Shroud assembly for a gas turbine engine

Details Shroud assembly for a gas turbine engine Shroud assembly for a gas turbine engine

1983-02-16

1985-02-05

Scott, Samuel

Rotary kinetic fluid motors or pumps

With diversely oriented inlet or additional inlet for...

415117, 415175, 415200, F01D 1108

Patent

active

044976100

ABSTRACT:
A shroud assembly for a gas turbine engine consists of a housing having a boundary wall and a gas contacting skin, the wall and skin being in segmented form. The skin consists of a thin metal sheet attached to the boundary wall, and a ceramic gas contacting coating. The skin is impingement cooled by cooling air flowing through apertures in the boundary wall, and the cooling air exhausts into the gas flow through passages.
The use of a thin metal sheet with a ceramic coating promotes favorable temperature gradients in the skin enabling the coating to run at optimum conditions for maximum cooling effect.

REFERENCES:
patent: 3423070 (1969-01-01), Corrigan
patent: 3694255 (1972-09-01), Brill-Edwards
patent: 3800864 (1974-04-01), Hauser
patent: 3963368 (1976-06-01), Emmerson
patent: 4050843 (1977-09-01), Needham
patent: 4127357 (1978-11-01), Patterson
patent: 4177004 (1979-12-01), Riedmiller
patent: 4251185 (1981-02-01), Karstensen
patent: 4273824 (1981-06-01), McComas
Principles of Engineering Heat Transfer, by Warren H. Giedt, Ph.D., Section 1.3, including pp. 4, 5, 6 and 7.

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