Gas turbine system and movable body including the same

Patent metadata

Field	Value
Publication number	US-11885232-B2
Application number	US-202017624965-A
Country	US
Kind code	B2
Filing date	Feb 13, 2020
Priority date	Jul 12, 2019
Publication date	Jan 30, 2024
Grant date	Jan 30, 2024

Abstract

A gas turbine system includes: a compressor configured to compress external air to generate compressed air; a combustor configured to burn the compressed air together with fuel to generate a combustion gas; a turbine configured to be driven by the combustion gas; an exhaust unit configured to guide the combustion gas, which has passed through the turbine, to outside; a shell having a cylindrical shape and extending along an axis line about which the turbine is configured to rotate and being arranged so as to cover the compressor, the combustor, the turbine, and the exhaust unit; and an exit unit configured to guide the combustion gas, which has passed through the turbine, to a discharge port in the surface of the shell.

First claim

The invention claimed is:

1. A gas turbine system comprising:
a compressor configured to compress a first external air to generate a compressed air;
a combustor configured to burn the compressed air together with a fuel to generate a combustion gas;
a turbine configured to be driven by the combustion gas;
an exhaust unit configured to guide the combustion gas that has passed through the turbine to an outside;
a shell having a cylindrical shape and extending along an axis line about which the turbine is configured to rotate, and being arranged so as to cover the compressor, the combustor, the turbine, and the exhaust unit;
a heat exchange unit configured to exchange a heat between the combustion gas that has passed through the turbine and a second external air on a surface of the shell, the heat exchange unit being configured to: (i) guide, to a plurality of discharge ports in the surface of the shell, the combustion gas that has passed through the turbine; and (ii) mix the combustion gas with the second external air to generate a mixed gas; and
an introduction unit configured to guide the mixed gas to the exhaust unit from a plurality of introduction ports in the surface of the shell,
wherein the discharge ports are defined in first portions, respectively, in a circumferential direction about the axis line,
wherein the introduction ports are defined in second portions, respectively, in the circumferential direction, and

wherein the discharge ports and the introduction ports are arranged at positions overlapping each other in the circumferential direction and aligned along the axis line and the shell is configured to guide the mixed gas to one of the introduction ports which is downstream of one of the discharge ports in a flow direction of the combustion gas and the second external air.

2. The gas turbine system according to claim 1 , further comprising at least one channel forming portion that covers at least one of the discharge ports and at least one of the introduction ports and defines a mixed gas channel for flow of the mixed gas between the channel forming portion and the surface of the shell.

3. The gas turbine system according to claim 2 ,
wherein the cylindrical shape of the shell is a first cylindrical shape,
wherein the channel forming portion extends along the axis line and has a second cylindrical shape about the axis line, and
wherein the mixed gas channel is defined annularly about the axis line.

4. The gas turbine system according to claim 2 , wherein a plurality of the channel forming portions extends along the axis line and is spaced apart in the circumferential direction so as to cover both the discharge ports and the introduction ports.

5. The gas turbine system according to claim 1 , further comprising a generator coupled to the turbine and configured to generate an electric power by driving of the turbine and supply the electric power to a thrust generator configured to generate a thrust from the electric power.

6. A movable body comprising:
the gas turbine system according to claim 5 ; and
the thrust generator.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Nakatani Yuichi
• Morisaki Yuki
• Saiki Yasuhiro

Classifications

• B64D27/34

  All-electric aircraft · CPC title

• F01D25/30 Primary

  Exhaust heads, chambers, or the like · CPC title

• B64D33/06 Primary

  Silencing exhaust or propulsion jets · CPC title

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• F01D15/10

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