Die Atomlagen-Thermosäule als Sensor für ein Oberflächenmessverfahren in der Strömungsmechanik

• Antragsteller: Dr.-Ing. Helmut Knauss
• Fachliche Zuordnung: Strömungsmechanik
• Förderung: Förderung von 2006 bis 2009
• Projektkennung: Deutsche Forschungsgemeinschaft (DFG) - Projektnummer 25637585

• Erstellungsjahr: 2008

Zusammenfassung der Projektergebnisse

Some of the key issues for the application of the Atomic Layer Thermopile (ALTP) heat flux gauge are addressed. First of all, the dynamic properties of the ALTP with respect to the optimization of its protective coating are studied by two different dynamic calibration procedures based on exposure to laser radiation and convection-dominated passing of a traveling shock wave. In addition, the results will be compared to theoretical estimations based on one-dimensional heat conduction. Furthermore, the capability of the ALTP to perform in partly or fully ionized plasmas was investigated in the test facility of an electric thruster. Finally, hypersonic boundary layer transition was studied in several facilities, showing the value of such a surface measurement technique with high temporal and spatial resolution provided by the ALTP. Experiments were carried out on fundamental models like flat plate and cone. The influence of acoustic noise on the transition scenario on the cone was studied in the Mach-6-Quiet tube of Purdue University. An array consisting of ALTP sensors was used for the first time to calculate growth rates of natural disturbances from quantitative spectral data. The results agreed well with rates measured with the same model in the Hypersonic Ludwieg Tube (HLB) / TU Braunschweig at least in the early stages of boundary layer (BL) transition. Hence, a general comparability of the transition research in both facilities could be shown. In addition, a staggered array of pressure and heat flux gauges was used to compare the growth rates from simultaneously measured pressure and heat flux spectra on a flat plate and cone. The results are in a good agreement with linear stability theory (LST) predictions.

Projektbezogene Publikationen (Auswahl)

• A novel sensor for fast heat flux measurements. AIAA Paper 2006-3637, 2006
  H. Knauss, T. Roediger, Bountin. D.A., B.V. Smorodsky, A.A. Maslov, U. Gaisbauer, E. Kraemer, J. Scrulijes, and F. Seiler
  
• A Novel Fast-Response Heat Flux Sensor for Fundamental Research in the Field of Future Space Transportation Systems, 58th International Astronautical Congress, 24 - 28 September 2007, Hyderabad, India
  Roediger, T.; Kraemer, E.
  
• A Novel Fast-Response Heat-Flux Sensor for Measuring Transition to Turbulence in the Boundary Layer behind a Moving Shock Wave, 26th International Symposium on Shock Waves, Göttingen, Jul. 2007
  Roediger, T.; Knauss, H. ; Srulijes, J.; Seiler, F.; Kraemer, E.
  
• Comparative Heat Transfer Studies at Hypersonic Conditions by means of three measurement techniques Part I: Measurement Techniques, Experimental Set-up and Preceding Investigations; Part II: Comparison of the Measurement Results and Identification with Theoretical Estimations, ICMAR 2007, Novosibirsk, Russia
  Zharkova,G.M.; Kovrizhina, V.N.; Petrov, A.P.; Smorodsky, B.V.; Knauss, H.; Roediger, T.; Wagner, S.; Kraemer, E.
  
• Pressure and Heat Flux Measurements on the Surface of a Low-aspect-ratio Circular Cylinder Mounted on a Ground Plate, 15th DGLR-STAB Symposium, Darmstadt, Nov. 2006. published in Notes on Numerical Fluid Mechanics and Multi Disciplinary Design (NNFM) in the series: New Results in Numerical and Experimental Fluid Mechanics, Vol. 96, Springer, 2007
  Roediger, T.; Knauss, H.; Gaisbauer, U.; Kraemer, E.
  
• The Atomic Layer Thermopile - A Fast Heat Flux Sensor for Measuring High Heat Loads in Short Duration Hypersonic Ground Testing Facilities, ICMAR 2007, Novosibirsk, Russia
  Roediger, T.; Knauss, H.; Wagner, S.; Kraemer, E.; Bountin, D.A.; Smorodsky, B.V.; Chirashenko, V.F.; Zvegintsev, V.I.; Maslov, A.A.
  
• Disturbancelevel and roughness-induced transition measurements in a conical boundary layer at Mach 6. AIAA Paper 08-3951, 2008
  D. Heitmann, T. Roediger, C. Kaehler, H. Knauss, R. Radespiel, and E. Kraemer
  
• Hypersonic instability waves measured using fast-response heat-flux gauges. AIAA Paper 2008-0638, 2008
  T. Roediger, H. Knauss, M. Estorf, S.P. Schneider, B.V. Smorodsky, and E. Kraemer
  
• Radespiel. Hypersonic instability waves measured on a flat plate at Mach 6. Proceedings ICMAR 2008, 2008
  T. Roediger, H. Knauss, B.V. Smorodsky, D.A. Bountin, A.A. Maslov, E. Kraemer, and R.
  
• Timeresolved heat transfer measurements on the tip wall of a ribbed channel using a novel heat flux sensor - Part I: Sensor and benchmarks. J.Turbomachinery, Vol. 130, p. 011018-1, 2008
  T. Roediger, S. Jenkins, H. Knauss, J. v. Wolfersdorf, U. Gaisbauer, and E. Kraemer
  
• Timeresolved heat transfer measurements on the tip wall of a ribbed channel using a novel heat flux sensor - Part II: heat transfer results. J.Turbomachinery, Vol. 130, 2008
  S. Jenkins, T. Roediger, H. Knauss, J. v. Wolfersdorf, U. Gaisbauer, and E. Kraemer