United Technologies Corporation

Grumman Aerospace Corporation

James T Dixon

Marvin R Glickstein

Donald M Podolsky

Aldo Arena

Raymond J Bruchez, Jr

Jim D Stewart

Wayne K Movick

Russell H Hagerman

George E Mount

A method and apparatus for supplying cooling air on vehicles such as high speed aircraft includes diverting high pressure air from the compressor section of a gas turbine engine, cooling this air in a heat exchanger, compressing the air and subsequently cooling the air in a second heat exchanger to provide cooled, high pressure air. One embodiment additionally provides cooled air at relatively medium pressure and relatively low pressure, while the alternate embodiment additionally provides cooled air at relatively low pressure.

High pressure air source for aircraft and engine requirements

A method for providing both starting power and thermal management requirements of a vehicle incorporating a gas turbine engine by using the same unit to alternately provide both starting power and cooling air.

Integrated auxiliary power system

An axisymmetric thrust vectoring exhaust nozzle includes a plurality of divergent flaps (30) each supported at the upstream end by a universal joint (32) and at the downstream end by a load link (34) connected to a unison ring (36) positioned by actuators (45).

Thrust vectoring exhaust nozzle

An engine is shown having means for providing cooling fluid to turbine blades on a disk while providing sealing means between the blade roots and cooperating disk slots and providing means for retaining the turbine blades on their disk. The device comprises a full ring coverplate which engages a small coverplate fixed to each blade. A small coverplate is fixed, such as by bonding, to the forward end of the root section of each blade and contoured so that it extends over the edges of the root and bears against the forward side of the disk when the blade root has been inserted in a blade slot. The blades are held in the disk by the full ring coverplate which engages all of the small coverplates at a midpoint between the inner and outer ends of the root. The position of the full ring coverplate can be adjusted to provide and vary a biasing force against the small coverplates to maintain a force keeping the small coverplates against the disk. Cooling air is injected at the inner diameter of the full ring coverplate and is directed to a hole in each of the small coverplates which permits the cooling air to enter the inside of the hollow blade. The full ring coverplate also acts as a forward disk seal.

Growing community of inventors

Jupiter, FL, United States of America

James T Dixon