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Can to can modal decoupling using can-level fuel splits

A fuel flow, fuel flow rate technology, applied in the control of thermal conditions of the combustion chamber, turbine/propulsion fuel delivery system, fuel control of the turbine/propulsion unit, etc., can solve problems such as limited maneuverability space

Active Publication Date: 2011-04-27
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This approach implies that the operability space can be limited by in-phase coherent tones

Method used

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  • Can to can modal decoupling using can-level fuel splits
  • Can to can modal decoupling using can-level fuel splits
  • Can to can modal decoupling using can-level fuel splits

Examples

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Embodiment Construction

[0087] figure 1 Diagrammatically shows a side view of a gas turbine system 100 in which an exemplary multi-circuit manifold may be implemented. In the exemplary embodiment, gas turbine 100 includes a compressor 110 configured to compress ambient air. One or more combustor cans 120 are in flow communication with compressor 110 through diffuser 150 . Combustor can 120 is configured to receive compressed air 115 from compressor 110 and combust fuel flow from fuel nozzles 160 to generate combustor exit airflow 165 that travels through combustor 140 to turbine 130 . Portions of the combustor 140 are included in a transition piece 145 that is coupled to the combustor can 120 . Turbine 130 is configured to expand the combustor out of airflow 165 to drive an external load. Combustor can 120 includes an outer shroud 170, and an end cap 175 configured to couple with a fuel hose (not shown) from a combustion manifold (not shown). Currently, a single fuel manifold provides a single f...

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PUM

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Abstract

In exemplary embodiments, a gas turbine system is provided. The gas turbine system can include a compressor configured to compress air and combustor cans in flow communication with the compressor, the combustor cans being configured to receive compressed air from the compressor and to combust a fuel stream. The gas turbine system can also include a multi-circuit manifold coupled to the combustor cans and configured to provide a split fuel stream from the fuel stream to the combustor cans.

Description

technical field [0001] The subject matter disclosed herein relates to gas turbines, and more particularly to can combustor de-tuning and frequency de-coupling through multi-circuit fuel manifolds. Background technique [0002] In gas turbines, multi-can combustors are in acoustic communication with each other due to the connections between the various cans. When heat release fluctuations in the combustor couple with the acoustic tone of the burner, large pressure oscillations, also known as combustion dynamics, result. Some of the acoustic tones of these combustor cans may be in phase with adjacent cans, while other tones may be out of phase with adjacent cans. In-phase tones are of particular concern because if they coincide with the blade natural frequency, they can excite the turbine blades in the hot gas path, affecting blade life. In-phase tones are of particular concern when the instabilities in different bins are coherent (ie there is a strong relationship between f...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C3/14F02C7/228
CPCF02C7/228F02C9/26F05B2270/15F05D2270/14
Inventor V·纳拉L·B·小戴维斯韩飞金冠佑K·K·辛赫S·K·斯里尼瓦桑K·K·文卡塔拉曼
Owner GENERAL ELECTRIC CO