Bremssteuerungsanordnung für ein Flugzeuggasturbinentriebwerk und Verfahren zur Verwendung davon

Details

Veröffentlichungs-Nr.

EP4464873

Aktenzeichen

EP24176782

Anmeldetag

17. Mai 2024

Veröffentlichung

20. November 2024

Rechtsraum

EP

IPC

F01D21/00F02C7/268F01D19/00

Abstract

An assembly for a gas turbine engine of an aircraft includes a rotational assembly, a starter generator (28), and a control relay (54). The starter generator (28) is coupled with the rotational assembly and is configured to selectively drive rotation of the rotational assembly and a motor winding (64) including a first electrical terminal (65) and a second electrical terminal (66). The control relay (54) includes a switch (72) electrically connected to the first electrical terminal (65). The switch (72) is positionable in a first contact position and a second contact position, in the first contact position, the first electrical terminal (65) is electrically isolated from the second electrical terminal (66) through the switch (72). In the second contact position, the first electrical terminal (65) is electrically connected to the second electrical terminal (66) through the switch (72) such that a closed electrical circuit is formed through the motor winding (64), the first electrical terminal (65), the second electrical terminal (66), and the switch (72).

Anmelder

Firma

PRATT & WHITNEY CANADA CORP.

Land

🇨🇦 Kanada

Fachgebiete