Electric power generating device for aircraft

Patent metadata

Field	Value
Publication number	US-2018237154-A1
Application number	US-201615556886-A
Country	US
Kind code	A1
Filing date	Mar 8, 2016
Priority date	Mar 9, 2015
Publication date	Aug 23, 2018
Grant date	—

Abstract

An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, comprises an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an electric power generator arranged with the input shaft and the transmission and driven by an output of the transmission; a driving force transmission mechanism disposed on a first end side of the input shaft in an axial direction thereof, the driving force transmission mechanism being configured to transmit the output from the transmission to the electric power generator; and a casing including a mounting section on the first end side of the input shaft in the axial direction, wherein the transmission includes an input section provided on a second end side of the input shaft in the axial direction, the input section being configured to receive as an input a rotational driving force from the input shaft, and an output section provided on the first end side of the input shaft in the axial direction, the output section being configured to output to the driving force transmission mechanism the rotational driving force whose speed has been changed, and wherein the driving force transmission mechanism has an inner space and the input shaft is inserted into the inner space.

First claim

1 . An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, the electric power generating device comprising:
an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an electric power generator arranged with the input shaft and the transmission and driven by an output of the transmission; a driving force transmission mechanism disposed on a first end side of the input shaft in an axial direction thereof, the driving force transmission mechanism being configured to transmit the output from the transmission to the electric power generator; and a casing including a mounting section on the first end side of the input shaft in the axial direction, wherein the transmission includes an input section provided on a second end side of the input shaft in the axial direction, the input section being configured to receive as an input a rotational driving force from the input shaft, and an output section provided on the first end side of the input shaft in the axial direction, the output section being configured to output to the driving force transmission mechanism the rotational driving force whose speed has been changed, and wherein the driving force transmission mechanism has an inner space and the input shaft is inserted into the inner space.

2 . The electric power generating device for the aircraft according to claim 1 ,
wherein the input shaft is disposed between the transmission and the electric power generator.

3 . The electric power generating for the aircraft according to claim 1 ,
wherein the driving force transmission mechanism is a gear mechanism and includes a hollow gear which transmits the rotational driving force of the input shaft toward the electric power generator and has a through-hole, and wherein the inner space is the through-hole of the hollow gear.

4 . The electric power generating device for the aircraft according to claim 3 ,
wherein the engine has an outer peripheral portion with a circular-arc shape, wherein the driving force transmission mechanism includes a plurality of gears, wherein the hollow gear is one of the plurality of gears, and wherein the plurality of gears are arranged in an arched shape along a circumferential direction of the outer peripheral portion of the engine.

5 . The electric power generating device for the aircraft according to claim 1 , further comprising:
at least one auxiliary unit driven by the output of the transmission, wherein the output is transmitted from the transmission to the at least one auxiliary unit via the driving force transmission mechanism to drive the at least one auxiliary unit.

6 . The electric power generating device for the aircraft according to claim 1 ,
wherein the transmission is a traction continuously variable transmission.

7 . The electric power generating device for the aircraft according to claim 1 ,
wherein the driving force transmission mechanism, a coupling portion at which the driving force transmission mechanism and the electric power generator are coupled to each other, and a coupling portion at which the driving force transmission mechanism and the transmission are coupled to each other are located in the vicinity of the mounting section.

Assignees

• Kawasaki Heavy Ind Ltd

Inventors

• Tanaka Kenichiro
• Imai Hideyuki
• Fujii Isao
• Goi Tatsuhiko
• Fuchiwaki Shogo

Classifications

• H02K7/1823

  structurally associated with turbines or similar engines · CPC title

• F01D15/10

  Adaptations for driving, or combinations with, electric generators · CPC title

• F16H2057/02082

  for application in vehicles other than propelling, e.g. adjustment of parts · CPC title

• F16H1/06

  with parallel axes · CPC title

• F16H15/38

  with two members B having hollow toroid surfaces opposite to each other, the member or members A being adjustably mounted between the surfaces · CPC title