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Annular combustion chamber bypass

A technology of annular combustion chamber and burner, which is applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve problems such as the limitation of the available partial load range of gas turbines, and achieve simple assembly and disassembly, simple realization, and emission reduction. Effect

Inactive Publication Date: 2014-11-26
SIEMENS AG
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

To avoid this, the usable part load range of gas turbines is limited

Method used

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Examples

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Embodiment Construction

[0023] figure 1 The combustion system of the annular combustion chamber 1 according to the invention is shown schematically and exemplarily. The annular combustion chamber 1 consists of a closed ring arranged around the axis of rotation 2. The burner 3 is arranged in the inlet 4 in the upper region of the combustion chamber 1. There, fuel 5 is mixed with compressed air 6. The self-combustion is realized in the combustion chamber 1. The hot combustion gas enters the turbine cavity 8 through the outlet 7 where the combustion gas contacts the first blade 9. In order to protect before ignition, the annular combustion chamber 1 is lined with a ceramic heat shield 10 and a metal heat shield 11, which are fixed on the shell 12.

[0024] According to the present invention, the combustion chamber shell 12 is provided with a channel in the area of ​​the outlet 7 between the last ceramic heat shield column 13 (ie the penultimate column heat shield) and the metal inlet shell plate (ie the...

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Abstract

The invention relates to an annular combustion chamber (1) for a gas turbine having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine chamber (8), wherein ducts (14) which can be closed, which are oriented substantially parallel to the symmetry axis (2) of the annular combustion chamber (1), and through which final compressor air can be guided into the annular combustion chamber (1) are provided in the outer shell (12) in the region of the outlet (7). Furthermore, the invention relates to a gas turbine.

Description

Technical field [0001] The present invention relates to an annular combustion chamber with a bypass device for reducing carbon monoxide emissions during partial load operation and a gas turbine with such an annular combustion chamber. Background technique [0002] During part-load operation of the gas turbine, the combustion temperature in the combustion chamber drops. As a result, the temperature in the primary zone related to carbon monoxide emissions also drops below the minimum value, thereby increasing the production or emissions of carbon monoxide. To avoid this situation, the available partial load range of the gas turbine is limited. Summary of the invention [0003] The technical problem to be solved by the present invention is to provide an annular combustion chamber of the aforementioned type, which can significantly increase the available partial load range. [0004] The technical problem is solved by an annular combustion chamber, which provides for such an annular co...

Claims

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Application Information

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IPC IPC(8): F23R3/04F23R3/26
CPCF23R3/26F23R3/04F23R3/08
Inventor F.本克勒T.布兰登堡O.戴斯T.格里布M.林克N.萨维利厄斯D.沃格特曼J.威尔克斯
Owner SIEMENS AG
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