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System and method for determining fuel composition fuel used in gas turbines

A fuel and fuel nozzle technology, applied in the direction of turbine/propulsion fuel delivery system, fuel control of turbine/propulsion device, charging system, etc., can solve problems such as complex control

Inactive Publication Date: 2018-05-29
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Disadvantageously, the specific composition of the fuel supplied to the burner may not be known, thereby complicating the control to maintain the burner within desired operating parameters

Method used

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  • System and method for determining fuel composition fuel used in gas turbines
  • System and method for determining fuel composition fuel used in gas turbines
  • System and method for determining fuel composition fuel used in gas turbines

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Embodiment Construction

[0017] One or more specific embodiments of the invention will be described below. In an effort to provide a concise description of these embodiments, it may not be possible for all features of an actual implementation to be described in this specification. It should be understood that in the development of any such actual implementation in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developer's specific goals, such as compliance with system-related and Business-Related Constraints. Furthermore, it should be appreciated that such development efforts might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and production for those of ordinary skill having the benefit of this disclosure.

[0018] When introducing elements of various embodiments of the invention, the articles "a," "an," "the," and "said" are intended to mean one or more of those elements. The terms "...

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PUM

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Abstract

The invention disclsoes a system and a method for determining fuel composition fuel used in gas turbines. The system includes a combustor assembly that receives a fuel flow. The system includes a pressure sensor disposed within the combustor assembly that measures a pressure of the fuel flow from a fuel supply to a fuel nozzle of the combustor assembly. The system includes a controller communicatively coupled to the pressure sensor. The controller is configured to receive a pressure measurement from the pressure sensor. The pressure measurement is a current operating parameter of the combustorassembly.

Description

technical field [0001] The subject matter of the present invention relates to gas turbine systems, and more particularly to a system for determining the fuel composition for a gas turbine system. Background technique [0002] A gas turbine system typically includes at least one gas turbine engine having a compressor, a combustor, and a turbine. The combustor may have one or more fuel nozzles for receiving fuel and injecting it into the combustion chamber. Certain fuel gases, such as nitrogen oxides (NOx), sulfur oxides (SOx), carbon monoxide (CO), carbon dioxide (CO2), and the like, can result in undesirable exhaust emissions. In some cases, emission levels may exceed thresholds for the gas turbine system, such as minimum emission compliance levels. Disadvantageously, the specific composition of the fuel supplied to the combustor may not be known, thereby complicating the controls to maintain the combustor within desired operating parameters. Contents of the invention ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C9/28
CPCF02C9/28F05D2240/35F02C9/26F23N1/002F23N5/242F05D2270/00F23K2300/00F02C9/40F05D2270/44F23N2241/20F23K2300/20Y02T50/60F05D2270/301F23R3/36
Inventor J.哈珀A.阿塔纳里
Owner GENERAL ELECTRIC CO