Nickel alloy for turbine engine components

Details Nickel alloy for turbine engine components Nickel alloy for turbine engine components

1998-12-08

2000-10-17

Wyszomierski, George

Metal treatment

Stock

Age or precipitation hardened or strengthened

148428, 420448, C22C 1905

Patent

active

061325279

ABSTRACT:
A new nickel base superalloy suitable for compressor or turbine discs of gas turbine engines with fatigue crack propagation resistance equal to Waspaloy, tensile strength higher than Waspaloy and higher operating temperature than Waspaloy or UDIMET 720 family of alloys. The nickel base superalloy has a preferred composition by weight % of 14.0-19.0% cobalt, 14.35-15.15 Chromium, 4.25-5.25 Molybdenum, 1.35-2.15 tantalum, 3.45-4.15 titanium, 2.85-3.15 aluminium, 0.01-0.025 boron, 0.012-0.033 carbon, 0.05-0.07 zirconium, 0.5-1.0 hafnium, up to 1.0 rhenium, up to 2.0 tungsten, less than 0.5 niobium, up to 0.1 yttrium, up to 0.1 vanadium, up to 1.0 iron, up to 0.2 silicon, up to 0.15 manganese and balance nickel plus incidental impurities.

REFERENCES:
patent: 5124123 (1992-06-01), Henry
patent: 5897718 (1999-04-01), Hessell et al.

Affiliated with

Also associated with

Rating

Nickel alloy for turbine engine components does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Nickel alloy for turbine engine components, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Nickel alloy for turbine engine components will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-464544