Combination low spool generator and ram air turbine generator
AssigneePratt & Whitney Canada Corp.
InventorsKevin Allan Dooley, Audrey Cheng, Jerzy Makuszewski
Life of this patent
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Abstract
A power generating apparatus for use with an aircraft gas turbine engine has a low pressure spool assembly which includes an electrical generator. The electrical generator includes a generator stator supported on a stationary structure of the engine and a generator rotor rotatable around the generator stator and mounted to the low pressure spool assembly.
Claims17
A power generating apparatus comprising an aircraft gas turbine engine having a low pressure compressor assembly including a bladed propulsor rotatable in response to ram air passing through the engine, an electrical generator including a generator stator and a generator rotor, and a power conditioning apparatus, the power conditioning apparatus providing first and second electrical outputs, the first having a higher voltage than the second, the generator rotor connected to a rotor disc of the low pressure compressor assembly for rotation with the bladed propulsor, wherein the generator rotor is radially positioned closer to an inner wall of an annular section of a main fluid path of the engine with respect to a shaft of the low pressure compressor assembly, the annular section of the main fluid path directing an air flow compressed by the low pressure compressor assembly.
An electric power generating apparatus for use with an aircraft gas turbine engine having a low pressure spool assembly including a low pressure compressor rotor disc mounted to a low pressure spool shaft and a plurality of blades radially extending from the rotor disc, the blades being rotatable within an annular section of a main fluid path of the engine for driving an air flow to pass through the section of the main fluid path during engine operation, the electrical power generating apparatus comprising a generator stator supported on a stationary structure and a generator rotor rotatable around the generator stator and mounted to the low pressure spool assembly, the generator rotor being radially positioned closer to an inner annular wall of the section of the main fluid path than with respect to the low pressure spool shaft.
A method of generating power on an aircraft, using an electric generator assembly associated with a low pressure compressor assembly of a gas turbine engine, the method comprising the steps of operating the gas turbine engine to drive the electric generator assembly to thereby provide a first electric power output from the electric generator assembly during normal engine operation, driving the generator assembly by a windmill action of the low pressure compressor assembly to thereby provide a second electric power output form the electric generator assembly during an engine-inoperative condition to provide power to the aircraft.
Dependencies are inferred from the claim text.