Aerospace Propulsion Laboratory

Department of Aeronautics and Astronautics, Kyushu University

Professor Nobuhiko YAMASAKI
Associate Professor Chihiro INOUE

For Japanese who wants to study in our graduate school

Please visit our 'open laboratory', which is held in early May every year.


Education and research on aerospace propulsion systems such as aircraft gas turbine engines, rocket engines, thrusters, and so on.


Graduate School

Undergraduate School

Recent Research Themes

Flutter Analysis based on Linear Unsteady Theories

Cascade flutters for subsonic to supersonic relative flows are analyzed. The governing Euler or Navier-Stokes equations are linearlized and unsteady equations are solved in the frequency domain, to shorten the time required for aero-engine design. Developping robust and fast code and its validations are main objectives of this study.
Acoustic Analysis based on Linear Unsteady Theories

Studies on the mathematical formulation and computer algorithms to predict the acoustic propagation in the frequency domain, based on the same idea with the above.
Multiphase Flow in Chemical Propulsion Systems

Rocket engines and satellite thrusters produce spray by atomization to enhance evaporation and mixing for efficient combustion. Detailed spray characteristics are elucidated using high-speed visualization, multi-phase CFD, and theoretical modeling. Performance of chemical propulsion systems, e.g. characteristic velocity, is able to be well predicted by developed model. The figure shows a high-speed visualization of impinging atomization model for satellite thrusters.
Multiphase Flow in Jet Engines and Fireworks

Air-blast atomizer for jet engines, in which liquid sheet breaks up due to high-speed air streams, is a crucial component both for performance and environment. The spray characteristics are clarified by high-speed visualization, laser diagnostics, and multiphase CFD. The picture shows a high-speed visualization of 2D liquid sheet.
Numerical Predictions of Fan Tone and Broadband Noises

On the subject of fan tone noise, the effects of lean and sweep of stator vanes are investigated by using the compressible unsteady RANS. With respect to the fan broadband noise, turbulent noise sources are studied by investigating the spatial distribution of the turbulent kinetic energy. The figure shows an instantaneous pressure field caused by rotor-stator interaction. These pressure fields are passed to duct-acoustics code (linear theory) to predict sound propagation/attenuation of spinning modes.
Active and Passive Controls for Fan Tone Noise

The tone noise is actively suppressed by sound generated by loudspeakers mounted on the fan duct, or passively suppressed by sound absorbing liners on the fan duct walls. Developping active control algorithms and/or efficient passive liners are main objectives of this research. The picture shows the fan model with a wake-generator upstream of the fan and 12 loudspeakers mounted on the duct wall.
Numerical Simulations on the Flow and Noise of an Automobile Turbocharger

The effects of mis-tuning due to manufacturing errors on the sound fields, the effects of upstream duct curvature on the performance, the effects of pulsating flow due to piston motion of the IC engine on the performance, the flowfield near the surge, and so on, are investigated by using a compressible unsteady RANS code. A LES code is also used to improve the prediction capability of the performance curves. The figure shows a pressure fields on the compressor rotor blades and streamlines of the flow in the volute. The color of the streamlines also indicates the pressure.
Rig Tests on the Flow of an Automobile Turbocharger

In automobile turbocharger, sudden decelerator operation sometimes causes flow instability called surge. A test rig is newly made to study this transient phenomena and to find effective ways to avoid the surge. The picture is a close view of the test rig. Compressed air with a 5kW electric heater is used to drive the turbine.
Experimental Investigation on Active Acoustic Liners

An acoustic liner of the Helmholtz resonator type has narrow frequency band of sound absorption. Introducing a bias flow to the aperture of resonator's perforated plate is known to improve the sound absorption in broad band frequency range. In this study, influence of the shape of apertures are experimentally investigated by using an acoustic tube. In the figure, the acoutic tube for two microphone method (ISO10534-2) is shown and a sub-figure illustrates vortex shedding from a aperture in the presence of a bias flow.
Numerical Investigation on Acoustic Liners

The mechanisms of sound absorption in an acoustic liner of perforated plate type are not well known when there exists a grazing flow or a bias flow. In this study, the effects of grazing flow and/or bias flow is investigated by using a large eddy simulation for computational aeroacoustics. The figure shows a vortex contour around a acoustic liner of the perforated plate type in the presence of a grazing flow.
Numerical Prediction of Jet Noises

The compressible NS equations are solved by the compact finite difference schemes for several kinds of nozzle shapes, to study the mechanisms of jet noise generation and to find effective ways of suppressing the jet noise. The farfield acoustics are estimated by the Ffowcs Williams-Hawkings method. In the figure, instantaneous flowfields are visualized as iso-surfaces of the second-invariant of velocity gradient tensor (gray scale) and dilatation field contours (multi-colors).
Jet Noise Suppressions Using Tab-Like Passive Control Devices

Noise spectrum and thrust are measured with various passive control devices, including tabs, chevrons, etc. The picture shows an experimental rig of a subsonic rectangular jet, with Mach number of 0.8. Three microphones are placed with the angles of 30, 60, and 90 degrees from the jet axis in the anechoic chamber.
Large Eddy Simulations of Turbulent Non-Premixed Jet Flames

Turbulent combustion fields are modeled by the laminar flamelet model. Flowfileds are solved by an incompressible LES code with a flamelet database. The figure shows instantaneous temperature field of a methane/air turbulent non-premixed flame (DLR-A flame).
Active Control of Combustion Instabilities

A model burner is used to artificially generate combustion oscillations and then the oscillations are suppressed by sound waves from a loudspeaker. The picture shows the methane-air premixed burner model, equipped with 4 quartz glasses for observation. A microphone is mounted above the quartz glass and is water-cooled.



Aerospace Propulsion Laboratory
Department of Aeronautics and Astronautics, Kyushu University
#805 West Zone Building 4, 744 Motooka, Nishi-ku, Fukuoka 819-0395, JAPAN

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