Ceramic blade with tip seal

Patent · Tue Dec 31 23:00:00 EST 1996

OSTI ID:871079

Glezer, Boris ^[1]; Bhardwaj, Narender K ^[2]; Jones, Russell B ^[2]

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1. Del Mar, CA
2. San Diego, CA

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).

• Research Organization: SOLAR TURBINES INC
• DOE Contract Number: AC21-93MC30246
• Assignee: Solar Turbines Incorporated (San Diego, CA)
• Patent Number(s): US 5653579
• OSTI ID: 871079
• Country of Publication: United States
• Language: English

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10
100
108
110
64
66
70
assembly
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attached thereto
blade
blades
ceramic
ceramic blade
defining
disc
disc assembly
distance
engine
equal
expansion
forming
gas
gas turbine
interface
plurality
positioned
preestablished
preestablished rate
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seal
shroud
shroud assembly
spaced
therebetween
thereto
thermal
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tip
tip seal
turbine
turbine engine