Rolls-Royce Corporation

Rowan H Colley

John Frederick Coplin

A common mechanism enables both throat area change in either a fan duct or an exhaust gas duct and flow deflection at the nozzle of the duct.

Fluid propulsion engine with flow exit control device

The invention relates to fuel burners and to combustion equipment for use in gas turbine engines. A more uniform mixture of fuel and air can be obtained in an annular flame tube by ensuring that each fuel injector is maintained in a fixed position in relationship to the annular flame tube. The present invention provides a fuel burner and combustion equipment with means to locate the fuel injector in a fixed position in relationship to the annular flame tube. The fuel burner comprises a fuel feed arm and a fuel injector. The fuel injector is attached to the fuel feed arm, and a fuel passage extends coaxially through the fuel feed arm and supplies fuel to the fuel injector. The fuel from the fuel passage is supplied to a fuel chamber in a pintle positioned within a duct in the fuel injector. The fuel chamber supplies the fuel through a number of fuel passages into the duct. The annular flame tube has a plurality of apertures in the head, and a swirler assembly is positioned coaxially within each aperture, and a fuel injector is positioned coaxially in each of the swirler assemblies. A tongue extends from and is substantially perpendicular to the axis of the fuel injector and the tongue engages with an upstream extending projection of the swirler assembly, to locate the fuel injector relative to the flame tube.

Combustion equipment for a gas turbine engine including a fuel burner

A rotor tip clearance control apparatus for a gas turbine engine comprises an annular shroud member which forms part of the static structure of the apparatus. The shroud member has an internal frusto-conical surface which co-operates with the outer extremities of the rotor to define a small clearance. In order to control this clearance the shroud member is mounted from fixed structure by rotatable eccentrics which can move the member axially and thus affect the clearance in a predetermined manner.

Rotor tip clearance control apparatus for a gas turbine engine

A constant speed drive comprises a frictional variable speed drive controlled by a control system to produce a constant output speed. The drive includes a rotatable disc having a frusto-conical surface and being urged into frictional engagement with a rotatable annulus having a corresponding frustoconical edge, the annulus and disc being relatively movable between a position in which they are coaxial and provide a unity drive ratio and a position in which they are eccentric and provide a different drive ratio determined by the relative positions of their axes. Actuation means are provided for adjusting the positions of the axes of the annulus and disc relative to one another, and the control system controls the actuation means to vary the relative positions of the axes of the disc and annulus and thus the drive ratio to maintain a sensibly constant output speed.

Constant speed drive

A gas turbine engine has a core engine which drives a fan, the fan comprising a main rotor stage and a stub rotor stage whose blades have a smaller radial extent than those of the main rotor stage. The main and stub stages of the fan both compress air to form a main fan airflow and a stub stage airflow respectively, the stub stage airflow being divided into two portions one of which rejoins the main fan airflow and one of which enters the core engine intake. In order to match the flow angles of the various flows, the stub stage has inner and outer outlet guide vanes which give different degrees of deflection to the two component portions of the stub stage airflow.

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Sunnyhill, United Kingdom

Rowan H Colley