Gas turbine engine case coated with thermal barrier coating to c

Details Gas turbine engine case coated with thermal barrier coating to c Gas turbine engine case coated with thermal barrier coating to c

1995-03-15

1997-07-08

Look, Edward K.

Rotary kinetic fluid motors or pumps

Including heat insulation or exchange means

Working fluid on at least one side of heat exchange wall

415177, F01D 2514

Patent

active

056453990

ABSTRACT:
An engine case of a gas turbine engine is selectively coated with a thermal barrier coating to control axial clearance between rotating and stationary airfoils. The coating is applied to the thinner portions of the engine case to retard thermal expansion of these portions of the engine case during transient conditions of the gas turbine engine operation. The selectively coated engine case responds substantially uniformly to heating and thermal expansion during transient conditions, thereby reducing axial vane lean in gas turbine engines.

REFERENCES:
patent: 4642027 (1987-02-01), Popp
patent: 4659282 (1987-04-01), Popp
patent: 5127795 (1992-07-01), Plemmons et al.

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