Segmented Combustor Nozzle Modules for Hydrogen Flame Stability
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Solution Overview
Problem
Gas turbines using hydrogen fuel experience flame instability and structural degradation due to high combustion rates, leading to reliability issues and increased nitrogen oxide generation.
Innovation Solution
A combustor nozzle with multiple nozzle modules, featuring a fuel supply pipe, manifolds, and fuel mixers that improve air-fuel mixing characteristics, including air inlet ports, fuel ports, and extensions to enhance mixing flow paths, minimizing nitrogen oxide production and stabilizing the flame.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If hydrogen fuel is used in gas turbine combustors, then combustion efficiency is improved, but flame stability deteriorates and structural degradation occurs due to high combustion rates
Solution Approach 1:
The nozzle is divided into multiple nozzle modules (first, second, and third nozzle modules) with different injection patterns. The first nozzle module injects fuel in a first pattern, the second in a second pattern, and the third in a third pattern, creating segmented combustion zones that improve overall flame stability while maintaining high combustion efficiency with hydrogen fuel.
Solution Approach 2:
Different regions of the combustor are provided with nozzles having different injection patterns and orientations. The first, second, and third nozzle modules are arranged to create locally optimized combustion conditions in different spatial zones, allowing each region to contribute to overall flame stability while maintaining high productivity.
2Productivity
If hydrogen fuel is used in gas turbine combustors, then combustion efficiency is improved, but nitrogen oxide generation increases
Solution Approach 1:
By segmenting the fuel injection into multiple patterns through different nozzle modules, the combustion process is distributed across multiple zones, reducing peak temperatures and localized nitrogen oxide formation while maintaining high combustion efficiency.
Solution Approach 2:
Different nozzle modules create locally optimized combustion conditions with varying air-fuel mixing characteristics, allowing control over temperature distribution and oxygen availability to minimize nitrogen oxide generation while preserving combustion efficiency.
3Device complexity
If conventional nozzles are used, then device complexity is low, but air-fuel mixing characteristics are insufficient leading to poor combustion performance
Solution Approach 1:
The nozzle system is segmented into multiple modules with distinct injection patterns, creating complex air-fuel mixing characteristics through coordinated operation of simpler individual units, thereby achieving superior combustion performance without excessive overall complexity.
Solution Approach 2:
Each nozzle module serves multiple functions: fuel injection, air-fuel mixing, and flame stabilization. This multi-functionality allows the system to achieve excellent air-fuel mixing characteristics while keeping individual component complexity manageable through standardized modular design.
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
The solution effectively improves air-fuel mixing, stabilizes the flame, and reduces nitrogen oxide generation, enhancing the reliability and efficiency of gas turbines when using hydrogen fuel.
Implementation Method 1
an mixing flow path through which air and the fuel flow
Data Source
AI summary
A combustor nozzle including nozzle modules, a combustor, and a gas turbine including the same are proposed. The nozzle module includes a fuel supply pipe having an internal fuel flow path, manifolds communicating with the fuel supply pipe and arranged in a row in a radial direction, and fuel mixers disposed along a circumferential direction at the rear side of the manifold to receive the fuel from the manifold and inject the fuel, each of the plurality of fuel mixers including a mixer body having one end communicating with the manifold, the other end that is opened, and an mixing flow path through which air and the fuel flow, an air inlet port formed on a lateral side of the mixer body, a fuel port formed inside the mixer body and discharging the fuel supplied from the manifold to the mixing flow path, and an extension located at the other end of the mixer body.