Abstract: A nacelle cooling and ventilation system for an aircraft gas turbine engine which includes a chin scoop and duct assembly for directing air through the engine bay where it is exhausted into the engine exhaust through an exhaust shroud eductor. The nacelle is enclosed so that effectively all of the cooling air entering the bay leaves the bay through the engine exhaust and is not dumped overboard, thereby adding to the effective thrust of the engine. An engine oil and generator oil heat exchanger is positioned in the cooling air duct into the bay so that the same air which cools the bay also cools engine and generator oil. The oil heat exchanger includes directional louvers which regulate and keep to a minimum the amount of cooling air and direct cooling air forwardly in the bay so that the entire bay area is cooled, and which can be shut as a fire control measure.

Abstract: A nacelle cooling and ventilation system for an aircraft gas turbine engine which includes a chin scoop and duct assembly for directing air through the engine bay where it is exhausted into the engine exhaust through an exhaust shroud eductor. The nacelle is enclosed so that effectively all of the cooling air entering the bay leaves the bay through the engine exhaust and is not dumped overboard, thereby adding to the effective thrust of the engine. An engine oil and generator oil heat exchanger is positioned in the cooling air duct into the bay so that the same air which cools the bay also cools engine and generator oil. The oil heat exchanger includes directional louvers which regulate and keep to a minimum the amount of cooling air and direct cooling air forwardly in the bay so that the entire bay area is cooled, and which can be shut as a fire control measure.

Abstract: A system is provided for preventing and removing ice accumulation from the leading edges of an inlet cowl of an aircraft gas turbine engine. High pressure, high temperature air, preferrably from a port on the engine compressor, is provided to an annular duct located within an annular chamber formed at the leading edge of the inlet cowl. A plurality of air ejector nozzles are spaced about the air duct and function to direct anti-icing air at a supersonic velocity toward the forward inboard surface of the inlet cowl and create a swirling air mass within the annular chamber.

Abstract: The present invention provides a device for transferring replacement fluid from a first to a second fluid system and for transferring overflow fluid from the second fluid system to the first fluid system. Replacement and overflow fluid is transferred between systems by first and second flow paths respectively, each flow path including a filter to prevent particle contamination between the systems.

Abstract: An auxiliary air system contained within the nacelle of a gas turbine engine having the functions of cooling engine components and measuring air inlet temperature. The system comprises an air ducting pipe, temperature sensors extending into the pipe, a structure to be cooled, such as an electronics module, preferably with a heat transfer chamber, an air flow inducer, and, if desired, means for directing air onto other engine components.

Abstract: Clearance control between an outer air seal of a gas turbine engine and an internal, turbine section of the engine is controlled by selectively modulating a cooling air supply that is directed to selected portions of the air seal supporting structure to control its thermal growth. Impingement of the cooling air causes contraction of the seal structure, thereby lessening the clearance for the purpose of improving engine performance. The flow of cooling air is modulated in response to engine speed and engine altitude to maintain relatively low clearance during critical periods of engine operation.