Cooled vane cluster

• US 20050135923A1
• Filed: 12/22/2003
• Published: 06/23/2005
• Est. Priority Date: 12/22/2003
• Status: Abandoned Application

• 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: Pietraszkiewicz, Edward, Coons, Todd
• Application Number:
  US10/743,516
• Publication Number:
  US 20050135923A1
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2230/12 by spark erosion methods
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2260/202 by film cooling

Abstract

A cast vane cluster with enhanced cooling contains an inner and an outer platform and at least two airfoils for directing a primary fluid stream axially rearward. A duct is bounded by inner, an outer endwall surfaces, and adjacent airfoil fluid directing surfaces. One or more cooling holes in the duct are drilled using an electrodischarge machine (EDM) method without a line of sight from the drilling equipment to the cooling hole location. One or more cooling holes, located in portions of the duct, may not be visible when viewed from an external location. Additionally, one or more cooling holes may only have an outlet cross sectional area visible when viewed along a longitudinal axis from an external location.

Claims

1. A vane cluster comprising:

An inner platform including an inner endwall surface and an inboard cavity;

An outer platform including an outer endwall surface and an outer cavity wherein said outer platform is spaced radially outboard of said inner platform and said outer endwall surface faces said inner endwall surface;

At least two airfoils spanning between said inner and outer endwall surfaces, each including a concave surface, a convex surface, a leading edge and a trailing edge located axially rearward of said leading edge, wherein said concave and convex surfaces of adjacent airfoils face each other;

A duct bounded by said adjacent concave and convex surfaces and said inner and outer endwall surfaces;

At least one hole including an inlet cross sectional area and an outlet cross sectional area; and

wherein said at least one hole outlet cross sectional area is located on said duct boundary.

2. A vane cluster comprising:

An inner platform including an inner endwall surface and an inboard cavity;

An outer platform including an outer endwall surface and an outer cavity wherein said outer platform is spaced radially outboard of said inner platform and said outer endwall surface faces said inner endwall surface;

At least two airfoils spanning between said inner and outer endwall surfaces, each including a concave surface, a convex surface, a leading edge and a trailing edge located axially rearward of said leading edge, wherein said concave and convex surfaces of adjacent airfoils face each other;

A duct bounded by said adjacent concave and convex surfaces and said inner and outer endwall surfaces;

At least one hole including an inlet cross sectional area and an outlet cross sectional area; and

wherein said at least one hole is not visible when viewed from a location external of said duct region.

3. The vane cluster of claim 2 wherein said external location is axially rearward of said trailing edges.

4. The vane cluster of claim 2 wherein said external location is axially forward of said leading edges.

5. A vane cluster comprising:

An inner platform including an inner endwall surface and an inboard cavity;

An outer platform including an outer endwall surface and an outer cavity wherein said outer platform is spaced radially outboard of said inner platform and said outer endwall surface faces said inner endwall surface;

At least two airfoils spanning between said inner and outer endwall surfaces, each including a concave surface, a convex surface, a leading edge and a trailing edge located axially rearward of said leading edge, wherein said concave and convex surfaces of adjacent airfoils face each other;

A duct bounded by said adjacent concave and convex surfaces and said inner and outer endwall surfaces;

A duct inlet area bounded by said at least two airfoil leading edges, said inner endwall surface and said outer endwall surface;

A duct outlet area bounded by said at least two airfoil trailing edges, said inner endwall surface and said outer endwall surface;

At least one hole including an inlet cross sectional area, an outlet cross sectional area, a bore extending between said inlet and said outlet areas wherein said bore has a central, longitudinal axis; and

Wherein said at least one outlet cross sectional area is located on said duct boundary and said at least one inlet cross sectional area is not visible when viewed along said longitudinal axis from an external location.

6. The vane cluster of claim 5 wherein said external location is located forward of said duct inlet area.

7. The vane cluster of claim 5 wherein said external location is located rearward of said duct outlet area.

8. The vane cluster of claim 5 further comprising at least one hollow passage, extending through an airfoil, said at least one hollow passage, communicating with said inboard and outboard cavities and forming an internal airfoil surface.

9. The vane cluster of claim 8 wherein said at least one hole inlet cross sectional area is located on said internal airfoil surface.

10. The vane cluster of claim 9 wherein said at least one hole is formed using an electrodischarge machine method.

11. The vane cluster of claim 10 wherein said at least one hole outlet cross sectional area is circular shaped.