Rolls-royce Corporation

Kevin M Britchford

Romuald Morvant

Peter Swann

Zahid Muhammad Hussain

Rory Douglas Stieger

Michael Georg Kozuch

Nicolas L Balkota

Paul J R Strange

Michael Kozuch

Nicolas Balkota

An aircraft hybrid propulsion system () comprising an inboard gas turbine engine () and an outboard gas turbine engine (), each comprising a propulsor () and a respective electric machine () coupled to one or more engine shaft (). An electrical interconnection () is provided between the electric machine () of the inboard gas turbine engine () and the electric machine () of the outboard gas turbine engine (). A controller () is configured to transfer electrical power between the inboard gas turbine engine electrical machine and the outboard gas turbine engine electrical machine when a thrust setting change is selected.

Aircraft hybrid propulsion system

An aircraft propulsion system comprises first and second thrust producing gas turbine engines. The system comprises a controller configured to determine a required overall propulsion system thrust level, and determine an engine core power level contribution from each aircraft gas turbine engine such that the overall propulsion system produces a minimum overall noise level and meets the required overall propulsion system thrust level. In meeting the minimum overall noise level, at least the first and second gas turbine engines are operated at different engine core power settings.

Aircraft propulsion system

A bleed valve for a gas turbine engine, the bleed valve comprising: an inlet coupled to an air source; and an outlet coupled to an air sink. The bleed valve also comprises a first stage of flow area modulation between the inlet and the outlet. Also a second stage of flow area modulation between the first stage and the outlet. The pressure can be equalized between the first and second stages. There is also an arrangement comprising a plurality of bleed valves and a controller to control the flow areas of at least one of the first and second stages of each bleed valve.

Bleed valve

A pylon for attachment of a gas turbine engine to a wing of an aircraft has a trailing edge which is rearward of the trailing edge of the core fairing and the trailing edge of the fan nacelle. The pylon has two laterally-spaced side faces which extend in the rearward direction of the engine to end at the trailing edge of the pylon. Each side face has a bottom edge which extends in a rearward direction of the engine from the core fairing to the bottom end of the trailing edge of the pylon. The bottom edges merge such that the bottom edges form a single bottom edge. The pylon is intended to exert control on the bypass flow of a gas turbine engine. Other pylons are also provided which can also exert such control.

Pylon for attaching a gas turbine engine

The present invention relates to a flow discharge device () for discharging a flow of gas (F) from a first gaseous fluid (A) into a second gaseous fluid (B) which is of a lower pressure than the first gaseous fluid. The discharge device comprises a valve () disposed between the first and second gaseous fluids and arranged to regulate the discharge flow (F) and a swirler means () disposed between the valve () and the second gaseous fluid. The swirler means () comprises a plurality of radially extending circumferentially spaced vanes (). In use the swirler means () swirls the discharge flow (F). This acts to reduce the energy, and therefore the pressure of the discharge flow. This results in quieter operation.

Flow discharge device

A gas turbine engine has an annular bypass duct defined between a fan nacelle and a core fairing through which fan air is discharged. One or more bifurcator members are positioned inside the exit of the bypass duct to bifurcate the air flow in the bypass duct around the bifurcator members prior to exiting the bypass duct. The bifurcator members modify the flow field of the air in the bypass duct radially and/or tangentially with respect to the axis of the annular bypass duct.

Gas turbine engine

Noise generated by a gas turbine enginesupported by a pylonon a wingof an aircraft is reduced by influencing a shear layer generated between the free-stream flowfield and flow from the engine. The shear layer is influenced by means of one or more wingletswhich interact with the free-stream flowfield to deflect the shear layerdownwardly, to avoid interaction with a flapon the wing, or to reduce the strength of the shear layer

Jet engine installation

In order to provide noise suppression, bumps or undulations are provided on a nozzle surface in order to vary the convergent-divergent ratio between that surface and an opposed nozzle surface. By such an approach, a circumferential variation in the shock cell pattern is created and the flow is deflected so as to enhance turbulent mixing thereby suppressing noise.

Growing community of inventors

Belper, United Kingdom

Kevin M Britchford