Method of remanufacturing turbine vane clusters for gas turbine engines

• US 4,176,433 A
• Filed: 06/29/1978
• Issued: 12/04/1979
• Est. Priority Date: 06/29/1978
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Lee, Jack W., Voehringer, Charles A.
• Primary Examiner(s): Husar, Francis S.
• Assistant Examiner(s): Crane, Daniel C.
• Application Number:
  US05/920,582
• Time in Patent Office: 523 Days
• Field of Search: 29/156.8 R, 29/156.8 B, 29/401 R, 29/401 A, 29/401 F, 29/412, 29/416, 29/527.4, 29/527.6, 148/11.5 N, 427/104, 415/189, 415/200, 415/198.1, 83/15, 83/170, 219/69 M, 219/69 E, 228/119, 228/170, 228/171, 228/231, 228/193
• US Class Current: 29/889.1
• CPC Class Codes: B23P 15/04 turbine or like blades from several pieces
• CPC Class Codes: B23P 6/002 Repairing turbine components, e.g. moving or stationary blades, rotors, B23P6/045 takes precedence
• CPC Class Codes: C23F 1/44 Compositions for etching metallic material from a metallic material substrate of different composition
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling
• CPC Class Codes: Y10T 29/49728 and by a metallurgical operation, e.g., welding, diffusion bonding, casting
• CPC Class Codes: Y10T 29/49751 Scrap recovering or utilizing
• CPC Class Codes: Y10T 29/49796 Coacting pieces
• CPC Class Codes: Y10T 83/041 By heating or cooling

Abstract

A method for remanufacturing turbine vane clusters of gas turbine engines is disclosed. Concepts and techniques for salvaging undamaged vanes from a damaged vane cluster are developed. In accordance with the method taught, protective coatings on the vane clusters are removed and residual stresses in the vanes are relieved before salvageable vanes are separated from their original vane cluster.

Claims

1. A method for remanufacturing turbine vane clusters of the type having two or more coated vanes extending between a common inner platform and a common outer platform, comprising the steps of:

inspecting damaged vane clusters and selecting complementary vanes and contiguous platforms for combination into a reconstructed cluster;

stripping the coating materials from the selected vanes and from the portions of the platforms contiguous thereto;

relieving residual stresses in the entire vane clusters in which the selected vanes are contained prior to the step of separating the selected vanes from the clusters;

separating the selected vanes and the portions of the platforms contiguous thereto from the vane clusters after the step of relieving stresses from the vane clusters;

machining bond faying surfaces on the platforms of the complementary vanes selected for combination;

cleaning the machined faying surfaces;

bonding the complementary vanes at the faying surfaces to form a reconstructed vane cluster;

solution heat treating the reconstructed vane cluster;

applying corrosion resistant coating to surfaces of the vane cluster which are to be exposed to hot working medium gases;

precipitation hardening the coated vane cluster.

2. A method for remanufacturing turbine vane clusters of the type cast of MAR-M-200+Hf alloy and coated with an aluminide corrosion resistant coating, comprising the steps of:

inspecting damaged vane clusters and selecting complementary vanes and contiguous platforms for combination to form a reconstructed vane cluster;

removing all appendages attached to the castings;

stripping the aluminide coating from the selected vanes by grit blasting the coated surfaces and immersing the clusters in a nitric acid solution until the coating is removed;

relieving residual stresses in the vane clusters by heating the clusters in an argon atmosphere for two (2) hours at two thousand two hundred degrees Fahrenheit (2200°

F.);

separating the selected vanes and contiguous platforms from the damaged vane clusters;

inspecting the separated vanes for distortion and correcting any such distortion by mechanically deforming the vane at temperatures up to two thousand degrees Fahrenheit (2000°

F.);

machining bond faying surfaces on the platforms of the complementary vanes;

cleaning the bond faying surfaces;

bonding the complementary vanes at the faying surfaces;

solution heat treating the bonded vanes in an argon atmosphere at two thousand two hundred degrees Fahrenheit (2200°

F.) for two (2) hours;

applying aluminide, corrosion resistant coating to surfaces of the cluster which are to be exposed to hot working medium gases;

precipitation heat treating the bonded vanes in or at sixteen hundred degrees Fahrenheit (1600°

F.) for thirty-two (32) hours.

3. The method according to claim 2 wherein the step of machining bond faying surfaces includes coelectric discharge machining the bond faying surfaces employing one of the complementary vanes as the negative electrode in the discharge machining apparatus and employing the opposing complementary vane as the positive electrode in the discharge machining apparatus.

4. The invention according to claims 2 or 3 wherein the step of cleaning the bond faying surfaces includes the step of electrolyte alkaline cleaning the surfaces.

5. The invention according to claims 2, 3 or 4 wherein the step of bonding complementary vanes includes the step of diffusion bonding the vanes.