Rolls-royce Corporation

Andrew Parsley

Natalie C Wong

Stephen John Bradbrook

Martin N Goodhand

Thomas S Binnington

Paul Michael Hield

John Leslie Gibbons

Robert J Corin

Martin Goodhand

Paul Francis Taylor

An apparatus and method for reducing a pressure differential across a turbineof a gas turbine engineduring a shaft break event, comprises a pressure equalization apparatusconfigured to introduce a pressurised fluid into a core airflow A at a region directly downstream of the turbinein the event of a shaft break to directly increase a local pressure at the downstream regionof the turbineand thereby reduce the pressure differential across the turbine. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine

Turbine overspeed protection

An apparatus and method for reducing a pressure differential across a turbineof a gas turbine engineduring a shaft break event, comprises a pressure equalization apparatusconfigured to introduce a pressurised fluid into a core airflow A at a region downstream of the turbinein the event of a shaft break to directly increase a local pressure at the downstream regionof the turbineand thereby reduce the pressure differential across the turbine. The pressure equalization apparatus comprises a sensorconfigured to directly detect a shaft break event. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine

An apparatus and method for reducing a pressure differential across a turbineof a gas turbine engineduring a shaft break event, comprises a pressure equalization apparatusconfigured to introduce a pressurised fluid into a core airflow A at a region downstream of the turbine, wherein a rearward movement of the turbineor a shaftin a shaft break event directly actuates the pressure equalisation apparatusto directly increase a local pressure at the downstream regionof the turbineand thereby reduce the pressure differential across the turbine. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine

A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes fan blades defining a fan diameter. The heat exchanger module is in communication with the fan assembly by an inlet duct, and the heat exchanger module further includes radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between hollow vanes. Each hollow vane accommodates at least one heat transfer element to transfer heat from a first fluid contained within the or each heat transfer element to a corresponding vane airflow passing through the hollow vane and over a surface of the or each heat transfer element. Each hollow vane further includes a flow modulator configured to regulate airflow in proportion to total airflow entering the heat exchanger module in response to a user requirement.

Heat exchanger

A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module including a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. Each heat transfer element may be individually and independently fluidly isolated from the remaining heat transfer elements.

A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module includes a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels.

A turbofan gas turbine engine includes heat exchanger module, fan assembly, compressor, turbine and exhaust modules. The fan includes a plurality of fan blades. The heat exchanger in fluid communicates with the fan assembly by an inlet duct, and the heat exchanger includes a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger is divided between a set of vane airflows and a set of channel airflows. Each vane airflow has a vane mass flow rate Flow, and each channel air flow has a channel mass flow rate Flow. Each hollow vane includes, an inlet, heat transfer, and exhaust portions, with the inlet portion comprising a diffuser element and the heat transfer portion including at least one heat transfer element. The diffuser element causes Flowto be lower than Flow.

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Bristol, United Kingdom

Andrew Parsley