Rolls-royce Corporation

Leonard J Rodgers

Kenneth Franklin Udall

Arnold C Newton

Andrew J Mullender

Peter G Farrar

James P Berry

Alan R Stuart

An exhaust nozzle () for a gas turbine engine is described for vectoring a flow of exhaust gases issuing therefrom at an angle to a centre line () of the engine. The exhaust nozzle () comprises a plurality of radially outer flaps () and radially inner flaps () which are circumferentially disposed around the engine. The radially outer flaps () and radially inner flaps () alternately overlap each other to define a path through which the exhaust gases flow. The radially outer flaps () can be moved asymmetrically about the engine centre line (). The radially inner flaps () are maintained in sealing contact with the outer flaps () by the flow of exhaust gases passing therethrough. The radially inner flaps () are divided into a number of triangular sections () which renders the flaps () torsionally flexible so that they can twist along their lengths to maintain sealing contact with adjacent radially outer flaps () when the outer flaps (25) are moved asymmetrically.

Exhaust nozzle for thrust vectoring

A nacelle having a porous structure is provided with laminar flow control and contamination protection. In region B suction through a composite layer is achieved by evacuating a chamber adjacent the inner surface of the nacelle to provide laminar flow control. At the leading edge of the nacelle a sintered metal sheet is attached to an inner surface of the composite layer to control the flow of a liquid over the leading edge of the nacelle. The liquid is contained in a chamber adjacent the sintered metal sheet which is defined by a backing sheet which has a series of depressions therein. Hot air fed through a perforated pipe impinges upon the backing sheet and the depressions transmit heat to the sintered metal sheet. The sintered metal sheet has good thermal conductivity and in turn heats the porous composite layer to prevent the formation of ice thereon.

Ice protection for porous structure

A mounting for connecting a turbofan gas turbine engine to an aircraft structure comprises three mounting points at the vertices of a triangle on the aircraft structure and three mounting points on the fan casing of the turbofan gas turbine engine. The first mounting point on the aircraft structure is connected to all of the three mounting points on the fan casing by three links. The second mounting point on the aircraft structure is connected to the second mounting point and the third mounting point on the fan casing by two links. The third mounting point on the aircraft structure is connected to the second mounting point and the third mounting point by two links. The links provide an open spaceframe which defines the structure of a pylon. The mounting has reduced weight compared to conventional mountings and is cheaper to manufacture.

Mounting for coupling a turbofan gas turbine engine to an aircraft

A porous material is manufactured by weaving polycarbonate fibres through a tow of carbon fibres which has been pre-impregnated with an epoxy resin. A second layer of pre-impregnated carbon fibres are superimposed on the woven layer and the epoxy resin is cured to bond the fibres together. A ceramic slurry is applied and allowed To penetrate through the second layer of fibres and part way through the woven layer of fibres to a controlled depth before being dried to form a mask. A thermoplastic powder is then applied to the unmasked region of the woven layer of fibres and sintered. Finally the mask and the polycarbonate fibres are removed chemically to produce a porous material which comprises a sintered thermoplastic layer reinforced with carbon fibres through which channels are provided.

Method of manufacturing a porous material

An exhaust mixer for a turbofan aeroengine can be classified as being of the multi-lobed type, with troughs between the lobes. Good mixing efficiency together with good aerodynamics, short axial length and low weight is achieved by forming the mixer from flow surfaces which are longitudinally twisted between their upstream and downstream ends, opposing sides of each lobe and trough being of opposite twist. Between the upstream and downstream ends of the twisted flow surfaces, their latitudinal contours become approximately S-shaped so as to define outer portions of the lobes, inner portions of the troughs and the opposed sides of the lobes and troughs.

Exhaust mixer for turbofan aeroengine

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.

Gas turbine engine gas flow ducts

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.

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Derby, United Kingdom

Leonard J Rodgers