Rolls-royce Corporation

Amarveer S Mann

Craig W Bemment

Nicholas Howarth

Ian J Bousfield

Benjamin J Sellers

Michael O Hales

High pressure ratio gas turbine engine

The present disclosure relates to a gas turbine engine for an aircraft comprising: an engine core comprising a turbine, a compressor, and a core shaft; and an environmental control system mounted on the engine core comprising a first air passage arranged to deliver air from outside the engine core to an aircraft cabin and/or for wing anti icing, a subsidiary compressor located in the first air passage and arranged to compress air in the first air passage, the subsidiary compressor being powered by the core shaft, and a second air passage arranged to inject air from the compressor into the first air passage.

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Derby, United Kingdom

Amarveer S Mann