AIRCRAFT ENGINE APPARATUS

• US 20180016989A1
• Filed: 11/04/2015
• Published: 01/18/2018
• Est. Priority Date: 12/24/2014
• Status: Active Grant

• Current Assignee: Kawasaki Jukogyo Kabushiki Kaisha
• Original Assignee: Kawasaki Jukogyo Kabushiki Kaisha
• Inventors: ABE, Akihito, GOI, Tatsuhiko
• Granted Patent: US 11,566,566 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 11/14 Spinners
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan; aircraft equipment (28) disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) coupled to the rotating shaft and the fan; a second motive force transmitter (32) disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment; and a support member (12) disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment.

Claims

1. An aircraft engine apparatus comprising:

a rotating shaft;

a fan driven by the rotating shaft;

a fan case surrounding the fan;

aircraft equipment disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case;

a casing that accommodates at least part of the rotating shaft and supports the fan case;

a first motive force transmitter coupled to the rotating shaft and the fan;

a second motive force transmitter disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment;

a support member disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment; and

a nose cone disposed upstream of the fan, wherein

the aircraft equipment is disposed inside the nose cone.

2. The aircraft engine apparatus according to claim 1, further comprising a transmission disposed between the rotating shaft and the first motive force transmitter, wherein

the first motive force transmitter is a hollow member that is coupled to the rotating shaft via the transmission and that extends in an axial direction of the rotating shaft.

3. The aircraft engine apparatus according to claim 2, wherein

the transmission includes an unmovable part fixed to the casing, and

the support member is coupled to the casing via the unmovable part.

4. The aircraft engine apparatus according to claim 3, wherein

the transmission is a star-type planetary gear mechanism including:

a sun gear;

a plurality of planetary gears meshed with the sun gear;

a ring gear meshed with the plurality of planetary gears; and

a carrier that supports the plurality of planetary gears, such that the planetary gears are rotatable, and

the unmovable part is the carrier.

5. The aircraft engine apparatus according to claim 2, wherein

the transmission includes a space, through which the support member passes, and

the support member passing through the space is coupled to the casing.

6. The aircraft engine apparatus according to claim 1, wherein

the second motive force transmitter is a shaft member extending in an axial direction of the rotating shaft.

7. The aircraft engine apparatus according to claim 1, further comprising a low-pressure turbine, wherein

the rotating shaft is a low-pressure shaft driven by the low-pressure turbine.

9. The aircraft engine apparatus according to claim 1, wherein

a heat exchanger is provided on a surface of the nose cone, the heat exchanger exchanging heat generated by the aircraft equipment with outside air.

10. The aircraft engine apparatus according to claim 1, wherein

the aircraft equipment is a power generator.

8. (canceled)