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}
}