Turbine Nozzle Vane Cooling Circuit for Thermal Erosion Resistance
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Solution Overview
Problem
Existing stationary engine structures in gas turbine engines lack effective cooling mechanisms for components like nozzle vanes, leading to thermal erosion and degradation.
Innovation Solution
A cooling system is integrated into the turbine engine structure, featuring a plenum, reverse flow combustor, and nozzle structure with cooling circuits that bleed air from the plenum to provide cooling air through passages in the platform and vanes, effectively cooling the turbine nozzle and vanes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If existing stationary engine structures are used without integrated cooling mechanisms, then the device complexity is reduced, but thermal erosion and degradation occur leading to reduced reliability
Solution Approach 1:
The cooling circuits are integrated directly into the nozzle structure, merging the cooling function with the existing nozzle components. The first cooling circuit is formed in the first platform and the second cooling circuit is formed in the vanes, combining structural support and thermal management in single components, thereby improving reliability without proportionally increasing device complexity
Solution Approach 2:
Cooling air acts as an intermediary substance that absorbs heat from the nozzle structure and vanes. The cooling circuits channel this intermediary cooling air through passages in the platform and vanes, transferring thermal energy away from critical components to prevent thermal erosion and degradation
2Temperature
If cooling air is bled from the plenum to cool the nozzle structure, then thermal management is improved, but energy loss increases
Solution Approach 1:
Cooling air is extracted (bled) from the plenum through the cooling circuits to specifically target and remove heat from the nozzle structure and vanes. This extraction of cooling air from the main flow path allows localized thermal management where it is most needed, controlling nozzle structure temperature while utilizing otherwise available cooling potential
Solution Approach 2:
The plenum, which naturally contains high-energy cooling air from the combustion process, is utilized as a source for the cooling circuits. What would otherwise be wasted thermal energy in the plenum is converted into a beneficial cooling resource by channeling it through the cooling circuits to protect the nozzle structure from thermal damage
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 erosion and degradation of turbine vanes by efficiently transferring heat energy away, enhancing the durability and performance of the engine components.
Implementation Method 1
The cooling system effectively reduces thermal erosion and degradation of turbine vanes by efficiently transferring heat energy away
Data Source
AI summary
An assembly is provided for a turbine engine. This assembly includes an engine structure, and the engine structure includes a plenum, a reverse flow combustor, a nozzle structure and a cooling circuit. The reverse flow combustor is disposed in the plenum and includes a combustion chamber. The nozzle structure is arranged at an outlet from the combustion chamber. The nozzle structure includes a first platform, a second platform and a plurality of vanes arranged circumferentially about an axis. The vanes extend across the flowpath from the first platform to the second platform. The cooling circuit extends in the first platform and between a circuit inlet into the cooling circuit and a circuit outlet from the cooling circuit. The circuit inlet is fluidly coupled with and disposed along the plenum. The circuit outlet is fluidly coupled with and disposed along the flowpath.