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Title: Ceramic blade with tip seal

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).

Inventors:
 [1];  [2];  [2]
  1. Del Mar, CA
  2. San Diego, CA
Issue Date:
Research Org.:
SOLAR TURBINES INC
OSTI Identifier:
871079
Patent Number(s):
5653579
Assignee:
Solar Turbines Incorporated (San Diego, CA)
DOE Contract Number:  
AC21-93MC30246
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
ceramic; blade; tip; seal; gas; turbine; engine; 10; disc; assembly; 64; defining; 66; plurality; blades; 70; attached; thereto; preestablished; rate; thermal; expansion; shroud; 100; spaced; distance; forming; interface; 108; therebetween; positioned; 110; equal; attached thereto; preestablished rate; turbine engine; thermal expansion; gas turbine; ceramic blade; shroud assembly; tip seal; disc assembly; /415/

Citation Formats

Glezer, Boris, Bhardwaj, Narender K, and Jones, Russell B. Ceramic blade with tip seal. United States: N. p., 1997. Web.
Glezer, Boris, Bhardwaj, Narender K, & Jones, Russell B. Ceramic blade with tip seal. United States.
Glezer, Boris, Bhardwaj, Narender K, and Jones, Russell B. Wed . "Ceramic blade with tip seal". United States. https://www.osti.gov/servlets/purl/871079.
@article{osti_871079,
title = {Ceramic blade with tip seal},
author = {Glezer, Boris and Bhardwaj, Narender K and Jones, Russell B},
abstractNote = {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).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1997},
month = {1}
}

Patent:

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