Sequential cooling insert for turbine stator vane

• US 8,684,668 B1
• Filed: 11/26/2012
• Issued: 04/01/2014
• Est. Priority Date: 11/13/2012
• Status: Active Grant

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Jones, Russell B, Krueger, Judson J, Plank, William L
• Primary Examiner(s): White, Dwayne J
• Application Number:
  US13/685,053
• Time in Patent Office: 491 Days
• Field of Search: 415/115, 415/116, 416/96.R, 416/97.R, 416/212.A
• US Class Current: 415/115
• 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: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F05D 2250/182 crenellated, notched
• CPC Class Codes: F05D 2250/183 zigzag
• CPC Class Codes: F05D 2250/184 sinusoidal
• CPC Class Codes: F05D 2250/191 perforated
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A sequential impingement cooling insert for a turbine stator vane that forms a double impingement for the pressure and suction sides of the vane or a triple impingement. The insert is formed from a sheet metal formed in a zigzag shape that forms a series of alternating impingement cooling channels with return air channels, where pressure side and suction side impingement cooling plates are secured over the zigzag shaped main piece. Another embodiment includes the insert formed from one or two blocks of material in which the impingement channels and return air channels are machined into each block.

Claims

1. An impingement cooling insert for a turbine stator vane of a gas turbine engine, the impingement cooling insert comprising:

a zigzag shaped main piece forming an alternating series of impingement cooling air channels and return air channels extending in a spanwise direction of a stator vane airfoil;

a pressure side wall secured to a pressure side of the zigzag shaped main piece;

a suction side wall secured to a suction side of the zigzag shaped main piece;

an inlet cover plate secured to a top side of the zigzag shaped main piece;

the top cover plate having cooling air supply openings that connect to the impingement cooling air channels;

a bottom cap secured to a bottom side of the zigzag shaped main piece to block off the impingement cooling air channels and the return air channels;

a row of impingement cooling air holes formed in the pressure side wall and connected to the impingement cooling air channels;

a row of return air holes formed in the pressure side wall and connected to the return air channels; and

,

a row of impingement cooling air holes formed in the suction side wall and connected to the return air channels.

2. The impingement cooling insert of claim 1, and further comprising:

the zigzag shaped main piece has flat surfaces on the pressure side and the suction side that form bonding surfaces for the pressure side wall and the suction side wall.

3. The impingement cooling insert of claim 1, and further comprising:

the zigzag shaped main piece forms converging shaped impingement cooling air channels and converging shaped return air channels in a direction of cooling air flow.

4. The impingement cooling insert of claim 1, and further comprising:

the bottom cap includes a slot on a bottom side;

a bottom cap receiver to be secured to an inner endwall of the stator vane;

ahe bottom cap receiver includes a rail on a top side that slides within the slot of the bottom cap to allow for a radial displacement of the bottom cap within the bottom cap receiver.

5. The impingement cooling insert of claim 1, and further comprising:

the zigzag shaped main piece forms diverging shaped impingement cooling air channels and diverging shaped return air channels in a direction of cooling air flow.

6. The impingement cooling insert of claim 3, and further comprising:

the rows of impingement cooling air holes are formed in the pressure side wall and the suction side wall and not in the zigzag shaped main piece; and

,

the return air holes are formed in the pressure side wall and the suction side wall and in the zigzag shaped main piece.

7. The impingement cooling insert of claim 1, and further comprising:

the pressure side wall and the suction side wall extend around both a forward side and an aft side of the zigzag shaped main piece with the pressure side wall secured to the suction side wall on the forward side and the aft side.

8. The impingement cooling insert of claim 7, and further comprising:

a forward radial extending seal groove on the forward side; and

,

an aft radial extending seal groove on the aft side.