Rolls-royce Corporation

Rolls-royce Deutschland Ltd & Co. Kg

Robert Goulds

Richard Peace

Roger Alexander Sutherland

Konstantinos Emmanouil

Brian Richard Lace

Roger Sutherland

A supersonic gas turbine engine for an aircraft that comprises a nacelle, a fan, an engine core including a primary duct configured to guide a core airflow through the engine core, a bypass duct extending between the engine core and an engine casing and configured to guide a bypass airflow through the bypass duct, an intake located upstream of the fan, and a tertiary airflow duct extending between the engine casing and the nacelle and configured to guide a tertiary airflow. The intake is configured to extract air from the intake and guide it to the tertiary airflow duct in which the extracted air flows as tertiary airflow. It is provided that at least one heat exchanger is mounted in the tertiary airflow duct.

Supersonic gas turbine engine

A gas turbine engine comprising: a compressor; a first turbine; and a first compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor; wherein the first compressor bleed valve is configured to release bleed air to a downstream location in the engine, the downstream location being downstream of the first turbine; wherein the first compressor bleed valve is configured to open wherein the first compressor bleed valve is configured to open to at least two positions, to thereby release a variable amount of bleed air from the compressor.

Gas turbine engine with compressor bleed valve including at least two open positions

A tail bearing housing of a turbomachine comprises an inner casing and an outer casing concentrically arranged along a longitudinal axis, and a plurality of vanes having a leading edge, a trailing edge, a first wall extending from the leading edge to the trailing edge and a second wall extending from the leading edge to the trailing edge, the first wall and the second wall defining an aerofoil, the vanes being connected at a first end to the outer casing and at a second end to the inner casing. At least one vane of the plurality of vanes is a vent vane comprising a first aperture arranged in the first end and a second aperture arranged in the aerofoil, the second aperture being configured to be in fluid communication with the first aperture through an inner cavity to vent bleed air.

Tail bearing housing

An electrical connector arrangement comprises a metal mounting bracket for securing the arrangement to a structure; an electrically insulating mounting block abutting the mounting bracket; a clamp to secure an electrical cable to the mounting block, the electrical cable comprising a plurality of electrical conductors; and a plurality of spaced-apart terminals to accommodate the respective electrical conductors.

Electrical connector arrangement

A centrifugal debris separator for removing debris from a gas turbine engine fuel system comprises a debris separator inlet, a debris separator outlet and a separating chamber with a centerline extending in an axial direction and defined by an outer wall formed around the centerline. The separating chamber comprises a separating chamber inlet for receiving fluid, a first separator outlet to the separating chamber, a second separator outlet to the separating chamber provided to the outer wall of the separating chamber and a third separator outlet to the separating chamber defined by a third separator outlet wall formed around the centerline of the separating chamber. The debris separator inlet is fluidly connected to the separating chamber inlet. The debris separator outlet is fluidly connected to the first separator outlet.

Debris separator

A gas turbine engine having a fire wall configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone. The gas turbine engine also has: (i) an actuator located in the first zone, (ii) an actuatable device that is located in the second zone, (iii) a bypass duct, (iv) an off-take device to extract cooling air from the bypass duct in the gas turbine engine and to supply the extracted cooling air into the elongate housing/shell, the off-take device having a first passage and a second passage, and (v) a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall. The mechanical force transmitting device is configured to actuate the actuatable device by transmitting a mechanical force to the actuatable device.

Growing community of inventors

Derby, United Kingdom

Robert Goulds