open onto the pressure side wall of the trailing edge region of the airfoil to discharge the cooling air. A row of submerged slots that open onto the suction side wall of the airfoil are connected to the metering channels by a row of small holes that bleed off the cooling air in the metering channel in a progressive manner and discharge the air into the slot. The trailing edge cooling circuit allows for a thinner trailing edge airfoil, reduces the metal temperature and reduces the shear mixing between the cooling air and the mainstream hot gas flow.

Claims

1. A process for cooling a trailing edge region of a turbine rotor blade, the turbine rotor blade having an impingement cavity located adjacent to the trailing edge region of the airfoil of the blade to supply cooling air, the process comprising:

metering cooling air from the impingement cavity along the trailing edge region of the airfoil;

bleeding off a portion of the metering cooling air through a plurality of holes and discharging the air along a slot extending along the suction side wall of the trailing edge region; and

,

discharging the remaining metering air out onto the pressure side wall of the trailing edge region of the airfoil.

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

progressively bleeding off the metering air and into the suction side slot as the metering air flows down the trailing edge region of the airfoil.

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

bleeding off the metering air along the length of the trailing edge region of the airfoil.

4. The process for cooling a trailing edge region of claim 2, and further comprising the step of:

metering the cooling air from the impingement cavity and bleeding off a portion of the metering air along the entire airfoil length in the spanwise direction.

5. The process for cooling a trailing edge region of claim 4, and further comprising the step of:

associating each suction side slot with a separate metering channel.