Abstract: An anti-icing system for a nacelle of a gas turbine powerplant is disclosed. Various construction details have been developed which provide means to exhaust fluid from an inlet shell cavity and into an external medium. In one embodiment, the exhaust means (62) includes a plurality of aerodynamically shaped vanes (66) disposed within the inlet shell cavity (52) and a plurality of exhaust slots (68) wherein each of the vanes is adjacent one of the exhaust slots. The vanes are adapted to turn a portion of the body of fluid flowing within the inlet shell cavity to a direction substantially normal to the direction of flow of the external medium.

Abstract: An anti-icing system for a nacelle of a gas turbine powerplant is disclosed. Various construction details have been developed which provide means to exhaust fluid from an inlet shell cavity and into an external medium. In one embodiment, the exhaust means (62) includes a plurality of aerodynamically shaped vanes (66) disposed within the inlet shell cavity (52) and a plurality of exhaust slots (68) wherein each of the vanes is adjacent one of the exhaust slots. The vanes are adapted to turn a portion of the body of fluid flowing within the inlet shell cavity to a direction substantially normal to the direction of flow of the external medium.

Abstract: A buffer system for cooling a buffer region 66 in the nacelle 14 of a gas turbine engine 12 after engine shutdown is disclosed. Various construction details are developed for positively providing cooling air after engine operation to the buffer region of the nacelle, such as with a blower means 74. A coolable component 96, 98, 100, is disposed in the region. In one detailed embodiment, a shroud 72 extends about the buffer region and at least a portion of the coolable component is disposed in the shroud.

Abstract: A buffer system for cooling a buffer region 66 in the nacelle 14 of a gas turbine engine 12 after engine shutdown is disclosed. Various construction details are developed for positively providing cooling air after engine operation to the buffer region of the nacelle, such as with a blower means 74. A coolable component 96, 98, 100, is disposed in the region. In one detailed embodiment, a shroud 72 extends about the buffer region and at least a portion of the coolable component is disposed in the shroud.

Abstract: A ventilation system for a nacelle 14 is disclosed. The ventilation system includes pressure relief doors 50 and 52, and a holdback device 68 which blocks each open door from moving from the open position to the closed position.