Patent ID: 6351090
Filing Date: 2002-02-26
Classification: F02C,F02N,F05D,Y02T

Abstract:
A gas turbine engine starting device adapted to be used in an aircraft having a front end compartment and a rearward end compartment opposite said front end compartment, said gas turbine starting device comprising:electrical power supply means located in said front end compartment of said aircraft for delivering a direct current source of power, said electrical power supply means comprising at least one storage battery and a voltage converter complementary therewith; a gas turbine engine located in said rearward end compartment of said aircraft, said gas turbine engine having an input shaft; a three-phase alternating current synchronous electric drive motor mounted adjacent said gas turbine engine, said electric drive motor having an output shaft mechanically coupled to said input shaft of said turbine engine for rotation therewith; and means for transmitting said electrical power supply means in said front end compartment to said electric drive motor located in said rearward end compartment of said aircraft, said means for transmitting comprising means for supplying alternating current (AC) to said electric drive motor, said means for supplying being electrically connected to said electric drive motor whereby power supplied by said electrical power supply means in said front end compartment of said aircraft is transmitted to said rearward end compartment to power said electric drive motor such that said electric drive motor drives said gas turbine engine to be started; such that said gas turbine is started with power supplied from said at least one storage battery located in said front end compartment of said aircraft and does not require additional power supplied from said rearward end compartment of said aircraft.