Repair of gas turbine blade tip without recoating the repaired blade tip
a gas turbine and blade tip technology, applied in the field of blade tip repair, can solve the problems of affecting the overall performance of the engine, the tip of some turbine blades may be damaged, and the removal of damaged turbine blades from service, so as to achieve the effect of significantly reducing the cost and processing time of the repair
Inactive Publication Date: 2009-10-08
GENERAL ELECTRIC CO
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AI Technical Summary
Benefits of technology
The method effectively reduces repair costs and time while maintaining acceptable mechanical and environmental resistance, making blade repair more economically viable compared to replacing the turbine blade.
Problems solved by technology
During service and despite the presence of the coating, the tips of some of the turbine blades may be damaged by rubbing contact with the stationary shroud of the gas turbine, by oxidation by the hot combustion gases, and by particle impacts.
If the damage becomes sufficiently severe to a turbine-blade tip so that the dimensions of the turbine blade are reduced to less than the specified minimum values and / or the overall engine performance becomes unacceptable, the damaged turbine blade is removed from service.
The damaged turbine blade may then be repaired and returned to service or discarded, but repair is preferred because of the high cost of each new turbine blade.
Method used
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[0021]FIG. 1 depicts the steps in a method for repairing a damaged gas turbine blade 40 which has previously been in service, and which is illustrated in FIG. 2. The damaged gas turbine blade 40 requiring repair is furnished, step 20. The damaged gas turbine blade 40 has a body 41 that is made of a base metal. The base metal is preferably a nickel-base superalloy. A nickel-base alloy has more nickel than any other element. A nickel-base superalloy is strengthened by the precipitation of gamma prime and / or a related phase. An example of an operable nickel-base superalloy is Rene™ N5, having a nominal composition in weight percent of about 7.5 percent cobalt, about 7.0 percent chromium, about 1.5 percent molybdenum, about 5 percent tungsten, about 3 percent rhenium, about 6.5 percent tantalum, about 6.2 percent aluminum, about 0.15 percent hafnium, about 0.05 percent carbon, about 0.004 percent boron, about 0.01 percent yttrium, balance nickel. The body 41 of the gas turbine blade 40 ...
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Abstract
A damaged gas turbine blade which has previously been in service, and which is made of a base metal, is furnished. Any damaged material is removed from the damaged blade tip. The damaged blade tip is weld repaired with a nickel-base superalloy that is more resistant to oxidation resistance than is the base metal in the operating environment of the tip-repaired gas turbine blade. The method does not include any step of coating a lateral surface of the repaired blade tip with a non-ceramic coating after the step of weld repairing.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS[0001]This application is a divisional of U.S. application Ser. No. 11 / 022,185, filed Dec. 23, 2004, which is incorporated by reference in its entirety.FIELD OF THE INVENTION[0002]This invention relates to the repair of the damaged blade tip of a damaged gas turbine blade and, more particularly, to such a repair wherein the repaired blade tip is not recoated with a non-ceramic environmental coating or bond coat.BACKGROUND OF THE INVENTION[0003]In an aircraft gas turbine (jet) engine, air is drawn into the front of the engine, compressed by a shaft-mounted compressor, and mixed with fuel. The mixture is combusted, and the resulting hot combustion gases are passed through a turbine mounted on the same shaft. The turbine includes a rotor body with a series of turbine blades extending radially outward from the rotor body, and a stationary shroud that forms a tunnel in which the rotor body and its blades turn. The flow of combustion gas turns the tu...
Claims
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IPC IPC(8): F01D5/14
CPCB23P6/007B32B15/01C22C19/057C23C26/02F01D5/005Y10T29/49734Y02T50/67Y02T50/673F05D2230/80Y10T29/49732Y10T29/49318F01D5/20Y02T50/60
InventorGORMAN, MARK DANIELGROSSKLAUS, JR., WARREN DAVIS
OwnerGENERAL ELECTRIC CO