Multi-turn Turbine Blade Cooling Circuit Topology
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Solution Overview
Problem
Traditional trailing edge cooling circuits in turbine blades inefficiently exhaust coolant without utilizing its maximum heat capacity, leading to suboptimal cooling performance.
Innovation Solution
A trailing edge cooling system with multi-turn cooling circuits that reuses coolant flow by directing it through a series of outward, turn, and return legs, allowing for enhanced heat transfer and subsequent use in other cooling circuits within the turbine blade, such as tip and platform cooling circuits.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If traditional single-pass cooling circuits are used, then the structure is simple, but the cooling efficiency is insufficient because coolant heat capacity is not fully utilized
Solution Approach 1:
The cooling circuit is segmented into multiple passes (first pass, second pass, third pass) with distinct functions. The first pass cools the trailing edge, the second pass cools the platform region, and the third pass provides film cooling. This segmentation allows the coolant to sequentially serve multiple cooling functions, maximizing heat capacity utilization while maintaining manageable structural complexity through modular circuit design
Solution Approach 2:
The cooling circuit implements continuous coolant flow through multiple passes without interruption. The coolant flows continuously from the first pass through the second pass to the third pass, maintaining useful cooling action throughout the entire circuit. This continuous flow ensures that the coolant's heat capacity is fully utilized across all cooling zones rather than being exhausted after a single pass
2Loss of energy
If multi-turn cooling circuits are implemented, then cooling efficiency is improved by reusing coolant, but device complexity increases
Solution Approach 1:
Multiple cooling functions are merged into a single integrated cooling circuit system. The first pass, second pass, and third pass are combined into one continuous coolant flow path, allowing the same coolant to perform multiple cooling tasks. This merging reduces the need for separate cooling circuits for different zones, optimizing cooling efficiency while controlling overall system complexity through integration
Solution Approach 2:
The cooling circuit is designed with multi-functionality where a single coolant flow serves multiple purposes: cooling the trailing edge (first pass), cooling the platform region (second pass), and providing film cooling (third pass). This universal cooling approach allows one cooling system to handle multiple thermal management requirements, improving overall cooling efficiency without proportionally increasing device complexity
3Ease of operation
If coolant is exhausted after single use, then the system is simple to operate, but heat transfer maximization is not achieved
Solution Approach 1:
The cooling circuit is pre-configured with multiple passes and flow direction control mechanisms before operation. The circuit geometry and flow path are designed in advance to automatically guide coolant through the optimal sequence of cooling zones (trailing edge, then platform, then film cooling). This preliminary design ensures that heat transfer is maximized without requiring complex real-time operational decisions, maintaining ease of operation while achieving superior thermal performance
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 maximizes the heat transfer and cooling efficiency of the turbine blade by reusing coolant flow, extending its heat capacity for further cooling applications within the turbine system, thereby improving overall performance.
Implementation Method 1
Cooling air (or other suitable coolant) provided by, for example, a compressor of a gas turbine system, may be passed through and out of the cooling passages to cool various portions of the multi-wall airfoil and/or turbine blade
Data Source
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AI summary
A trailing edge cooling system for a turbine blade 2 is disclosed. The system may include a cooling circuit including an outward leg 34, and a return leg 38 positioned adjacent the outward leg. The outward and return leg each may extend toward and away, respectively, from a trailing edge 16 of the turbine blade. The cooling circuit may also include a plurality of turn legs 36. The plurality of turn legs may include a turn leg positioned directly adjacent the trailing edge of the turbine blade, and a distinct turn leg positioned axially adjacent the turn leg, and opposite the trailing edge of the turbine blade. The distinct turn leg may be oriented non-parallel to at least one of the outward leg and the return leg.