Combined power main engine start system
AssigneeHamilton Sundstrand Corporation
InventorRobert Thompson
Life of this patent
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Abstract
A starting system for starting the propulsion engines of gas turbine powered aircraft that combines power sources delivered by the APU so that essentially then entire power delivered by the APU for pneumatic, hydraulic and electric power is applied to corresponding starters on each propulsion engine during MES simultaneously.
Claims27
A starting system for starting the propulsion engines of gas turbine powered aircraft comprising:
- an auxiliary power unit (APU) with a pneumatic supply source and an auxiliary supply source;
- at least one gas turbine propulsion engine with a pneumatic starter and an auxiliary starter;
- a pneumatic supply path for controlling and distributing pneumatic power from the pneumatic supply source to the pneumatic starter upon main engine start (MES);
- and
- an auxiliary supply path for controlling and distributing auxiliary power from the auxiliary supply source to the auxiliary starter upon MES.
A starting system for starting the propulsion engines of gas turbine powered aircraft comprising:
- an auxiliary power unit (APU) with a pneumatic supply source comprising a load compressor and an auxiliary supply source comprising a dynamoelectric machine;
- at least one gas turbine propulsion engine with a pneumatic starter and an auxiliary starter comprising a dynamoelectric machine;
- a pneumatic supply path comprising pneumatic ductwork and valving for controlling and distributing pneumatic power from the pneumatic supply source to the pneumatic starter upon main engine start (MES);
- and
- an auxiliary supply path comprising wiring and switching for controlling and distributing auxiliary power from the auxiliary supply source to the auxiliary starter upon MES.
A starting system for starting the propulsion engines of gas turbine powered aircraft comprising:
- an auxiliary power unit (APU) with a pneumatic supply source comprising a load compressor and an auxiliary supply source comprising a hydraulic pump;
- at least one gas turbine propulsion engine with a pneumatic starter and an auxiliary starter comprising a hydraulic motor;
- a pneumatic supply path comprising pneumatic ductwork and valving for controlling and distributing pneumatic power from the pneumatic supply source to the pneumatic starter upon main engine start (MES);
- and
- an auxiliary supply path comprising hydraulic valving and tubing for controlling and distributing auxiliary power from the auxiliary supply source to the auxiliary starter upon MES.
A starting system for starting the propulsion engines of gas turbine powered aircraft comprising:
- an auxiliary power unit (APU) with a pneumatic supply source comprising a load compressor and an auxiliary supply source comprising a dynamoelectric machine and a hydraulic pump;
- at least one gas turbine propulsion engine with a pneumatic starter and an auxiliary starter comprising a dynamoelectric machine and a hydraulic pump;
- a pneumatic supply path comprising pneumatic ductwork and valving for controlling and distributing pneumatic power from the pneumatic supply source to the pneumatic starter upon main engine start (MES);
- and
- an auxiliary supply path comprising wiring and switching for controlling and distributing auxiliary power from the auxiliary supply source to the electric portion of the auxiliary starter and hydraulic valving and tubing for controlling and distributing auxiliary power from the auxiliary supply source to the hydraulic portion of the auxiliary starter upon MES.
Dependencies are inferred from the claim text.