Patent ID: 11859563
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Transport (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 6:
7. A method of operating a first gas turbine engine of a multi-engine aircraft, the first gas turbine engine having a main gaspath extending through a compressor section, a combustor, and a turbine section, the method comprising:
operating the first gas turbine engine of the aircraft during flight at an altitude above a ground in a standby mode in which the first gas turbine engine is operating, receives a fuel flow, and provides substantially no motive power to the multi-engine aircraft;
operating a second gas turbine engine of the aircraft during flight in an active mode during the flight at the altitude above the ground; and
during the flight at the altitude above the ground, directing pressurized air from a bleed air system of the second gas turbine engine to a secondary air system of the first gas turbine engine, the secondary air system including one or more of a sealing system and a lubrication system, wherein the directing of the pressurized air to the secondary air system includes directing the pressurized air to the secondary air system while bypassing the main gaspath, including fluidly connecting a bleed outlet of the compressor section of the first gas turbine engine to at least one control valve via a first conduit and fluidly connecting the at least one control valve to a bleed outlet of a compressor section of the second gas turbine engine via a second conduit,
wherein each of the first and second conduits include a plurality of branch conduits disposed in between the respective bleed outlets and the at least one control valve, wherein the plurality of branch conduits are configured to provide the bleed air from the respective first and second conduits to one or more of the sealing system and the lubrication system.