Patent ID: 8240126
Filing Date: 2012-08-14
Classification: F01D,F02K,F04D,F05D,Y02T

Abstract:
1. A valve system intermediate a secondary flow path and a primary flow path of a gas turbine engine comprising: a contoured frame including a flow passage there through; a shaped door pivotable relative said contoured frame between an open position and a closed position, said shaped door and said contoured frame together defining an airfoil shape when said shaped door is in said closed position; a nozzle to eject said primary flow; said door located at a downstream end of said nozzle; wherein said contoured frame is mounted to an inner cooling liner structure of a core of a gas turbine engine; wherein said shaped door is pivotable about a door axis at a downstream end of said shaped door and said shaped door opens to direct airflow through said contoured frame.