Airfoil with cooling passage providing variable heat transfer rate

• US 8,303,252 B2
• Filed: 10/16/2008
• Issued: 11/06/2012
• Est. Priority Date: 10/16/2008
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Piggush, Justin D.
• Primary Examiner(s): Summons, Barbara
• Application Number:
  US12/252,514
• Publication Number:
  US 20100098526A1
• Time in Patent Office: 1,482 Days
• Field of Search: 416/96.R, 416/96.A, 416/97.R, 415/115
• US Class Current: 416/97.R
• CPC Class Codes: B22C 9/10 Cores; Manufacture or installation of cores breaker cores B22C9/084
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2230/211 by precision casting, e.g. microfusing or investment casting
• CPC Class Codes: F05D 2250/25 helical
• CPC Class Codes: F05D 2250/90 Variable geometry
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/221 Improvement of heat transfer
• CPC Class Codes: Y10T 29/49341 with cooling passage

Abstract

A turbine engine airfoil includes an airfoil structure having a side with an exterior surface. The structure includes a cooling passage extending a length within the structure and providing a convection surface facing the side. The convection surface is twisted along the length, which varies a heat transfer rate between the exterior surface and the convection surface along the length. In one example, the cooling passage is provided by a refractory metal core that is used during the airfoil casting process. The core includes multiple legs joined by a connecting portion. At least one of the legs is twisted along its length. The legs are deformed toward one another opposite the connecting portion to provide a desired core shape that corresponds to the shape of the cooling passage. Accordingly, the cooling passage provides desired cooling of the airfoil.

Claims

1. A turbine engine airfoil comprising:

an airfoil structure including a side having an exterior surface, the structure having a cooling passage with a cross-sectional area provided by a width and a thickness, the width greater than the thickness, the cooling passage extending a length within the structure and providing a convection surface facing the side, the convection surface twisted along the length varying a heat transfer rate between the exterior surface and the convection surface along the length, wherein the convection surface twists less than one complete turn along the length.

2. The turbine engine airfoil according to claim 1, comprising a platform from which the airfoil structure extends, and a root extending from the platform opposite the airfoil structure.

3. The turbine engine airfoil according to claim 2, wherein the cooling passage extends in a direction from the platform to a tip of the airfoil structure.

4. The turbine engine airfoil according to claim 2, comprising a cooling channel extending along the length within the structure, the cooling passage arranged between the cooling channel and the exterior surface.

5. The turbine engine airfoil according to claim 1, wherein the cooling passage includes a generally uniform cross-sectional area along the length.

6. The turbine engine airfoil according to claim 5, wherein the cross-sectional area is generally rectangular in shape.

7. The turbine engine airfoil according to claim 1, wherein the cooling passage includes an arcuate cross-sectional shape.

8. The turbine engine airfoil according to claim 1, comprising a wall between the exterior surface and the convection surface, the wall having a greater volume away from a tip of the airfoil structure than in closer proximity to the tip.

9. The turbine engine airfoil according to claim 8, wherein the cooling passage includes a cross-sectional area perpendicular to a radial direction of the airfoil structure, the convection surface of the cross-sectional area including a first portion at a first distance from the exterior surface and a second portion at a second distance from the exterior surface, the second distance greater than the first distance.

10. The turbine engine airfoil according to claim 1, comprising multiple cooling passages interconnected by a connecting portion.

11. A turbine engine airfoil comprising:

an airfoil structure including a side having an exterior surface, the structure having a cooling passage with a cross-sectional area provided by a width and a thickness, the width greater than the thickness, the cooling passage extending a length within the structure and providing a convection surface facing the side, the cooling passage separated from the exterior surface by a wall, the convection surface having a generally uniform width, the convection surface at a first distance from the exterior surface at a first location along the length and at a second distance greater than the first distance at a second location along the length, wherein the convection surface twists less than one complete turn along the length.

12. The turbine engine airfoil according to claim 11, wherein the side is a suction side of the airfoil.

13. The turbine engine airfoil according to claim 11, wherein the cooling passage extends radially along the airfoil structure from a platform toward a tip.