Combined Pump system for size reduction of thermal management heat exchangers and optimized ventilation to the aircraft cabin

A compression pump (128) for an engine (100) is provided. The pump (128) may include a first impeller (136) operatively coupled to a main shaft (108) of the engine (100), a first inlet (144) configured to at least partially receive bypass airflow and a first outlet (148) configured to direct compressed air to a thermal management system (130).