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| Content Provider | The American Society of Mechanical Engineers (ASME) Digital Collection |
|---|---|
| Author | Giuliani, Fabrice Lang, Andreas Gradl, Klaus Johannes Siebenhofer, Peter Fritzer, Johannes |
| Copyright Year | 2011 |
| Abstract | A specific actuator able to modulate the air feed of a gas a burner at a given frequency and amplitude is presented. The Combustion Department at the Institute for Thermal Turbomachinery and Machine Dynamics at the Graz University of Technology has experience on the study of combustion instabilities in gas turbines using a flow excitor. The stability of an industrial burner is tested at elevated pressure and temperature conditions in the frame of the NEWAC project. For practical matters of operation among which the possibility to induce progressively a perturbation when the flame conditions are all set, the need was expressed to design, construct and validate a flexible actuator able to set an air flow modulation at a given frequency and at a desired amplitude level, with the possibility during operation to let these two factors vary in a given range independently from each other. This device should operate within the 0–1 kHz range and 0–20% amplitude range at steady-state, during transients, or follow a specific time sequence. It should be robust and sustain elevated pressures. The objective is to bring a perturbation in the flow to which the combustor will respond, or not. For elevated levels of pulsation, it can simulate the presence of vortex-driven combustion instabilities. It can also act as a real-time actuator able to respond in frequency and in phase to actively damp a “natural” combustion instability. Other issues are a better and quicker mixing due to the enhanced turbulence level, and pushing forward the blow out limits at lean conditions with controlled injection dynamics. The basic construction is the one of a siren, with an elevated pressure side where the air is throttled, and a low pressure outlet where the resulting sonic jet is sheared by a rotating wheel. A mechanism allows to let vary the surface of interaction between the wheel and the jet. Two electro-motors driven by Labview set both frequency and amplitude levels. This contribution describes the actuator’s principles, design, operation range and the results of the characterisation campaign. |
| Sponsorship | International Gas Turbine Institute |
| Starting Page | 9 |
| Ending Page | 17 |
| Page Count | 9 |
| File Format | |
| ISBN | 9780791854631 |
| DOI | 10.1115/GT2011-45071 |
| Volume Number | Volume 3: Controls, Diagnostics and Instrumentation; Education; Electric Power; Microturbines and Small Turbomachinery; Solar Brayton and Rankine Cycle |
| Conference Proceedings | ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition |
| Language | English |
| Publisher Date | 2011-06-06 |
| Publisher Place | Vancouver, British Columbia, Canada |
| Access Restriction | Subscribed |
| Subject Keyword | Actuators Construction Temperature Turbulence Stability Wheels Motors Turbomachinery Combustion Pressure Flow (dynamics) Steady state Transients (dynamics) Design Air flow Flames Gas turbines Dynamics (mechanics) Vortices Combustion chambers Machine dynamics |
| Content Type | Text |
| Resource Type | Article |
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