Independent Variable Vane Actuation for Gas Turbine Optimization
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Solution Overview
Problem
Traditional gas turbine engine variable vane actuation systems rely on linked multistage adjustment structures, where adjusting one stage of variable vanes simultaneously affects others, limiting independent optimization of vane angles and compromising engine efficiency and stability.
Innovation Solution
The implementation of independent electric actuators for each stage of variable vanes, allowing for separate control of sync-rings and vane angles based on sensor data, such as pressure and temperature measurements, enabling independent optimization of vane angles and reducing the need for multi-stage linkages.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If linked multistage adjustment structures are used to adjust variable vanes, then the structure can be simplified with fewer actuators, but the ability to independently optimize each stage's vane angle is lost
Solution Approach 1:
The patent divides the actuation system into separate actuators for each variable vane stage, allowing independent control of each stage's vane angles. This segmentation enables each stage to be optimized independently for different operating conditions, resolving the contradiction between structural simplicity and independent optimization capability.
2Adaptability or versatility
If separate actuators are used for each stage of variable vanes, then independent optimization of each stage is enabled, but the device complexity and number of actuators increase
Solution Approach 1:
The patent implements dynamic control capabilities where each actuator can independently adjust its stage's vane angles based on real-time sensor feedback and controller commands. This dynamic independence allows the system to adapt to varying operating conditions, achieving superior engine performance despite the increased number of actuators.
3Volume of moving object
If a shared torque box is used to actuate multiple stages simultaneously, then the actuation system is more compact, but the engine efficiency and stability are compromised due to inability to optimize each stage independently
Solution Approach 1:
The patent segments the actuation system into separate actuators for each variable vane stage, eliminating the shared torque box configuration. This segmentation enables independent optimization of each stage's vane angles, thereby improving engine efficiency and stability while accepting a larger overall actuation system volume.
4Quantity of substance
If linked multistage adjustment structures are used, then fewer sensors and actuators are needed, but the ability to respond to varying operating conditions is limited
Solution Approach 1:
The patent implements feedback control systems where sensors monitor operating conditions and provide data to controllers that independently adjust each stage's vane angles. This feedback mechanism enables the system to respond dynamically to varying operating conditions, achieving superior adaptability despite the increased number of sensors and actuators required.
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 allows for optimized and independent adjustment of vane angles, improving engine efficiency, stability, and reducing fuel consumption by accommodating varying operating conditions and eliminating constraints from prior art limitations.
Implementation Method 1
each variable vane stage may include its own respective actuator 80 and sync-ring 70. In a particular embodiment, each actuator 80 may be an electric actuator
Data Source
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AI summary
According to one aspect of the present disclosure, a gas turbine engine is disclosed that includes an engine section (60) comprising a plurality of stages (62A, B) of variable vanes (64), and also includes first and second synchronizing rings (sync-rings) (70A, 70B). Movement of the first sync-ring (70A) adjusts vane angles of a first one of the stages (62A) of variable vanes (64), and movement of the second sync-ring (70B) adjusts vane angles of a second one of the stages (62B) of variable vanes (64). At least one sensor (81A-C) is configured to measure a condition of the gas turbine engine. A controller (78) is configured to move the first sync-ring (70A) independently of the second sync-ring (70B) based on data from the at least one sensor (81A-C).