Abrasive blade tip

• US 5,551,840 A
• Filed: 06/07/1995
• Issued: 09/03/1996
• Est. Priority Date: 12/08/1993
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Benoit, Roland, Love, Charles M., Beverly, Eugene M., Mack, Gregory J.
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US08/483,644
• Time in Patent Office: 454 Days
• Field of Search: 416/241 R, 416/241 B, 416/, 415/200, 277/53, 277/55, 277/56, 428/220
• US Class Current: 416/241.00B
• CPC Class Codes: F01D 11/12 using a rubstrip, e.g. erodible. deformable or resiliently-biased part
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An improved abrasive blade tip for gas turbine engines is taught, wherein an abrasive tip coating is applied to the blade tip in such a manner as to lessen wear through of the abrasive and the underlying airfoil on the leading and trailing edges, by coating the blade tip with abrasive not only on the tip surface per se, but so as to cover portions of the convex and concave airfoil surfaces at the corners where the tip surface intersects the leading and trailing edges.

Claims

1. A gas turbine engine blade having a convex surface, a concave surface, a leading edge, a trailing edge and a tip surface, said blade comprising an abrasive layer encompassing portions of the convex surface and the concave surface at corners where the tip surface intersects the leading edge and the trailing edge of the blade.

2. The blade as set forth in claim 1, wherein portions 0f the leading edge and the trailing edge of the blade are overplated with the abrasive layer.

3. The blade as set forth in claim 1, wherein the abrasive layer comprises cubic boron nitride.

4. The blade as set forth in claim 1 wherein portions of the tip surface are overplated with the abrasive layer.

5. The blade as set forth in claim 1 wherein the abrasive layer comprises alumina.

6. The blade as set forth in claim 1 wherein the abrasive layer comprises alumina-zirconia.

8. A blade as set forth in claim 1, wherein the abrasive layer is from about 0.030 to 0.070 inches thick.

9. A blade as set forth in claim 1, wherein the abrasive layer is applied to said blade tip by electroplating.

10. A blade as set forth in claim 1, wherein the size of said cubic boron nitride is from about 60 to 230 mesh.

11. A blade as set forth in claim 1, wherein said cubic boron nitride is from about 100 to 120 mesh in size.

7. A rotatable blade for a gas turbine engine, said blade comprising a tip surface having thereupon an abrasive layer bonded to said surface by a metal matrix, said abrasive layer containing cubic boron nitride, said abrasive layer encompassing a portion of the leading and trailing edges of said blade adjacent said blade tip, said abrasive layer also encompassing portions of the convex and concave surfaces of the airfoil of said blade adjacent the leading and trailing edges of said blade, such that said airfoil is coated with said abrasive layer in areas bounded by the end point of the blade tip, a point located on the surface of the blade tip from about 0.025 to 0.100 inches from the end of the blade tip toward the center of the blade tip, and a point located on the edge of the blade from about 0.025 to 0.100 inches from the end point of the blade tip toward the radially inner end of the blade.