Gas Turbine Combustor Cooling Measurement Flat Plate Model
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Solution Overview
Problem
Full-scale model experiments for gas turbine combustors are hindered by high costs and complex result analysis, necessitating the development of a cost-effective method to measure wall surface cooling characteristics while ensuring consistency with actual operating conditions.
Innovation Solution
A device and method for measuring wall surface cooling characteristics of gas turbine combustors, featuring a flat plate cooling structure model with specific aperture, spacing, and holes-area ratios, and adjusting parameters like temperature and flow rate to simulate actual operating conditions, utilizing a hot flow inlet, cold flow inlet, and gas discharge sections with rectification orifice plates and thermal imaging for accurate measurement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If full-scale model experiments are conducted for gas turbine combustors, then measurement accuracy is improved, but experimental cost and device complexity increase significantly
Solution Approach 1:
The patent creates a simplified model copy of the combustor wall surface with cooling holes, rather than using a full-scale combustor. The model replicates the essential cooling structure characteristics (hole distribution, spacing, and geometry) to enable accurate measurement of cooling characteristics while dramatically reducing device complexity and experimental cost.
Solution Approach 2:
The patent extracts the key cooling characteristic elements from the complex combustor system, focusing specifically on the wall surface cooling holes and their flow patterns. By isolating and studying only the essential cooling components in a simplified model, the system achieves accurate measurement without the complexity of a complete combustor setup.
2Measurement precision
If full-scale model experiments are conducted for gas turbine combustors, then measurement accuracy is improved, but experimental cost increases
Solution Approach 1:
The patent creates a simplified model copy of the combustor wall surface with cooling holes, rather than using a full-scale combustor. The model replicates the essential cooling structure characteristics (hole distribution, spacing, and geometry) to enable accurate measurement of cooling characteristics while dramatically reducing device complexity and experimental cost.
Solution Approach 2:
The patent employs a simplified, inexpensive model structure that can be easily manufactured and potentially replaced or modified for different cooling configurations. This approach avoids the high cost of building and maintaining full-scale combustor experimental setups, making repeated experiments more economically viable.
3Measurement precision
If full-scale model experiments are conducted for gas turbine combustors, then measurement accuracy is improved, but result analysis complexity increases
Solution Approach 1:
The patent extracts the key cooling characteristic elements from the complex combustor system, focusing specifically on the wall surface cooling holes and their flow patterns. By isolating and studying only the essential cooling components in a simplified model, the system achieves accurate measurement without the complexity of a complete combustor setup, thereby simplifying result analysis.
Solution Approach 2:
The patent segments the complex combustor system into its fundamental cooling elements (cooling holes, wall surface geometry, and local flow patterns). By studying these segmented, simplified components separately, the research avoids the analytical complexity of full-scale combustor simulations while maintaining measurement accuracy for cooling characteristics.
4Device complexity
If a small-sized model is designed to measure cooling characteristics, then device complexity is reduced, but consistency with actual operating conditions deteriorates
Solution Approach 1:
The patent carefully controls and matches key dimensionless parameters (such as Reynolds number, Mach number, and geometric similarity ratios) between the small-scale model and the actual combustor operating conditions. By adjusting flow rates, temperatures, and pressure conditions in the experiment, the model achieves dynamic similarity with the full-scale system, ensuring reliable results despite the size reduction.
Solution Approach 2:
The patent focuses on achieving accurate local flow and thermal conditions at the cooling hole region, rather than attempting to replicate the entire combustor environment. By concentrating on the critical local parameters (cooling hole geometry, local flow velocity, temperature gradients), the simplified model maintains reliability for cooling characteristic measurements while keeping overall device complexity low.
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 improves experimental accuracy, reduces complexity and costs, and allows for real-time measurement of cooling characteristics, enhancing the understanding of cooling mechanisms and efficiency.
Implementation Method 1
the cold flow inlet section and the experimental section are communicated through cooling holes of a cooling structure model
Implementation Method 2
a tail end of the experimental section is provided with a thermocouple threading seat
Implementation Method 3
the experimental section is provided with an infrared thermal imaging measurement window
Data Source
AI summary
A device for measuring a wall surface cooling characteristic of a gas turbine combustor and a modeling method thereof are provided. The device includes a hot flow inlet section, a cold flow inlet section, and a gas discharge section, where the cold flow inlet section is communicated with an experimental section; the cooling structure model is a flat plate structure; a tail end of the experimental section is provided with a thermocouple threading seat; the gas discharge section is provided with a laser injection window; and the experimental section is provided with an infrared thermal imaging measurement window and a visual observation window. The modeling method includes: modeling the wall surface of the gas turbine combustor into the flat plate structure; determining a pressure, a temperature, and a velocity on a hot flow side of the device; and determining a material and a thickness of the cooling structure model.