Thermal blade tip clearance control for gas turbine engines

Details Thermal blade tip clearance control for gas turbine engines Thermal blade tip clearance control for gas turbine engines

1991-07-01

1992-10-13

Denion, Thomas E.

Rotary kinetic fluid motors or pumps

Including thermal expansion joint

Radially sliding

415134, 4151736, 4151737, F01D 2526

Patent

active

051545756

ABSTRACT:
An axial-flow compressor in which rotor blade clearance, in an area where the stator case surrounding a rotor blade stage is unsupported, is controlled by the cross-sectional area of a ring surrounding the stator case and by a gap between the inner surface of the ring and the outer surface of the stator case established at the time of compressor build.

REFERENCES:
patent: 4008978 (1977-02-01), Smale
patent: 4101242 (1978-07-01), Coplin et al.
patent: 4398866 (1983-08-01), Hartel et al.
patent: 4522559 (1985-06-01), Burge et al.
patent: 4596116 (1986-06-01), Mandet et al.

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