Noise originating from the unsteady heat-release during the combustion process in the combustor of a gas turbine is well known. However, an effect known as indirect combustion noise has received considerable interest only recently. Indirect combustion noise will be generated, when entropy or vorticity fluctuations will be subject to a strong velocity gradient like in nozzle guide vane of the high pressure turbine. First experimental proof of this phenomenon could be obtained some years ago in a dedicated small-scale laboratory experiment. Recent experiments performed in the Hot Acoustic Test rig (HAT) by the German Aerospace Center (DLR) aim at further understanding of this phenomenon by investigating the sound propagation through a nozzle and sound generation when cold air spots are injected into a hot mean flow. The nozzle Mach number was varied from subsonic to sonic conditions. First results based on propagation time analysis reveal noise generation at the location of the nozzle. Parameter studies of nozzle Mach number, temperature of the cold streaks, and the way the cold air is injected (radial/axial blowing) have been performed.
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ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
June 15–19, 2015
Montreal, Quebec, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5664-2
PROCEEDINGS PAPER
Noise Generation in Hot Nozzle Flow
Karsten Knobloch,
Karsten Knobloch
German Aerospace Center (DLR), Berlin, Germany
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Tiago Werner,
Tiago Werner
German Aerospace Center (DLR), Berlin, Germany
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Friedrich Bake
Friedrich Bake
German Aerospace Center (DLR), Berlin, Germany
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Karsten Knobloch
German Aerospace Center (DLR), Berlin, Germany
Tiago Werner
German Aerospace Center (DLR), Berlin, Germany
Friedrich Bake
German Aerospace Center (DLR), Berlin, Germany
Paper No:
GT2015-43702, V02BT41A012; 14 pages
Published Online:
August 12, 2015
Citation
Knobloch, K, Werner, T, & Bake, F. "Noise Generation in Hot Nozzle Flow." Proceedings of the ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 2B: Turbomachinery. Montreal, Quebec, Canada. June 15–19, 2015. V02BT41A012. ASME. https://doi.org/10.1115/GT2015-43702
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