Turbine Cooling Conduits with Offset Rows for Heat Transfer
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Solution Overview
Problem
Current cooling systems for turbine engines, particularly gas turbine engines, face inefficiencies in cooling high-temperature components like the high pressure turbine, where the temperature difference between the compressor air and turbine air limits effective heat transfer, and clogging of cooling conduits can reduce cooling efficiency.
Innovation Solution
The design incorporates a trailing edge cooling passage with cooling conduits arranged in multiple rows, where the second row has a smaller cross-sectional area than the first row, creating an offset arrangement that enhances heat transfer through impingement of the cooling fluid and reduces clogging risks by increasing turbulence, and the conduits are formed using a core that allows for efficient manufacturing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling conduits are arranged in multiple rows with decreasing cross-sectional area, then heat transfer coefficient is improved, but manufacturing complexity increases
Solution Approach 1:
The cooling conduits are arranged in multiple rows where each subsequent row has a smaller cross-sectional area than the previous row. This local variation in geometry creates impingement of the cooling fluid on downstream conduits, significantly enhancing the heat transfer coefficient in critical cooling regions without requiring a complete redesign of the entire cooling system.
Solution Approach 2:
The invention transitions from a single-row or uniform cross-section cooling conduit design to a multi-row arrangement with varying cross-sectional areas along the flow direction. This dimensional variation creates a three-dimensional cooling pattern where cooling fluid impinges on subsequent rows, adding a new dimension to heat transfer enhancement while maintaining a relatively simple overall conduit structure.
2Ease of manufacture
If cooling conduits have uniform cross-sectional area, then manufacturing is simplified, but cooling efficiency decreases due to lower turbulence
Solution Approach 1:
The invention modifies the cross-sectional area parameter of the cooling conduits along the flow direction, creating a gradient where each subsequent row has a smaller cross-section. This parameter change increases turbulence and impingement effects, thereby enhancing cooling efficiency while maintaining a systematic geometric progression that can be manufactured using standard molding or machining processes.
3Reliability
If cooling conduits are clogged, then cooling efficiency is reduced, but increasing turbulence to prevent clogging increases pressure drop
Solution Approach 1:
The varying cross-sectional area arrangement creates dynamic flow conditions where the cooling fluid accelerates as it passes from larger to smaller cross-sections. This dynamic variation in flow velocity increases turbulence and reduces the likelihood of particulate matter settling and clogging the conduits, thereby improving system reliability while the gradual transition minimizes excessive pressure drops.
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 heat transfer coefficients, reduces the risk of clogging, and optimizes cooling efficiency, leading to enhanced performance and reduced bleed air requirements, thereby increasing overall engine efficiency.
Implementation Method 1
cooling is accomplished by ducting cooler air from the high and/or low pressure compressors to the engine components that require cooling
Implementation Method 2
routing the cooling air through the blade to cool different portions of the blade
Implementation Method 3
creating an offset arrangement that enhances heat transfer through impingement of the cooling fluid and reduces clogging risks by increasing turbulence
Data Source
AI summary
An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.