United Technologies Corporation

Jack W Wilson, Jr

Mark S Maier

George A Bonner

Lee E Hansen

Ernest W Wilcox

Gerald F Goetz

James T Balkcum, Iii

Eric J Gamble

Eliott L Calzadilla

The nacelle of the aircraft is purged and the sidewall of the vector nozzles of the gas turbine engine in the nacelle is cooled by utilizing the engine fan air to drive ejector pumps mounted in series flow relationship, a rectangular mixing zone and a diffuser with a rectangular cross section and a step in the exhaust nozzle gaspath. This results in minimizing the amount of fan air for driving the system and enhancing engine thrust and enhanced sidewall cooling because the temperature of the mixed air is lower than heretofore known systems.

Nacelle air pump for vector nozzles for aircraft

The backbone which is a load carrying support member of the aft end of the compressor of a gas turbine engine is fabricated from an annular disk-like element that is generally straight in cross section. The points of attachment permit circumferential thermal growth with radial restraint and snugness at judicious locations for minimizing scrubbing of the case-tied segmented inner stator case.

Backbone support structure for compressor

Tip shroud segments (26) are supported in support ring (24). The ring has at its downstream end conical surface (32) mating and in interference fit with conical surface (16). When flange (20) is torqued, face (22) aligns and forces support ring (24) into the interference fit. Concentricity and rigidity of the shroud support is obtained in a structure easily assembled and disassembled.

Gas turbine blade shroud support

A cylindrically shaped spacer between a shaft and hub of a turbine rotor of a gas turbine engine as fabricated from a flexible resilient material and interference fitted at discrete points on either side of the transverse axis of the spacer between the shaft and spacer and between the hub and spacer to impart a twist of the spacer about this axis to remain in contact with the hub and shaft throughout its entire rotating envelope.

Means for maintaining concentricity of rotating components

A seal between co-rotating, opposed annular surfaces of interconnected elements comprises a multi-filament wire rope disposed within an annular groove formed at the interface between the two surfaces, the groove being wedge-shaped in cross-section, one side of the wedge being formed by each element. The wire rope is forced into sealing relationship with the groove surfaces along its entire length by centrifugal forces. The multi-filament wire rope has improved sealing capability over solid, single filament wire seals of the prior art. The seal is particularly well suited for use in the hot turbine section of a gas turbine engine and is resistent to damage and failures due to multiple engine cycles.

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West Palm Beach, FL, United States of America

Jack W Wilson, Jr