United Technologies Corporation

Roger J Comeau

Aaron S Butler

Franklin J Davis

Robert F Brodell

Walter J Baran, Jr

James R Harders

Gordon Pfeifer

Randy McKinney

Thomas J Malitsky

An improved fuel nozzle guide (100) for a gas turbine engine combustion chamber (65) includes an eccentric detent (150) which allows only a predetermined amount of limited pivotable movement of a retainer (125) and bushing (105) employed in the guide.

Fuel nozzle guide for a gas turbine engine combustor

An assembly of a bulkhead 48 and fuel nozzle guide 62 for a fuel nozzle 46 disposed in a combustion chamber 24 is disclosed. Various construction details which provide for positively cooling components of the assembly are developed. In one detailed embodiment, the nozzle fuel guide is spaced from the bulkhead to form an annular gap G.sub.1 which is divided by a heat shield 72 into annular orifices 108, 112 for supplying to cooling air passages 126, 128 bounded by the heat shield 72.

Bulkhead and fuel nozzle guide assembly for an annular combustion chamber

The first stage turbine vanes in a gas turbine are supported both axially and for torque control in a ring located within the diffuser case such that it is free to expand to minimize thermal stresses. The support ring is modified to permit assembly of all the turbines within the ring.

First stage turbine vane support structure

A nonrotating flow directing assembly 14 for a gas turbine engine is disclosed. The flow directing assembly is formed of a circumferentially segmented inner case 24 supported by an annular sleeve 22. The inner case 24 is formed of a plurality of arcuate segments 26 extending axially continuously through the engine. A method of assembling the circumferentially continuous annular sleeve about an axially continuous rotor is also disclosed. In an alternate embodiment the inner case 124 is formed of several pluralities of arcuate segments 126.

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Ware, MA, United States of America

Roger J Comeau