Abstract: An aircraft gas turbine engine nacelle comprising a thrust reversal arrangement. The thrust reversal arrangement comprises at least one thrust reverser cascade box comprising a fixed structure and a plurality of thrust reverser vanes configured to direct bypass air forwardly. At least a subset of the thrust reverser vanes are pivotable and/or translatable relative to the fixed structure between a deployed position, in which the vanes define a first volume, and a stowed position, in which the pivotable vanes define a second, smaller volume.

Abstract: An aircraft pneumatic system comprises a gas turbine engine (10) comprising a compressor (14), a fan (12) and a core turbine (12) coupled to one of the compressor (14) and the fan (12), an auxiliary turbine (50) having an inlet in fluid communication with the core turbine (20), the auxiliary turbine (50) being configured to power an auxiliary compressor (40), an inlet of the auxiliary compressor (40) being in fluid communication with an outlet of the fan (12), and an outlet of the auxiliary compressor (40) being in fluid communication with an aircraft environmental control system (48).