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Title: Ceramic blade with tip seal

Abstract

The present gas turbine engine includes a disc assembly defining a disc having a plurality of blades attached thereto. The disc 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. A shroud assembly is attached to the gas turbine engine and is spaced from the plurality of blades a preestablished distance forming an interface there between. Positioned in the interface is a seal having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades. 4 figs.

Inventors:
; ;
Publication Date:
Research Org.:
Solar Turbines Inc
Sponsoring Org.:
USDOE, Washington, DC (United States)
OSTI Identifier:
516915
Patent Number(s):
US 5,653,579/A/
Application Number:
PAN: 8-555,686
Assignee:
Solar Turbines Inc., San Diego, CA (United States)
DOE Contract Number:  
AC21-93MC30246
Resource Type:
Patent
Resource Relation:
Other Information: PBD: 5 Aug 1997
Country of Publication:
United States
Language:
English
Subject:
03 NATURAL GAS; 33 ADVANCED PROPULSION SYSTEMS; GAS TURBINE ENGINES; TURBINE BLADES; SEALS; CERAMICS; THERMAL EXPANSION; EQUIPMENT INTERFACES

Citation Formats

Glezer, B, Bhardwaj, N K, and Jones, R B. Ceramic blade with tip seal. United States: N. p., 1997. Web.
Glezer, B, Bhardwaj, N K, & Jones, R B. Ceramic blade with tip seal. United States.
Glezer, B, Bhardwaj, N K, and Jones, R B. Tue . "Ceramic blade with tip seal". United States.
@article{osti_516915,
title = {Ceramic blade with tip seal},
author = {Glezer, B and Bhardwaj, N K and Jones, R B},
abstractNote = {The present gas turbine engine includes a disc assembly defining a disc having a plurality of blades attached thereto. The disc 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. A shroud assembly is attached to the gas turbine engine and is spaced from the plurality of blades a preestablished distance forming an interface there between. Positioned in the interface is a seal having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades. 4 figs.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1997},
month = {8}
}