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Gas Turbine Combustion System

A gas turbine and combustion system technology, applied in the direction of turbine/propulsion fuel delivery system, gas turbine device, combustion chamber, etc., can solve the problem of not providing service ability, improve maintainability, high maintainability, and reduce development time and cost effects

Active Publication Date: 2016-08-24
ANSALDO ENERGIA SWITZERLAND AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The state of the art does not provide an unrestricted higher service capacity compared to ring-type designs

Method used

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  • Gas Turbine Combustion System
  • Gas Turbine Combustion System
  • Gas Turbine Combustion System

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0061] figure 1 Shown is a can combustor 100 that allows individual combustion operations without deleterious interaction with other individual can combustors during combustion operations. The can burner 100 includes a number of removable premix burners 10 . Therefore, according to figure 1 The can architecture includes multiple premix furnaces 10 arranged on the can burner front 15, which allow individual combustion operations.

[0062] A premix furnace 10 (eg according to EP 0704657 A1) consists of the following devices: a swirl generator basically according to EP 0321809 A1 for the combustion air flow; means for fuel injection; and a mixing path formed by mixing tubes, which Located downstream of the swirl generator, wherein the mixing path includes a transition duct extending in the direction of flow within a first portion of the path for transferring the flow formed in the swirl generator to the junction In the cross-section of the flow of the mixing path downstream ...

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Abstract

The present invention relates to a gas turbine combustion system, wherein the gas turbine comprises: at least one compressor; at least one combustor for generating working gas, wherein the combustor is connected to receive compressed air from the compressor; at least one turbine connected to to receive working gas from the combustion chamber. The combustion chamber consists of a single can burner or several can burners arranged in an annular can architecture, wherein the can burner has at least one premixing furnace. The ignition of the mixture starts at the outlet of the premixing furnace and the flame stabilizes in the region of the outlet of the premixing furnace by means of the recirculation zone. The can burner includes some premixed burners arranged uniformly or divided into at least two groups within the can burner.

Description

technical field [0001] The invention relates to a gas turbine combustion system according to claims 1 and 2 . The invention additionally relates to a method for operating a turbine with a can burner comprising a plurality of premixing furnaces according to the present description. Background technique [0002] US 6935116 B1 discloses a method for reducing pollution emissions (such as NO x and CO) while being able to provide a stable combustion gas turbine combustion system under lower load conditions. The combustion system includes a housing having a central axis in fluid communication with an engine compressor, and an end cover secured to the housing. In a preferred embodiment, the end cap includes a first plurality of injectors arranged in a first array about the end cap and a second plurality of injectors arranged about the end cap in a second array, wherein the second array is adjacent to the first array. Radial outside. A first swirler (also referred to as a swirl g...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/28F23R3/14F23R3/34
CPCF23C6/047F23R3/286F23R3/346F23R3/46F23C2201/301F23C2201/40F23C2900/07002F23R2900/00014F23R2900/03341F02C3/14F02C6/003F23M20/005F02C7/22
Inventor F.M.根恩N.阿鲁里J.塞尔尼A.埃罗格鲁E.帕斯夸洛托
Owner ANSALDO ENERGIA SWITZERLAND AG