Method for forming a thin-walled combustion liner for use in a g

Details Method for forming a thin-walled combustion liner for use in a g Method for forming a thin-walled combustion liner for use in a g

1994-03-10

1995-05-09

Yee, Deborah

Metal treatment

Process of modifying or maintaining internal physical...

With casting or solidifying from melt

148675, 164114, C21D 900

Patent

active

054136474

ABSTRACT:
A vacuum centrifugally cast combustion liner suitable for use in a gas turbine engine operating at temperatures ranging from ambient up to about 1700.degree. F. is provided. The combustion liner is formed by centrifugally vacuum casting a precipitation hardened nickel-based superalloy having controlled, low amounts of aluminum and titanium. The combustion liner is characterized by a homogeneous grain structure having enhanced strength and creep resistance particularly at elevated temperatures. In addition, the preferred elemental composition, particularly the relatively small amounts of aluminum and titanium, enhance the weldability and overall manufacturability of the combustion liner.

REFERENCES:
patent: 2400495 (1946-05-01), Ford et al.
patent: 3527285 (1970-09-01), Webbere
patent: 4621499 (1986-11-01), Mori et al.
patent: 4646810 (1987-03-01), Lardellier
patent: 4810467 (1989-03-01), Wood et al.
patent: 5101547 (1992-04-01), Tanaka et al.
Metals Handbook, 9th Ed, vol. 15 "Centrifugal Casting" pp. 296-307.

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