Gas turbine system and moving body including the same

Patent metadata

Field	Value
Publication number	US-2022243652-A1
Application number	US-202017625949-A
Country	US
Kind code	A1
Filing date	Feb 13, 2020
Priority date	Jul 12, 2019
Publication date	Aug 4, 2022
Grant date	—

Abstract

Provided is a gas turbine system that is used for a moving body including a thrust generator configured to generate thrust from electric power and includes: a combustor that burns a compressed air generated by a compressor together with fuel to generate a combustion gas; a turbine driven by the combustion gas generated by the combustor; a generator that is coupled to the turbine to generate electric power by driving of the turbine and supplies electric power to the thrust generator; a turbofan that guides external air to the compressor; and an exhaust unit that guides a combustion gas that passed through the turbine to the outside, and the turbofan is driven by a part of a combustion gas guided to the exhaust unit or by external air heated by heat exchange with a part of a combustion gas guided to the exhaust unit.

First claim

1 . A gas turbine system used for a moving body comprising a thrust generator configured to generate thrust from electric power, the gas turbine system comprising:
a compressor that compresses external air to generate compressed air; a combustor that burns the compressed air generated by the compressor together with fuel to generate a combustion gas; a turbine driven by the combustion gas generated by the combustor; a generator that is coupled to the turbine to generate electric power by driving of the turbine and supplies electric power to the thrust generator; a turbofan that guides external air to the compressor; and an exhaust unit that guides a combustion gas that passed through the turbine to outside, wherein the turbofan is rotated by a part of a combustion gas guided to the exhaust unit or by external air heated by heat exchange with a part of a combustion gas guided to the exhaust unit.

2 . The gas turbine system according to claim 1 further comprising a bypass unit that guides a part of a combustion gas guided to the exhaust unit to the turbofan,
wherein the turbofan is rotated by the combustion gas guided by the bypass unit.

3 . The gas turbine system according to claim 2 further comprising:
a shell arranged so as to cover the compressor, the combustor, the turbine, and the exhaust unit; and
an exit unit that guides a combustion gas guided to the turbofan by the bypass unit to a discharge port provided in a surface of the shell.

4 . The gas turbine system according to claim 1 further comprising:
a heat exchanger that exchanges heat between external air and a combustion gas;
an intake fan that guides external air to the heat exchanger;
a bypass unit that guides a part of a combustion gas guided to the exhaust unit to the heat exchanger; and
an introduction unit that guides, to the turbofan, heated air generated by heating external air with a combustion gas at the heat exchanger,
wherein the turbofan is rotated by the heated air guided by the introduction unit.

5 . The gas turbine system according to claim 4 ,
wherein the bypass unit guides, to the intake fan, a part of the combustion gas guided to the exhaust unit, and wherein the intake fan is driven by the combustion gas guided by the bypass unit.

6 . The gas turbine system according to claim 4 further comprising:
a shell arranged so as to cover the compressor, the combustor, the turbine, and the exhaust unit; and
an exit unit that guides the heated air guided to the turbofan by the introduction unit to a discharge port provided in a surface of the shell.

7 . The gas turbine system according to claim 2 ,
wherein the exhaust unit has an inner wall member formed in a cylindrical shape and extending along an axis line about which the turbine rotates and an outer wall member formed in a cylindrical shape and extending along the axis line and arranged so as to surround the outer circumference side of the inner wall member, wherein the inner wall member and the outer wall member form an annular channel through which a combustion gas discharged from the turbine flows and which extends along the axis line, wherein the generator is arranged in an accommodation space formed on the inner circumference side of the inner wall member, and wherein the bypass unit introduces a part of a combustion gas from the annular channel.

8 . A moving body comprising:
the gas turbine system according to claim 1 ; and a thrust generator that generates thrust from electric power generated by the gas turbine system.

9 . The gas turbine system according to claim 5 further comprising:
a shell arranged so as to cover the compressor, the combustor, the turbine, and the exhaust unit; and
an exit unit that guides the heated air guided to the turbofan by the introduction unit to a discharge port provided in a surface of the shell.

10 . The gas turbine system according to claim 3 ,
wherein the exhaust unit has an inner wall member formed in a cylindrical shape and extending along an axis line about which the turbine rotates and an outer wall member formed in a cylindrical shape and extending along the axis line and arranged so as to surround the outer circumference side of the inner wall member, wherein the inner wall member and the outer wall member form an annular channel through which a combustion gas discharged from the turbine flows and which extends along the axis line, wherein the generator is arranged in an accommodation space formed on the inner circumference side of the inner wall member, and wherein the bypass unit introduces a part of a combustion gas from the annular channel.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Morisaki Yuki
• Imai Kazuhiro
• Oda Masayuki
• Nakatani Yuichi
• Saiki Yasuhiro

Classifications

• F02K3/075

  controlling flow ratio between flows · CPC title

• F02K3/115

  by means of indirect heat exchange · CPC title

• F02C1/04

  the working fluid being heated indirectly {(in a fluidised-bed combustor F02C3/205)} · CPC title

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title