公开(公告)号：US20200032714A1

公开(公告)日：2020-01-30

申请号：US16440393

申请日：2019-06-13

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Satoshi NAKAYAMA ,  Akihisa OKA ,  Hiroki SEIKE

IPC: F02C7/275

Abstract: A starting device for driving a compressor-side rotary shaft of a two-shaft type gas turbine engine at a time of starting the gas turbine engine includes: a starter motor serving as a drive source for the compressor-side rotary shaft; a speed increaser configured to increase a speed of rotation of the starter motor; and a clutch mechanism configured to disconnectably connect the starter motor and the compressor-side rotary shaft with each other, the clutch mechanism being provided between the compressor-side rotary shaft and the speed increaser.

公开(公告)号：US20190390577A1

公开(公告)日：2019-12-26

申请号：US16527649

申请日：2019-07-31

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Kazuhiko TANIMURA ,  Hikaru SANO ,  Satoshi NAKAYAMA ,  Naoki MIYAKE ,  Akihisa OKA

IPC: F01K25/00 ,  F01K23/10

Abstract: A hydrogen/oxygen stoichiometric combustion turbine system includes: a high-pressure steam turbine (2); a low-pressure steam turbine (3); and a heater (5) disposed between the high-pressure and low-pressure steam turbines. The heater (5) has a combustion portion (53) in which stoichiometric combustion of hydrogen and oxygen is caused, and a mixing portion (55) configured to mix discharged steam (S4) from the high-pressure steam turbine (2) with combustion gas (R) from the combustion portion (53) and to supply the obtained product to the low-pressure steam turbine (3).

公开(公告)号：US20190292991A1

公开(公告)日：2019-09-26

申请号：US16441786

申请日：2019-06-14

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Satoshi NAKAYAMA ,  Akihisa Oka ,  Hiroki Seike

IPC: F02C7/28 ,  F02C3/06

Abstract: A gas turbine engine configured to combust, by means of a combustor, a compressed air obtained through compression by a compressor, and drive a turbine with use of high-temperature and high-pressure combustion gas generated by the combustion, the gas turbine engine including: a plurality of air passages through which different portions in the gas turbine engine communicate with one another; and a switching device configured to switch air flow paths between the plurality of air passages, wherein the plurality of air passages are each formed by an air pipe disposed outside a compressor casing, and the switching device is mounted to an outer surface of the compressor casing via a heat insulation member.