Turbine vane with dirt separator

• US 8,142,153 B1
• Filed: 06/22/2009
• Issued: 03/27/2012
• Est. Priority Date: 06/22/2009
• 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): Look, Edward
• Assistant Examiner(s): DAVIS, JASON GREGORY
• Application Number:
  US12/489,030
• Time in Patent Office: 1,009 Days
• Field of Search: 416/1, 416/95, 416/96.A, 416/96.R, 416/97.R, 415/1, 415/115, 415/169.1, 415/209.4
• US Class Current: 416/1
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F05D 2250/185 serpentine-like
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/607 Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Abstract

A turbine stator vane with a cooling circuit that improves the cooling effectiveness of the airfoil as well as collects any dirt particles before passing the clean cooling an through the cooling circuit. The airfoil includes a 3-pass aft flowing serpentine circuit with a first leg located along the airfoil leading edge and connected to a showerhead arrangement for film cooling discharge. A cooling air supply channel is located between the first leg and the second leg of the serpentine flow circuit, and the cooling supply channel includes ribs arranged to produce a vortex flow within the cooling air that collects the dirt particles within a center of the vortex flow and deposits the dirt particles at the bottom of the channel. The vortex flow cooling air flows through impingement holes to produce impingement cooling on the backside wall of the leading edge with clean cooling air. The vortex flow pattern produces higher flow velocities at the outer periphery of the vortex which produces a higher impingement jet velocity of the cooling air to improve convection and impingement cooling capability.

Claims

1. An air cooled turbine stator vane comprising:

an outer endwall and an inner endwall;

an airfoil extending between the outer endwall and the inner endwall;

a 3-pass aft flowing serpentine flow cooling circuit formed within the airfoil to provide cooling;

the 3-pass serpentine circuit including a first leg located along the leading edge of the airfoil;

a cooling an supply channel positioned between the first leg and the second leg of the 3-pass serpentine circuit;

the cooling air supply channel having an arrangement of ribs along the walls to produce a vortex flow within the cooling supply air;

a row of impingement cooling holes between the cooling supply channel and the first leg of the serpentine circuit; and

,

a dirt collector pocket located on a bottom of the cooling air supply charnel.

2. The air cooled turbine stator vane of claim 1, and further comprising:

the first leg of the serpentine circuit includes a showerhead arrangement of film cooling holes.

3. The air cooled turbine stator vane of claim 1, and further comprising:

the first leg is connected to the second leg by an inner diameter turn channel; and

,

the second leg is connected to the third leg by an outer diameter turn channel.

4. The air cooled turbine stator vane of claim 1, and further comprising:

the last leg of the serpentine circuit is located adjacent to the trailing edge of the airfoil; and

,

a row of exit slots is connected to the last leg to discharge cooling air from the airfoil.

5. The air cooled turbine stator vane of claim 1, and further comprising:

the cooling air supply channel has a decreasing cross sectional flow area in a direction of the cooling air flow.

6. The air cooled turbine stator vane of claim 5, and further comprising:

the second leg of the serpentine circuit is located on the aft side of the cooling air supply channel and has a decreasing cross sectional flow area in a direction of the cooling air flow.

7. The air cooled turbine stator vane of claim 1, and further comprising:

the legs of the serpentine circuit each includes trip strips along the walls to increase a heat transfer coefficient form the walls to the cooling air flow.

8. A process for cooling a turbine stator vane and separating dirt particulates from the cooling air, the process comprising the steps of:

supplying pressurized cooling air to a cooling supply channel formed within the vane airfoil;

producing a vortex flow in the cooling air supply to collect any dirt particulates along a center of the vortex flow;

collecting the dirt particulates at a bottom of the vortex flow in the cooling supply channel;

impinging the vortex flowing cooling air against the backside wall of the airfoil leading edge;

discharging some of the spent impingement cooling air as film cooling air onto an outer surface of the airfoil leading edge; and

,

passing the dirt free and remaining spent impingement cooling air along a serpentine flow path to provide cooling for the remaining sections of the airfoil.

9. The process for cooling a turbine stator vane of claim 8, and further comprising the step of:

maintaining an outer periphery air flow velocity of the vortex flow cooling air by decreasing a cross sectional flow area of the cooling au supply channel while collecting the dirt particulates.

10. The process for cooling a turbine stator vane of claim 8, and further comprising the step of:

discharging the cooling air from the serpentine flow path through trailing edge cooling slots to cool the trailing edge region of the airfoil.