High temperature airfoil

• US 6,322,322 B1
• Filed: 09/25/2000
• Issued: 11/27/2001
• Est. Priority Date: 07/08/1998
• Status: Expired due to Term

• Current Assignee: Rolls-Royce North American Technologies Incorporated
• Original Assignee: Rolls-Royce North American Technologies Incorporated
• Inventors: Rhodes, Jeffrey F., Harvey, Jon D.
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US09/668,916
• Time in Patent Office: 428 Days
• Field of Search: 416/224, 416/229.R, 416/229.A, 416/230, 416/241.R, 416/241.B, 416/95, 416/96.R, 416/96.A, 416/97.R, 416/131, 416/132.R, 416/140, 415/115, 415/191, 415/200, 244/132, 244/123, 403/381, 403/353, 298/897.1, 298/900.1, 294/28
• US Class Current: 415/191
• CPC Class Codes: F01D 11/008 by spacer elements between the blades, e.g. independent interblade platforms
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F01D 5/3084 the blades being made of ceramics
• CPC Class Codes: F16B 2200/30 Dovetail-like connections
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49337 Composite blade
• CPC Class Codes: Y10T 29/49826 Assembling or joining
• CPC Class Codes: Y10T 403/362 Nonaligned axes

Abstract

A high temperature repairable airfoil having a plurality of flow path cover tiles coupled to a single crystal spar member. In one embodiment, the plurality of flow path cover tiles include an attachment portion that is received within a groove formed in the outer surface of the spar. The attachment portion slides into a retaining feature within the groove so as to limit movement of the plurality of flow path cover tiles. Upon rotation of the airfoil, the plurality of flow path cover tiles become centrifugally loaded with a portion of the spar member. In one embodiment, the plurality of flow path cover tiles are formed of a material selected from the group consisting of ceramics, intermetallic, and thermal barrier coated single crystal alloy material.

Claims

1. A gas turbine engine vane, comprising:

a structural member positioned within an airfoil shaped apparatus, the apparatus having an exterior surface, at least a portion of the exterior surface including a cover member;

wherein one of the cover member and the structural member has a mating portion and the other of the cover member and the structural member has a corresponding receiving portion, the mating portion having a plurality of spaced protruding elements extending therefrom; and

the receiving portion defines a groove with a first portion and a second portion, the first portion having a width at least as wide as the protruding elements, the second portion having a width less than the width of the protruding elements, wherein the plurality of spaced protruding elements are positionable within the second portion to couple the cover member to the structural member.

2. The vane of claim 1, wherein the structural member has the receiving portion formed therein and the cover member includes the mating portion, and wherein the structural member defines a spar.

3. The vane of claim 2, wherein the structural member is formed of a super-alloy material.

4. The vane of claim 3, wherein the structural member is a single crystal.

5. The vane of claim 1, wherein the groove includes a centerline, and wherein the plurality of spaced protruding elements are aligned substantially parallel to the centerline.

6. The vane of claim 1, wherein the groove is linear.

7. The vane of claim 1, wherein the groove is non-linear.

8. The vane of claim 7, wherein the non-linear groove includes a plurality of discrete groove portions, and wherein each of the plurality of groove portions has a centerline.

9. The vane of claim 8, wherein the exterior surface is defined by a plurality of the cover members, and wherein at least one of the plurality of cover members has a spanwise length different than the spanwise length of the other of the plurality of cover members.

10. The vane of claim 9, wherein the groove portions have different spanwise lengths.

11. A gas turbine engine vane, comprising:

a structural member positioned within an airfoil shaped apparatus, the apparatus having an outer surface at least a portion of which includes a plurality of flow path cover members; and

plug and slide means for coupling each of the plurality of flow path cover members with the structural member.

12. The gas turbine engine vane of claim 11, which further includes a continuous cooling media discharge between at least two of the plurality of flow path cover members.

13. The gas turbine engine vane of claim 11, wherein the structural member is a single crystal super-alloy.