公开(公告)号：US09797314B2

公开(公告)日：2017-10-24

申请号：US14708716

申请日：2015-05-11

Applicant: ROLLS-ROYCE PLC

Inventor： Malcolm Hillel ,  Thierry Moes ,  Rory Douglas Stieger

IPC: F01D17/00 ,  F02C9/18 ,  F02C3/04 ,  F01D15/10 ,  F04D27/02 ,  B64D13/06 ,  F04D19/02

CPC classification number: F02C9/18 ,  B64D2013/0618 ,  B64D2013/0644 ,  F01D15/10 ,  F02C3/04 ,  F04D19/02 ,  F04D27/0223 ,  F04D27/0261 ,  F05D2220/76 ,  F05D2270/101 ,  Y02T50/56

Abstract: A method of operating a gas turbine engine compressor. The method includes: determining an operating point of the compressor, and modulating mass flow of environmental control system input air to maintain the operating point of the gas turbine engine compressor within predetermined limits.

公开(公告)号：US09776727B2

公开(公告)日：2017-10-03

申请号：US14150183

申请日：2014-01-08

Applicant: Rolls-Royce PLC

Inventor： Sean Patrick Ellis ,  Rory Douglas Stieger

IPC: F02C7/18 ,  B64D33/02

CPC classification number: B64D33/02 ,  F02C7/185 ,  F02K3/115 ,  F05D2260/213 ,  F05D2270/112 ,  Y02T50/676

Abstract: A method of controlling an aircraft gas turbine engine cooling system. The cooling system includes a heat exchanger having a first fluid path through which fan air flows, and a second fluid path through which relatively hot compressor air flows. The cooling system includes a valve configurable between an open position corresponding to a first operating mode, where fan air flows through the first path cooling the compressor air in the second path to a lower temperature, and a closed position corresponding to a second operating mode, where fan air may flow through the first path at a reduced rate, thus the compressor air in the second path could be cooled to a lesser extent. The valve is operated in first mode when the aircraft is in a descent mode, or when turbine entry temperature is above a predetermined amount. Otherwise, the valve is operated in second mode.