Rolls-royce Corporation

Sidney E Slattery

Peter Havercroft

Harry Henshaw

Richard B Smart

The combustion equipment of a gas turbine engine comprises an annular flame tube and a support casing both subjected to relatively high temperatures. Engine acceleration or engine deceleration causes the temperature in the combustion equipment to increase or decrease respectively, and this results in either expansion or contraction of the annular flame tube and the support casing. The annular flame tube has a greater rate of thermal expansion/contraction than that of the support casing and this results in distortion or cracking of the combustion equipment if the annular flame tube and support casing are rigidly mounted to each other. To overcome this problem a relatively flexible support structure which has a generally U-shaped cross-section is positioned radially between the annular flame tube and the support casing, and a first limb of the flexible support structure is secured to the annular flame tube and a second limb of the flexible support structure is secured to the support casing, and the flexible support structure permits relative radial movement of the annular flame tube and the support casing.

Mounting arrangements for combustion equipment

In order to cool the annular upstream wall of a gas turbine engine combustion chamber and thereby to prevent the deposition of carbon particles, the wall is formed of upstream and downstream portions which between them define a chamber arranged to receive a flow of cooling air. The downstream portion has a central opening for an airspray fuel burner and on each side of the opening the downstream portion has a pair of facets each facet having apertures for the throughflow of cooling air over the face of the downstream portion.

Gas turbine engine combustion chambers

Combustion apparatus for reducing objectionable exhaust emissions from gas turbine engines comprises a hollow conical member with an air inlet and fuel injector at its narrower end, the wider end being open into a combustion chamber, the wall of the conical member having a number of orifices for the throughflow of air, the orifices being directed tangentially into the interior of the conical member to impart a swirl to the mixture of fuel and air from the air inlet and fuel injector within the conical member.

Combustion apparatus for gas turbine engines

Plates are mounted over holes formed in the heat shield of a gas turbine engine combustion chamber, which plates are slightly spaced from the heat shield so that air issues radially outwardly from behind the plates to produce film cooling of the heat shield.

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Foston, United Kingdom

Sidney E Slattery