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Dampers for Gas Turbines

A gas turbine and damper technology, which is applied in the direction of combustion chambers, combustion methods, combustion equipment, etc., can solve problems such as hindering dampers, and achieve the effect of prolonging the operating life

Active Publication Date: 2016-09-28
ANSALDO ENERGIA IP UK LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In fact, the thermal expansion of the different layers that make up the combustion chamber prevents the direct application of such dampers

Method used

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  • Dampers for Gas Turbines
  • Dampers for Gas Turbines

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Embodiment Construction

[0045] figure 1 A schematic cross-sectional view of a damper 100 having a part of a combustion chamber 200 of a gas turbine according to an embodiment of the present invention is shown, with some parts cut out for clarity. The damper 100 includes a resonant cavity 110 having a box shape or a cylindrical shape as defined by the peripheral wall 102 and the inlet 104. Such as figure 1 As shown, the main part of the resonant cavity 110 is cut away, because this will not hinder the complete and complete understanding of the technical solution of the present invention. In addition, for clarity and conciseness, figure 1 Only the parts of the combustion chamber 200 closely related to the present invention are shown. Resonant cavity 110 by figure 1 A fastener not shown is airtightly attached to the structure 106 of the combustion chamber 200. In an exemplary embodiment of the present invention, the structure 106 of the combustion chamber 200 may be the shell of the combustion chamber 2...

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Abstract

The invention relates to a damper for a gas turbine. In particular, the present invention relates to a damper for reducing pulsations in a combustion chamber of a gas turbine, wherein the damper comprises: a resonant cavity having an inlet and in flow communication with the interior of the combustion chamber and the resonant cavity A neck tube, and a compensating assembly, which is pivotally connected to the neck tube and inserted between the resonance chamber and the combustion chamber, allow relative rotation between the combustion chamber and the resonance chamber. With the damper according to the invention, by providing a compensation assembly ensuring compensation of the relative rotation between the combustion chamber and the resonant cavity, the operating life is thus extended.

Description

Technical field [0001] The present invention relates to a gas turbine, and more particularly, to a damper for reducing pulsation in a combustion chamber of a gas turbine. Background technique [0002] In conventional gas turbines, acoustic oscillations usually occur in the combustion chamber of the gas turbine due to combustion instability and changes during the combustion process. This acoustic oscillation can develop into a very significant resonance. This type of oscillation, also known as combustion chamber pulsation, can use the amplitude of the combustion chamber itself subject to severe mechanical loads and the associated pressure fluctuations, which can decisively shorten the life of the combustion chamber, and in the worst case, it can even be Cause the destruction of the combustion chamber. [0003] Generally, a type of damper called Helmholtz damper is used to dampen the pulsation generated in the combustion chamber of a gas turbine. Currently, a major difficulty in u...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/00
CPCF23R3/002F23R3/60F23M2900/05002F23R2900/00005F23R2900/00014F23M20/005F23R3/16
Inventor U.本滋N.奈拉伊
Owner ANSALDO ENERGIA IP UK LTD
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