Skip to Content
Find More Like This
Return to Search

TWO PRESSURE COOLING OF TURBINE AIRFOILS

United States Patent Application

20180066523
A1
View the Complete Application at the US Patent & Trademark Office
An airfoil cooling system (54) for a gas turbine engine (10) is disclosed. The airfoil cooling system (54) may be formed from at least a first cooling fluid supply system (56), and a second cooling fluid supply system (58). The first cooling fluid supply system (56) may be configured to supply cooling fluids at a first pressure to one or more airfoils of a first row (68) of airfoils, and the second cooling fluid supply system (58) may be configured to supply cooling fluids at a second pressure to the one or more airfoils of the first row (68) of airfoils. Additionally, the second pressure may be lower than the first pressure. As such, each of the one or more airfoils may be cooled by cooling fluids at two different pressures. In particular embodiments, this may allow the airfoils to be cooled, while lowering the cost to the turbine engine (10) for providing such cooling.
Marsh, Jan H. (Orlando, FL), Marra, John J. (Winter Springs, FL), Scribner, Carmen Andrew (Fort Mill, SC)
15/ 558,343
April 6, 2015
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT [0001] Development of this invention was supported in part by the United States Department of Energy, Advanced Hydrogen Turbine Development Program, Contract No. DE-FC26-05NT42644. Accordingly, the United States Government may have certain rights in this invention.