Ceramic blade with tip seal

Details Ceramic blade with tip seal Ceramic blade with tip seal

1995-11-14

1997-08-05

Kwon, John T.

Rotary kinetic fluid motors or pumps

Bearing, seal, or liner between runner portion and static part

Between blade edge and static part

4151736, F01D 520

Patent

active

056535791

ABSTRACT:
The present gas turbine engine (10) includes a disc assembly (64) defining a disc (66) having a plurality of blades (70) attached thereto. The disc (66) has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc (66). A shroud assembly (100) is attached to the gas turbine engine (10) and is spaced from the plurality of blades (70) a preestablished distance forming an interface (108) therebetween. Positioned in the interface is a seal (110) having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades (70).

REFERENCES:
patent: 4050845 (1977-09-01), Gemein et al.
patent: 4057362 (1977-11-01), Schwaebel
patent: 5106104 (1992-04-01), Atkinson et al.
patent: 5439347 (1995-08-01), Brandon
patent: 5480162 (1996-01-01), Beeman, Jr.
patent: 5503528 (1996-04-01), Glezer et al.
patent: 5511940 (1996-04-01), Boyd
"Some Metallographic Results for Brush Bristles & Brush Segments . . . " Preprint from Seals Flow Code Development--93 NASA Conference Nov. 3, 1993 .

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