Showing papers by "Rolls-Royce Limited published in 1976"

Matching thermal expansion of components of turbo-machines

Abstract: A turbo-machine casing comprises a part double skinned portion at a location surrounding at least one stage of rotor blades; the spaces defined between the two skins containing a heat insulating medium, and the inner of the two skins being additionally provided upon its radially innermost surface with a lining of heat insulating material, the casing being connected to a mass disposed radially outwardly of the casing whereby the rate of thermal expansion of the casing can be reduced nearly equal to the bladed rotor which it surrounds.

Gas turbine engine with improved compressor casing for permitting higher air flow and pressure ratios before surge

Abstract: A plurality of skewed slots of a particular shape are provided within a compressor casing adjacent at least one stage of compressor blade tips, the slots having an axial length greater than that of the adjacent blade tips. The slots are provided such that upon occurrence of compressor surge or stall, the stagnating air occurring about the blade row may be directed by the slots downstream of the compressor blade row back into the main stream of fluid passing through the compressor. By such an arrangement, the slots provide a compressor in which the air flow and pressure ratio may be increased before reaching compressor stall or surge.

Vane for a gas turbine engine having means for impingement cooling thereof

Abstract: A vane for directing hot gases of a gas turbine engine and comprising at least one platform and a hollow aerofoil portion having an air entry tube extending spanwise therein, the tube being provided with a plurality of apertures, the size and the spacing therebetween being chosen to cause cooling fluid to impinge on the interior surface of the aerofoil portion in the form of a plurality of jets. A plurality of columnar projections extend between the interior surface of the aerofoil portion and the exterior of the air entry tube, each projection being positioned directly upstream of one of the apertures in the air entry tube with respect to the general flow of impinged fluid in the space between the interior surface of the aerofoil portion and the exterior of the air entry tube.

Gas turbine engine gas flow ducts

Abstract: A ducted fan gas turbine engine power plant has an augmenter air intake and a flow mixer for selectively mixing the augmenter air with the remaining engine flows.

Priming systems for pumps

Abstract: A reservoir is provided in the inlet line to a pump in which air and vapor collects. The air and vapor is drawn out by a fuel operated pump and supplied to a fuel/air separator. Fuel passes back to the inlet line and the air and vapor is allowed to escape.

Bypass gas turbine fan employing a stub rotor stage and a main rotor stage

Abstract: 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.

Gas turbine jet propulsion engine

Abstract: A gas turbine engine has three turbines, the intermediate and high pressure turbines running at substantially constant corrected speed. The low pressure turbine has variable nozzle guide vanes and the low pressure compressor has variable stators so as to enable its speed to be varied, while its mass flow is arranged to be large at low speeds.

Fuel supply system for a gas turbine engine

Abstract: In order to improve the start-up of a gas turbine engine, a control system is provided which fills part of the fuel manifold with compressed air during start-up so as to prevent fuel flowing to all the burners and thereby to improve the performance of the remaining burners.

Combustion chambers for gas turbine engines

Abstract: 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

Fuel injectors for gas turbine engines

Abstract: An airspray burner is supplied with fuel tangentially through a port and the upstream end of the burner is provided with a helical wall to prevent the fuel from passing back out of the fuel delivery port.

Ejector sleeves for aircraft mounted gas turbine engines

Abstract: An aircraft jet propulsion power plant is fitted with a sliding ejector sleeve for the provision by selection, of an auxiliary flow of ambient air within the sleeve so as to quieten the noise of the gas efflux The sleeve is mounted independently of the power plant and is supported from a side of the aircraft fuselage The sleeve mounting structure has an arm which projects into the fuselage to provide a further mounting point, the reaction loads of which act downwardly so as to counteract the downwardly acting weight of the cowl on the side mounting