Patent ID: 11859536
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. An engine system of a multi-engine aircraft, comprising:
a first engine configured for operation in an active mode to provide motive power to the multi-engine aircraft, the first engine having a first bleed air system enabling operation of the first engine in the active mode;
a second engine configured for operation in an active mode or a standby mode, the second engine having a second bleed air system enabling operation of the second engine in the active mode;
a control system including a controller in communication with the first engine and the second engine, the controller configured to operate the second engine in either the active mode or the standby mode while the first engine operates in the active mode, wherein in the standby mode the second engine provides substantially no motive power to the aircraft;
an air system operatively connected to the first and second bleed air systems, the air system including at least one control valve in communication with the controller of the control system, the controller actuating the control valve to selectively execute any one of: i) fluidly connect the first and second bleed air systems to each other when the second engine is in the standby mode, and ii) fluidly disconnect the first and second bleed air systems from each other when the second engine is in the active mode; and
a pressure wave damper positioned in the air system fluidly proximate to the at least one control valve so as to attenuate at least a part of air pressure fluctuations generated in the air system during a switch over of the air system between: i) fluidly connecting the first and second bleed air systems to each other, and ii) fluidly disconnecting the first and second bleed air systems from each other;
wherein the air system comprises a first control valve operable to selectively connect the first and second bleed air systems to each other, and the pressure wave damper is a plurality of pressure wave dampers that includes a first pressure wave damper disposed fluidly between the first control valve and the first bleed air system, and a second pressure wave damper disposed fluidly between the first control valve and the second bleed air system; and
wherein the air system comprises a second control valve operable to selectively connect the first bleed air system to a source of pressurized air external to both the first and second engines, a third control valve operable to selectively connect the second bleed air system to the source of pressurized air, the plurality of pressure wave dampers includes a third pressure wave damper disposed fluidly between the second control valve and the first bleed air system, and a fourth pressure wave damper disposed fluidly between the third control valve and the second bleed air system.