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US 2017/0370242 A1Published application
Tip clearance control system
AssigneeROLLS-ROYCE plc
InventorsMarko BACIC, Glenn A KNIGHT
Life of this patent
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Abstract
A gas turbine engine is disclosed having a tip clearance control system. The tip clearance control system has a cabin blower system, a casing arranged in use about a rotor of a gas turbine engine and a fluid delivery passage. The cabin blower system having a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and to compress fluid conducted via the fluid delivery passage into heat exchange with the casing.
Claims15
A gas turbine engine comprising:
- a tip clearance control system having a casing arranged about a rotor of a gas turbine engine and a fluid delivery passage;
- and
- a cabin blower system having a cabin blower compressor;
- wherein the output of the cabin blower compressor is coupled to and arranged to deliver fluid to the fluid delivery passage and to a cabin of an aircraft.
1 more element
Dependencies are inferred from the claim text.