Abstract: A gas turbine engine comprises a bypass duct and a heat exchanger assembly, the heat exchanger assembly comprising a heat exchanger and a heat exchanger duct having an inlet region, an inflection region and an outlet region. A direction of a centreline of the heat exchanger duct has a tangential component with respect to a principal rotational axis of the gas turbine engine at one or more of the inlet region, the inflection region and the outlet region. The heat exchanger is disposed within the inflection region and configured to transfer heat generated by the gas turbine engine into the flow of air as it passes through the inflection region.

Abstract: A gas turbine engine comprises a bypass duct and a heat exchanger assembly, the heat exchanger assembly comprising a heat exchanger and a heat exchanger duct having an inlet region, an inflection region and an outlet region. A direction of a centreline of the heat exchanger duct has a tangential component with respect to a principal rotational axis of the gas turbine engine at one or more of the inlet region, the inflection region and the outlet region. The heat exchanger is disposed within the inflection region and configured to transfer heat generated by the gas turbine engine into the flow of air as it passes through the inflection region.

Abstract: A composite fan blade for a gas turbine engine, the blade comprises a root portion for connecting the blade to a hub and an aerofoil portion. The aerofoil portion comprises an external cover formed from a non-metallic material and an internal structure enclosed within the cover. The internal structure comprises a plurality of support members extending generally from a pressure side of the internal structure to a suction side of the internal structure, and wherein the plurality of support members define a plurality of cells or channels.

Abstract: A rake for measuring pressures or temperatures in a gas flow includes an elongate member which has a single recess in the front face thereof. Within the recess are located a plurality of sensors. The recess defines a single cavity around the sensors and bleed slots are provided in the side faces of the member which are in fluid communication with the cavity. The sensors are connected to a remote pressure or temperature measuring system. In operation the rake is supported in a gas flow a proportion of which passes into the cavity. The cavity decelerates the gas and removes any swirl so that the sensors take an accurate measurement of the pressure or temperature. The gas then exits the cavity through the bleed slots.

Abstract: A multi-lane controller providing redundancy comprises two lanes. Each lane comprises an input/output interface, a data flow controller and a control data processor. Each data flow controller receives input data from and supplies output data to both input/output interfaces. The information exchange between each lane does not rely on the proper operation of either the control data processor or data flow controller of any of the lanes.