An aircraft power and propulsion system includes a gas turbine engine having first and second spools, the first spool being a starting spool; first and second DC electrical networks having first and second operating voltages; a first electrical machine joined with the first spool, the first electrical machine having first and a second winding sets; a second electrical machine joined with the second spool; a first, second and third AC:DC converter; and a controllable switching arrangement configured so that a connection to an AC-side of the third AC:DC converter is switchable between a winding of the second electrical machine or the second DC electrical network via an inductor.
ELECTRICALLY STARTING A GAS TURBINE ENGINE
2025-06-12
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / H02P CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS , Steuern oder Regeln von elektrischen Motoren, elektrischen Generatoren, dynamoelektrischen Umformern |
Turbine technology for engine starting
Automotive engineering | 1981
|Turbine Engine Starting System Design Requirements
SAE Technical Papers | 1999