Rotor Support Plasma Actuation for Turbine Tip Leakage
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Solution Overview
Problem
Gas turbine engines face inefficiencies due to gas leaks from the clearance between rotor blades and the annular casing, leading to vortex formation and reduced energy efficiency.
Innovation Solution
A rotor support device utilizing dielectric barrier discharge (DBD) plasma actuators with multiple electrodes and a dielectric material to induce intermittent gas flows, reducing leak flows by controlling dielectric barrier discharge between the electrodes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If the clearance between rotor blades and annular casing is reduced, then gas leak flow is reduced, but the risk of blade-casing contact increases due to thermal expansion and manufacturing tolerances
Solution Approach 1:
A dielectric material is introduced as an intermediary between the rotor blade and the annular casing. This dielectric material enables the plasma actuator system to control gas flow without requiring direct mechanical contact or extremely tight clearances, thus reducing gas leaks while maintaining safe blade-casing spacing
Solution Approach 2:
The patent replaces mechanical flow control methods (such as mechanical seals or tight clearance design) with a plasma-based actuator system. The plasma actuator uses electromagnetic fields to generate body forces in the gas, controlling leak flow without mechanical contact between the rotor blade and casing
2Productivity
If plasma actuators are attached to the rotor blade, then gas flow control is improved, but the device complexity increases
Solution Approach 1:
The plasma actuator system merges multiple components (electrodes, dielectric material, power supply) into an integrated assembly that is mounted on the rotor blade. This combining of elements into a unified system reduces overall complexity compared to separate flow control mechanisms while achieving effective gas flow control
Solution Approach 2:
The plasma actuator controls gas flow by changing physical parameters such as voltage frequency and amplitude applied to the electrodes. By adjusting these electrical parameters, the system can dynamically control gas flow characteristics without mechanical adjustments or complex mechanical structures
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 solution effectively reduces gas leaks, improving energy efficiency in gas turbine engines by preventing vortex growth and optimizing gas flow patterns.
Implementation Method 1
induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes
Data Source
AI summary
A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor.