Combustor Inlet Flow Conditioner for Uniform Air Distribution
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Solution Overview
Problem
Non-uniform flow of pressurized air into the premix passage of a fuel nozzle in gas turbine combustors can lead to inefficient combustor operations.
Innovation Solution
The implementation of an inlet flow conditioner with a sleeve that circumferentially surrounds a portion of the fuel nozzle assembly, extending from the combustion liner to the end cover, and defines a plurality of apertures for fluid communication, which helps to distribute the flow uniformly into the premix passage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If pressurized air flows directly from the compressor into the combustor head end volume, then the system structure remains simple, but the flow becomes non-uniform which reduces combustor efficiency
Solution Approach 1:
The patent introduces a flow conditioner as an intermediary component between the compressor inlet and the combustor head end volume. This flow conditioner includes a flow straightening section with vanes that condition the incoming air flow, and a flow distribution section with distribution plates that evenly distribute the flow to multiple burners. This intermediary device transforms the non-uniform direct flow into a uniform distributed flow, resolving the contradiction between structural simplicity and combustor efficiency.
2Productivity
If a flow conditioner is added to distribute air flow uniformly, then combustor efficiency improves, but device complexity increases
Solution Approach 1:
The flow conditioner is segmented into distinct functional sections: a flow straightening section with individual vanes for each burner, and a flow distribution section with separate distribution plates. Each burner receives conditioned air through its own dedicated flow path. This segmentation allows the complex flow conditioning function to be broken down into manageable, modular components that can be designed and manufactured independently, reducing overall system complexity while maintaining high combustor efficiency.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution ensures a more uniform air flow into the premix passage, enhancing the efficiency of the combustor by promoting a consistent fuel and air mixture for combustion, thereby improving the overall performance of the gas turbine.
Implementation Method 1
The sleeve defines a plurality of apertures circumferentially spaced about the sleeve... A portion of the inner surface of the end cover and the sleeve define a head end volume of the combustor... An inlet to a premix passage of at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume
Data Source
AI summary
A combustor includes an inlet flow conditioner. The inlet flow conditioner includes a sleeve that circumferentially surrounds a portion of a fuel nozzle assembly and that extends from a forward end of a combustion liner to an inner surface of an end cover. The sleeve defines a plurality of apertures circumferentially spaced about the sleeve. A portion of the inner surface of the end cover and the sleeve define a head end volume of the combustor. An inlet to a premix passage of at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume.