Turbine Bucket Cooling Control via Shape Memory Alloy
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Solution Overview
Problem
Conventional gas turbine cooling systems are optimized for full-load operations, leading to inefficient cooling during part-load and off-design conditions, where reduced cooling is necessary to maintain component temperatures and efficiency.
Innovation Solution
A cooling gas flow control device with an internal pathway and an adjustable gas flow valve using shape memory materials that adjust gas flow based on compressor exit parameters, such as temperature, to optimize cooling gas delivery to the turbine rotor and components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If cooling circuits are optimized for full load operations, then component cooling is sufficient at full load, but excessive cooling is provided during part load operations reducing efficiency
Solution Approach 1:
The patent applies a variable geometry nozzle that can dynamically adjust its opening area in response to changing operating conditions. The nozzle geometry is modified based on whether the turbine is operating at full load or part load, allowing the cooling air flow to be optimized for each operating regime. This dynamic adjustment prevents excessive cooling air bleed during part load operations while maintaining adequate cooling when needed.
Solution Approach 2:
The patent changes the geometric parameters of the cooling air nozzle to match different operating conditions. By varying the nozzle opening area as a function of operating parameters (such as power output or temperature differential), the system adapts the cooling air flow rate to match actual cooling demands. This parameter change allows the system to transition from excessive cooling at full load to appropriate cooling at part load.
2Temperature
If cooling air is bled from compressor to cool turbine components, then component temperatures are maintained within safe limits, but turbine efficiency is reduced due to loss of compressed air
Solution Approach 1:
The system uses the temperature differential between the compressed cooling air and the turbine inlet air to automatically drive the cooling air flow through the variable geometry nozzle. The thermal energy of the hot compressed air itself provides the driving force for the cooling air flow, eliminating the need for additional mechanical work or external power sources. This self-service mechanism reduces the parasitic loss associated with mechanical drive systems.
Solution Approach 2:
The patent replaces traditional mechanical flow control mechanisms (such as adjustable valves or variable pitch nozzles requiring mechanical actuation) with a thermally-driven flow control system. The variable geometry nozzle is actuated by thermal expansion or contraction of a responsive material, or by pressure differential driven by the temperature difference between cooling air and inlet air. This substitution eliminates mechanical complexity and reduces energy losses associated with mechanical drive systems.
3Ease of manufacture
If fixed geometry cooling nozzles are used, then manufacturing is simple, but the system cannot adapt to part load operations
Solution Approach 1:
The patent transitions from a static, fixed-geometry nozzle to a dynamic nozzle that can change its configuration during operation. The variable geometry nozzle incorporates movable components or shape-memory materials that allow it to adapt its opening area in response to operating conditions. This dynamic capability enables the same nozzle structure to serve both full load and part load operations effectively, eliminating the need for multiple fixed nozzles or complex manual adjustment mechanisms.
Solution Approach 2:
The nozzle geometry parameters are made variable rather than fixed. The opening area, angle, or shape of the nozzle can change as a function of operating parameters such as power output, temperature differential, or pressure ratio. This parameter change capability allows the nozzle to be optimized for different operating regimes without requiring separate nozzles for each condition, maintaining manufacturing simplicity while achieving adaptability.
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
Improves turbine efficiency by precisely controlling cooling gas flow during part-load and off-design conditions, reducing the need for excessive compressor bleed and maintaining component temperatures, thereby enhancing operational efficiency and extending component life.
Implementation Method 1
the adjustable gas flow valve adjusts gas flow through the cooling gas pathway based on a physical parameter of compressed gas exiting a compressor of the turbine
Data Source
AI summary
A cooling gas flow control device for a turbine rotor that is internally located between the compressor and the turbine section of a turbine is disclosed. The cooling gas flow control device has a shape memory material that is used to actively adjust the cooling gas flow to internal parts of the turbine section between, including the buckets.


