Power generation unit of integrated gearbox design for aircraft engine

Patent metadata

Field	Value
Publication number	US-9548639-B2
Application number	US-201414550083-A
Country	US
Kind code	B2
Filing date	Nov 21, 2014
Priority date	May 30, 2012
Publication date	Jan 17, 2017
Grant date	Jan 17, 2017

Abstract

A power generation unit is connected with an engine rotary shaft via an accessory gearbox. A rotor extends through the accessory gearbox and a drive gear is disposed at an intermediate portion of the rotor for driving the latter. Permanent magnet elements are mounted on opposite side portions with the intermediate portion intervening therebetween, and stator coils are disposed so as to confront respective outer peripheries of the permanent magnet elements.

First claim

What is claimed is:

1. A power generation unit for an aircraft engine, which unit is connected with an engine rotary shaft of the aircraft engine via an accessory gearbox, the power generation unit comprising:
a rotor extending through the accessory gearbox and having an intermediate portion positioned longitudinally intermediate of the rotor, and opposite side portions with the intermediate portion intervening therebetween;
a drive gear mounted on the intermediate portion of the rotor to drive the rotor;
permanent magnet elements respectively mounted on outer peripheries of the opposite side portions of the rotor; and
stator coils disposed separately from each other so as to respectively confront outer peripheries of the permanent magnet elements and the outer periphery of the rotor on which the permanent magnet elements are mounted, the stator coils being electrically connected with each other.

2. The power generation unit for the aircraft engine as claimed in claim 1 , wherein the rotor is disposed parallel to the engine rotary shaft.

3. The power generation unit for the aircraft engine as claimed in claim 1 , wherein the stator coils are electrically connected in series with each other.

4. The power generation unit for the aircraft engine as claimed in claim 1 , further comprising a mechanical clutch configured to selectively couple and decouple between the drive gear and an input shaft of the accessory gearbox, the input shaft of the accessory gearbox being connected with the engine rotary shaft through an output shaft.

5. The power generation unit for the aircraft engine as claimed in claim 1 , further comprising a squeeze film damper configured to support a bearing of the rotor with respect to a power generator housing.

6. The power generation unit for the aircraft engine as claimed in claim 1 , wherein the rotor is in the form of a single rod-like member.

7. The power generation unit for the aircraft engine as claimed in claim 1 , wherein the rotor is configured to be divided into the intermediate portion and the opposite side portions.

8. The power generation unit for the aircraft engine as claimed in claim 1 , wherein the power generation unit is connected with a high pressure shaft that forms a part of the engine rotary shaft, and is configured to operate as an engine starter.

9. An accessory gearbox for an aircraft engine, comprising:
an input shaft connected through an output shaft with an engine rotary shaft of the aircraft engine;
the power generation unit as defined in claim 1 ; and
a mechanical clutch configured to selectively couple and decouple between the input shaft and the drive gear.

Assignees

• Kawasaki Heavy Ind Ltd

Inventors

• Goi Tatsuhiko
• Tanaka Kenichiro

Classifications

• F05D2220/768

  equipped with permanent magnets · CPC title

• H02K7/108

  with friction clutches · CPC title

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• H02K7/116 Primary

  with gears · CPC title

• H02K7/1807 Primary

  Rotary generators (H02K7/006 takes precedence) · CPC title