Burner for a gas turbine

A technology of gas turbines and burners, which is applied in the directions of combustion chambers, combustion methods, combustion equipment, etc., can solve the problems of reducing the efficiency of gas turbines, etc.

Inactive Publication Date: 2018-03-27
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this operation is disadvantageous because it reduces the efficiency of the gas turbine and cannot be performed at part loads less than 40% of full load

Method used

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  • Burner for a gas turbine
  • Burner for a gas turbine
  • Burner for a gas turbine

Examples

Experimental program
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Effect test

Embodiment Construction

[0023] figure 1 One example of gas turbine engine 10 is shown in cross-section. Gas turbine engine 10 includes an inlet 12 , a compressor section 14 , a combustor section 16 , and a turbine section 18 in a flow sequence generally arranged in flow sequence and generally about and in the direction of a longitudinal or rotational axis 20 . Gas turbine engine 10 also includes a shaft 22 rotatable about an axis of rotation 20 and extending longitudinally through gas turbine engine 10 . Shaft 22 drivingly connects turbine section 18 to compressor section 14 .

[0024] In operation of gas turbine engine 10 , air 24 drawn through air inlet 12 is compressed by compressor section 14 and delivered to combustion section or combustor section 16 . As part of the compression process, the air temperature typically increases from ambient to about 400-400°C as the air pressure increases. The combustor section 16 includes a combustor plenum 26 , one or more combustion chambers 28 and at least...

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Abstract

The invention relates to a burner for a gas turbine (10), wherein the burner (30) comprises a combustion chamber (28), a preheating device adapted to preheat air before it enters the combustion chamber (28) and a swirler (107) adapted to guide a swirler air flow (125) that comprises the preheated air to the combustion chamber (28), wherein the swirler (107) comprises a base plate (116) with a surface that confines the swirler air flow (125), wherein the surface has a hole (103) adapted to inject a liquid fuel into the swirler air flow (125) and the base plate has a channel (131 to 134) for transporting the liquid fuel to the hole (103), wherein at least a part of the channel (131 to 134) is oriented essentially parallel to the surface so that the liquid fuel can stream essentially parallelto the surface and can be preheated by the swirler air flow (125).

Description

Background technique [0001] Combustors for gas turbines can be operated under certain operating conditions by injecting water into the combustion chamber in order to lower the flame temperature and thus reduce NO x emissions. [0002] Used to reduce NO x An alternative approach to the emissions of DLE consists in the use of dry low emissions (DLE) burners, which operate without water injection and are based on premixing fuel and air prior to combustion. DLE burners emit low concentrations of NO x And produce a dense flame. However, DLE burners are generally designed for full load operation. In particular, DLE combustors include a fuel lance for injecting liquid fuel into the combustion chamber, wherein the lance is sized such that efficient atomization of the liquid fuel and efficient mixing of the fuel with air occurs when operating at full load. [0003] However, when the burner is operated at part load operation, the pressure drop across the lance is smaller compared t...

Claims

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Application Information

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Patent Type & AuthorityApplications(China)
IPC IPC(8): F23R3/14F23R3/28
CPCF23R3/14F23R3/286Y02E20/34F23C7/004F23C7/06
InventorG·布拉特
OwnerSIEMENS AG