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Title: CMC blade with pressurized internal cavity for erosion control

Abstract

A ceramic matrix composite blade for use in a gas turbine engine having an airfoil with leading and trailing edges and pressure and suction side surfaces, a blade shank secured to the lower end of each airfoil, one or more interior fluid cavities within the airfoil having inlet flow passages at the lower end which are in fluid communication with the blade shank, one or more passageways in the blade shank corresponding to each one of the interior fluid cavities and a fluid pump (or compressor) that provides pressurized fluid (nominally cool, dry air) to each one of the interior fluid cavities in each airfoil. The fluid (e.g., air) is sufficient in pressure and volume to maintain a minimum fluid flow to each of the interior fluid cavities in the event of a breach due to foreign object damage.

Inventors:
;
Issue Date:
Research Org.:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1237087
Patent Number(s):
9,249,669
Application Number:
13/439,892
Assignee:
General Electric Company (Schenectady, NY)
DOE Contract Number:  
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Apr 05
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION

Citation Formats

Garcia-Crespo, Andres, and Goike, Jerome Walter. CMC blade with pressurized internal cavity for erosion control. United States: N. p., 2016. Web.
Garcia-Crespo, Andres, & Goike, Jerome Walter. CMC blade with pressurized internal cavity for erosion control. United States.
Garcia-Crespo, Andres, and Goike, Jerome Walter. Tue . "CMC blade with pressurized internal cavity for erosion control". United States. https://www.osti.gov/servlets/purl/1237087.
@article{osti_1237087,
title = {CMC blade with pressurized internal cavity for erosion control},
author = {Garcia-Crespo, Andres and Goike, Jerome Walter},
abstractNote = {A ceramic matrix composite blade for use in a gas turbine engine having an airfoil with leading and trailing edges and pressure and suction side surfaces, a blade shank secured to the lower end of each airfoil, one or more interior fluid cavities within the airfoil having inlet flow passages at the lower end which are in fluid communication with the blade shank, one or more passageways in the blade shank corresponding to each one of the interior fluid cavities and a fluid pump (or compressor) that provides pressurized fluid (nominally cool, dry air) to each one of the interior fluid cavities in each airfoil. The fluid (e.g., air) is sufficient in pressure and volume to maintain a minimum fluid flow to each of the interior fluid cavities in the event of a breach due to foreign object damage.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2016},
month = {2}
}

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