Title:
AIRCRAFT HYBRID MOTIVE POWER SOURCE SYSTEM AND METHOD FOR CONTROLLING SAME
Document Type and Number:
WIPO Patent Application WO/2024/018988
Kind Code:
A1
Abstract:
This aircraft hybrid motive power source system is installed in an aircraft and comprises: a gas turbine engine (20) that includes a low-pressure shaft (27) and a high-pressure shaft (28) as rotating shafts; a first electric generator (31) that is drivably connected to the high-pressure shaft (28); a second electric generator (32) that is drivably connected to the low-pressure shaft (27); a fuel cell (40) to which fuel gas and oxidant gas are supplied; a fuel gas generation unit (50) that generates fuel gas from a raw material through heating using exhaust gas of the gas turbine engine (20); and a control unit (60) that, on the basis of information indicating the running state of the gas turbine engine (20) and/or demand for electric power in the aircraft, supplies, to the first electric generator (31) or the second electric generator 32, electric power of the fuel cell (40) obtained through the supply of fuel gas.
Inventors:
SEKI NAOKI (JP)
OYORI HITOSHI (JP)
OYORI HITOSHI (JP)
Application Number:
PCT/JP2023/025869
Publication Date:
January 25, 2024
Filing Date:
July 13, 2023
Export Citation:
Assignee:
IHI CORP (JP)
International Classes:
B64D27/24; B64D27/10; F01D25/36; F01K23/02; F02C7/00; F02G5/02; H01M8/00; H01M8/04014; H01M8/04111; H01M8/04858; H01M8/10
Foreign References:
| EP3012438A1 | 2016-04-27 | |||
| JP2006205755A | 2006-08-10 | |||
| JPH11200888A | 1999-07-27 |
Attorney, Agent or Firm:
MIYOSHI Hidekazu et al. (JP)
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