Integrated Combustor and Stage 1 Nozzle for Gas Turbine
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Solution Overview
Problem
Gas turbine combustors face challenges with leakage at the interface between the combustor and turbine sections, leading to elevated NOx emissions and requiring the use of seals, which complicates the design and increases part count, making it difficult to integrate the first stage nozzle into the transition piece due to the conventional length of the combustor.
Innovation Solution
The integration of a combustion chamber with small scale mixing devices that concentrate heat release and reduce flame length, allowing the stage one nozzle, liner, and transition piece to be combined into a single part, thereby eliminating the need for seals and reducing combustor length.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the combustor and turbine are kept as separate components with seals at the interface, then leakage is minimized, but the device complexity increases and emissions capability deteriorates
Solution Approach 1:
The patent merges the combustor and turbine into a single integrated component by integrating the stage 1 nozzle into the combustor structure. This eliminates the interface between separate components, removing the need for seals and eliminating leakage issues while reducing device complexity
2Length of stationary object
If the transition piece length is reduced to enable integration, then the combustor length decreases, but the combustion completeness may be compromised
Solution Approach 1:
The patent changes the combustion parameters by implementing a multi-zone combustion chamber with different combustion intensities. The first combustion zone operates at high intensity with high swirl and fuel injection, while the second zone provides lower intensity combustion, enabling complete combustion in a shorter overall length
3Reliability
If conventional combustion design is used, then the combustor length is sufficient for complete combustion, but integration with stage 1 nozzle becomes impractical
Solution Approach 1:
The patent merges the combustor and stage 1 nozzle into a single integrated part by redesigning the combustion chamber to be more compact. The multi-zone combustion approach enables complete combustion in a shorter length that is practical for integration, eliminating separate components and reducing part count
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 approach reduces the number of parts, minimizes leakage, and enhances emissions control by creating a compact combustor design that reduces chamber-to-chamber variation and part count, leading to lower costs and reduced outage times.
Implementation Method 1
At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length
Implementation Method 2
The mixture is then ignited generating hot combustion gases
Data Source
AI summary
An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.