US 12,269,601 B2
Air pressurisation system
Christopher A. Murray, Nottingham (GB)
Assigned to Rolls-Royce PLC, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Feb. 1, 2023, as Appl. No. 18/163,143.
Claims priority of application No. 2201470 (GB), filed on Feb. 4, 2022.
Prior Publication US 2023/0373635 A1, Nov. 23, 2023
Int. Cl. F02C 6/08 (2006.01); B64D 13/02 (2006.01)
CPC B64D 13/02 (2013.01) [F02C 6/08 (2013.01); F05D 2220/323 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An air pressurisation system for an aircraft, comprising:
a blower compressor configured to be mechanically coupled to a spool of a gas turbine engine and configured to receive a first inlet flow of air from a bypass duct of the gas turbine engine;
an air treatment apparatus comprising:
an air cycle line configured to condition air received from the blower compressor; and
a bypass line for receiving air from the blower compressor, and configured to bypass the air cycle line;
wherein the air treatment apparatus is configured to mix air from the air cycle line with air from the bypass line to control a temperature of air for discharge to an airframe system; and
a core bleed line configured to provide a second inlet flow of air from a compressor of the gas turbine engine to the air treatment apparatus in an augmented air supply mode of the air pressurisation system;
wherein the core bleed line is further configured to:
provide the second inlet flow of air directly to the bypass line.