Forward Facing Step Nozzle for Turbine Cooling
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Solution Overview
Problem
Existing impingement cooling assemblies for turbine machinery require complex setups to enhance heat transfer coefficients, which can lead to increased efficiency and reduced cooling flow consumption, but these setups are intricate and may not be optimally effective.
Innovation Solution
A forward-facing step nozzle with elongated first sides and narrow second sides is used to fluidly couple two cooling cavities within a turbine assembly or combustion chamber, creating a channel with a smaller cross-sectional area at the steps, which directs cooling air efficiently from a larger cavity to a smaller one, enhancing heat transfer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a complicated assembly is used to improve heat transfer coefficient, then cooling performance is improved, but device complexity increases
Solution Approach 1:
The cooling assembly is divided into multiple cooling cavities (first cooling cavity, second cooling cavity, third cooling cavity) that are spatially segmented and functionally differentiated. Each cavity receives cooling air through specific nozzles and directs it to specific target walls, allowing the system to achieve complex cooling patterns through simple, modular cavity structures rather than a single complicated assembly
Solution Approach 2:
Different cooling cavities are configured with different nozzle types (impingement nozzles, slot nozzles, film nozzles) and different geometries to provide locally optimized cooling for different target walls. The first cooling cavity targets a first wall, the second cooling cavity targets a second wall, and the third cooling cavity targets a third wall, allowing each region to receive cooling tailored to its specific heat load and geometric requirements
2Temperature
If higher heat transfer coefficient is achieved, then cooling performance improves, but cooling flow consumption may increase
Solution Approach 1:
The system utilizes parameter changes in the cooling air flow by directing it through multiple cavities with different nozzle configurations. The impingement nozzles create high-velocity jets for intense localized cooling, while slot nozzles provide distributed cooling patterns, and film nozzles create protective cooling films. These parameter variations allow the system to achieve high heat transfer coefficients with optimized cooling flow distribution rather than simply increasing overall flow quantity
Solution Approach 2:
The cooling flow is segmented into multiple streams that are distributed through different cavities and nozzles. This segmentation allows each cooling stream to be optimized for its specific function (impingement, slot, or film cooling) and target region, improving the overall efficiency of cooling flow utilization and reducing total consumption needed to achieve the desired heat transfer coefficient
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 configuration improves the heat transfer coefficient compared to baseline channels without the step nozzle, allowing for better cooling performance and potentially higher turbine inlet temperatures while reducing cooling flow consumption.
Implementation Method 1
Impingement cooling systems utilize air flowing inside an assembly such as a turbine assembly or combustion chamber. In the assembly, the pressurized air is led through one or more impingement holes. The high velocity jet is directed to a target wall which is under a high heat load.
Implementation Method 2
The pressurized air is led through one or more impingement holes. The high velocity jet is directed to a target wall
Implementation Method 3
One issue with known impingement cooling assemblies, however, is that the cooling assemblies tend to require complicated assemblies in order to improve the heat transfer coefficient over the turbine assemblies.
Data Source
AI summary
An assembly comprises a first cooling cavity disposed within one or more of a turbine assembly or a combustion chamber of an engine. The first cooling cavity directs cooling air within the one or more of the turbine assembly or the combustion chamber. The assembly comprises a second cooling cavity also disposed within the one or more of the turbine assembly or the combustion chamber. The second cooling cavity receives at least some of the cooling air from the first cooling cavity. A forward facing step nozzle forms a channel that fluidly couples the first cooling cavity with the second cooling cavity. The step nozzle includes steps having elongated first sides and narrow second sides. The elongated first sides of the steps protrude into the channel such that a cross-sectional area of the channel of the step nozzle at the steps is smaller than a cross-sectional area of the channel of the step nozzle outside of the steps.