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Einfluss einer oszillierenden Luftströmung auf den Zerstäubungsprozess bei der Airblast-Zerstäubung

Project: MAGISTER

Machine learning for Advanced Gas turbine Injection SysTems to Enhance combustoR performance.

Air transportation is expected to grow persistently over the next decades. Clean combustion technology for aircraft engines is a key enabler to reduce the impact of this growth on ecosystems and humans’ health. The vision for European aviation is shaped by the Advisory Council for Aviation Research and Innovation in Europe in the Flight Path 2050 goals, which define stringent regulations on pollutant emissions.

To meet these goals, the major engine manufacturers develop lean premixed combustors operated at very high pressure. This development introduces a large risk for reduced reliability and lifetime of engines: pressure oscillations in the combustor called thermoacoustics.

Aviation industry encounters currently the fourth industrial revolution: cyber-physical systems analyze and monitor technical systems and take automated decisions. This industrial revolution is known as “Industry 4.0” in Germany and “Industrial Internet” in the USA. An essential enabler of the fourth industrial revolution is Machine Learning.

The ITN MAGISTER will utilize Machine Learning to predict and understand thermoacoustics in aircraft engine combustors, and lead combustion research a revolutionary new approach in this area.

 

Research

The target of this experimental research is to produce a database of droplet characteristics during prefilming airblast atomization process, when the airflow is subject to a forcing.

The main airflow is split in two different channels. About 30% of the total air mass flow can flow through the siren and is excited at determined frequencies, before it is mixed with the rest of the mass flow, which is bypassed through an air plenum. The product airflow of the mixing flows through a 1.5 m long resonance tube before it reaches the airblast prefilmer nozzle at atmospheric pressure. 

The designed and manufactured airblast atomizer consists of a stainless steel standardized symmetrical airfoil profile (NACA-0010), with a chord length of 73 mm and a trailing edge thickness, i.e. an atomization lip thickness of approximately 200 μm. The cavity on the inside hosts the liquid, which then emerges on the surface of the prefilmer through 40 equidistant drilled holes generating a uniform liquid film. The air is flowing on both sides of the prefilming atomizer while the liquid film covers only the one side, replicating in this way the prefilming surface of a conventional airblast atomizer.

The airflow velocity and its fluctuation over time due to the siren was measured by means of hot wire Constant Temperature Anemometry (CTA). The data rate of this device can be as high as 100 kHz, which is one of the main reasons that it was preferred for measuring an airflow fluctuating at relatively high frequencies.
The characterization of the spray, i.e. the droplet velocity and diameter, was accomplished via Phase Doppler Anemometry (PDA). The meeting point of the laser beams that defines the measurement volume was set at the middle of the spray, downstream of the atomization edge.

 

Siren and bypass plenum configuration.

 

 

Model of prefilming airblast atomizer.

 

Fast Fourier Transform of the air velocity signalfor 21 different rotational speeds of the siren.

 

Phase averaging of velocity signal at 860 RPM for one rotation of the siren.

 

SMD fluctuation in one siren rotation at 860 RPM in comparison with three unforced flow cases.

 

Size-class separation for the phase averaged mean droplet velocity at 860 RPM.

 

Averaging of spray volume flow rate and air-to-liquid ratio (ALR) for one rotation of the siren rotor at 860 RPM.


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