Transition Nozzle Cooling via Rib-Defined Channels
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Solution Overview
Problem
Gas turbine systems face leakage issues between the combustor and turbine, leading to decreased performance and emissions efficiency, and increased operating temperatures shorten the lifespan of components, while traditional seal maintenance is inefficient and costly.
Innovation Solution
A transition nozzle with a cooling duct defined between the liner and wrapper, featuring a plurality of ribs that create cooling channels, supplied with a cooling fluid such as steam to enhance cooling and reduce thermal stress.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If seals are used between combustor and turbine to reduce leakage, then emissions capability is improved, but seal reliability deteriorates due to weakened seals from increased operating temperatures
Solution Approach 1:
The patent removes the seals between the combustor and turbine, eliminating the sealing function from this location. Instead of maintaining seals that fail at high temperatures, the design accepts the leakage and manages it through other means, thereby eliminating the reliability issue while maintaining emissions performance.
Solution Approach 2:
The transition nozzle wrapper acts as an intermediary thermal barrier between the hot combustor and the turbine. By providing thermal protection to the turbine inlet, it reduces the temperature differential that would otherwise require sealing, allowing the system to operate without seals while maintaining performance.
2Object-generated harmful factors
If operating temperature of combustor is increased to improve emissions capability, then emissions capability is improved, but combustor lifespan deteriorates due to thermal stress
Solution Approach 1:
The cooling channels in the transition nozzle wrapper are pre-configured to receive cooling fluid before the combustor reaches damaging temperatures. This preliminary cooling action prevents thermal stress accumulation and extends the combustor's operational life while maintaining high operating temperatures for emissions compliance.
Solution Approach 2:
The transition nozzle wrapper serves as a thermal intermediary between the high-temperature combustor and the turbine. It absorbs and dissipates heat through its cooling channels, protecting the combustor from thermal stress while allowing the combustor to operate at high temperatures needed for low emissions.
3Productivity
If seals are used to prevent leakage, then performance efficiency is improved, but maintenance complexity increases due to tedious and costly seal maintenance
Solution Approach 1:
The patent eliminates seals from the combustor-turbine interface, removing the maintenance burden entirely. The design accepts that some leakage occurs but manages it through the cooling and thermal management system, thereby improving ease of repair while maintaining performance efficiency.
4Strength
If cooling ducts are added to transition nozzle, then thermal stress is reduced, but device complexity increases
Solution Approach 1:
The transition nozzle wrapper performs multiple functions: it provides structural support, acts as a thermal barrier, and incorporates cooling channels for heat dissipation. By combining these functions into a single component, the design reduces thermal stress without proportionally increasing device complexity.
Solution Approach 2:
The cooling channels are nested within the walls of the transition nozzle wrapper itself, rather than being separate external systems. This nested integration allows the cooling function to be embedded in the existing structure, reducing overall complexity while providing effective thermal stress relief.
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 cooling system effectively reduces thermal stress and maintains performance by providing efficient cooling to the transition nozzle, potentially extending the lifespan of turbine components and improving emissions efficiency.
Implementation Method 1
A cooling fluid source may be supplied to the cooling duct to facilitate cooling the transition portion
Implementation Method 2
As the cooling fluid flows through the cooling channels, it facilitates cooling the transition nozzle
Data Source
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AI summary
A transition portion (204) is provided. The transition portion (204) includes a liner (202), a wrapper (214) circumscribing the liner such that a cooling duct (216) is defined between the wrapper and the liner, a cooling fluid inlet (230) configured to supply a cooling fluid to the cooling duct, and a plurality of ribs (220) coupled between the liner and the wrapper such that a plurality of cooling channels (222) are defined in the cooling duct.