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Combustion device for gas turbine engine

a combustion device and gas turbine engine technology, applied in the direction of turbine/propulsion fuel valves, burner details, lighting and heating apparatus, etc., can solve the problem of particularly likely backfiring phenomenon, achieve low combustion, suppress backfiring phenomenon, and stable combustion

Inactive Publication Date: 2017-03-16
KAWASAKI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent describes a new design for a combustor in a gas turbine engine. The design prevents high-temperature combustion, reduces NOx emissions, and prevents backfiring to keep the flame stable. In one embodiment, each fuel injection annular portion is designed as a hollow space with an annular fuel flow passage. This allows the fuel to flow in a circular direction and cool the exposed portion of the fuel injection annular portion that is exposed to high temperature caused by the flame in the combustion chamber. Overall, this design improves efficiency and performance of gas turbine engines.

Problems solved by technology

However, in a gas turbine engine using a highly reactive fuel including hydrogen, the backfiring phenomenon is particularly likely to occur.

Method used

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  • Combustion device for gas turbine engine
  • Combustion device for gas turbine engine
  • Combustion device for gas turbine engine

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Embodiment Construction

[0041]Hereinafter, embodiments of the present invention will be described with reference to the drawings, but the present invention is not limited to the embodiments.

[0042]FIG. 1 shows a schematic configuration of a gas turbine engine (hereinafter referred to simply as a gas turbine) GT in which a combustor according to an embodiment of the present invention is applied. In the gas turbine GT, introduced air is compressed by a compressor 1 and guided to a combustor 3, and fuel is injected into the combustor 3. The fuel is combusted with the air, and the resulting high-temperature and high-pressure combustion gas drives a turbine 5. The turbine 5 is connected to the compressor 1 via a rotary shaft 7, and the compressor 1 is driven by the turbine 5. A load L such as a rotor of an aircraft or a generator is driven by an output of the gas turbine GT. In the present embodiment, hydrogen gas is used as the fuel injected into the combustor 3. In the following description, a side, in an axia...

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PUM

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Abstract

A combustor includes: a combustion liner having a combustion chamber formed therein; a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion; and a supplemental burner. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel and air into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide groove that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

Description

CROSS REFERENCE TO THE RELATED APPLICATION[0001]This application is a continuation application, under 35 U.S.C. §111(a), of international application No. PCT / JP2015 / 065477, filed May 28, 2015, which claims priority to Japanese patent application No. 2014-113269, filed May 30, 2014, the disclosure of which are incorporated by reference in their entirety into this application.BACKGROUND OF THE INVENTION[0002]Field of the Invention[0003]The present invention relates to combustors used in gas turbine engines.[0004]Description of Related Art[0005]For environment protection purposes, in gas turbine engines, strict environmental standards are set for the composition of emitted combustion exhaust gas. It is required to reduce harmful substances such as nitrogen oxide (hereinafter referred to as NOx) from the exhaust gas. Under such circumstances, in recent years, a combustion system adopting a premix combustion system which effectively reduces the amount of generated NOx, for example, a com...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F23R3/28F23R3/00
CPCF23R3/002F23R3/286F02C7/232F23R3/28F23R3/30F23R3/32F23R3/34F23R3/16F23R3/283F23C2900/9901F23D2209/20F23R2900/03044Y02T50/678Y02T50/60
Inventor HORIKAWA, ATSUSHIKAZARI, MASAHIDEOKADA, KUNIOKITAJIMA, JUNICHI
Owner KAWASAKI HEAVY IND LTD
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