Turbine Link Wall Coolant Circuit for Thermal Gradient Reduction
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Solution Overview
Problem
The existing turbine engine combustion chamber link walls suffer from temperature gradients and mechanical stresses leading to crack formation and reduced lifespan, with current cooling solutions being inadequate.
Innovation Solution
Incorporating a coolant fluid circuit within the link walls to reduce temperature variations, with the circuit extending between the radially inner and outer ends, and utilizing a motor and control system to manage coolant flow, especially during critical flight phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If holes are formed in link walls or shrouds to cool the link walls, then the temperature gradient is reduced, but the structural strength is compromised
Solution Approach 1:
The patent applies hydraulic cooling by introducing a coolant fluid circuit within the link wall structure. The circuit delivers cooling fluid through channels formed in the link wall, allowing direct thermal contact between the coolant and the heated regions. This hydraulic approach effectively reduces temperature gradients without requiring holes that would compromise structural integrity, as the cooling channels are integrated within the existing wall geometry.
2Temperature
If conventional cooling holes are formed in link walls, then cooling effectiveness is improved, but device complexity increases
Solution Approach 1:
The patent merges the cooling function with the structural link wall by integrating the coolant fluid circuit directly within the link wall geometry. The cooling channels are formed as part of the link wall manufacturing process, combining thermal management and structural support into a single integrated component. This eliminates the need for separate cooling systems or additional holes, thereby reducing device complexity while maintaining cooling effectiveness.
3Temperature
If coolant fluid circuit is introduced in link wall, then temperature gradient is reduced, but device complexity increases
Solution Approach 1:
The patent utilizes a structured approach where the link wall incorporates internal channels forming a controlled fluid passage network. Rather than adding external cooling components, the link wall itself is designed with integrated coolant circuits that follow the thermal gradient paths. This internal channel integration reduces temperature gradients effectively while minimizing overall system complexity by embedding the cooling function within the existing structural geometry.
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 coolant fluid circuit significantly reduces temperature gradients, enhancing the mechanical strength and lifespan of the link walls without additional fuel consumption, as heat exchange occurs through turbine vibration.
Implementation Method 1
a temperature gradient is formed in the inner and outer annular link walls 20 and 22, between their ends where they meet the inner and outer annular shrouds 12 and 14, respectively, and their opposite ends where they meet the inner and outer casings 24 and 26
Implementation Method 2
at least a first one of the inner and outer annular link walls includes at least one coolant fluid circuit extending between the radially inner and outer ends of said first annular link wall
Implementation Method 3
heat exchange occurs through turbine vibration
Data Source
AI summary
A turbine engine including a combustion chamber having an inner annular shroud and an outer annular shroud that are coaxial with each other and that are connected at their downstream ends respectively to an inner annular link wall and to an outer annular link wall, for linking respectively to an inner casing and to an outer casing. At least a first one of the inner and outer annular link walls includes at least one coolant fluid circuit extending between the radially inner and outer ends of said first annular link wall.