Numerical analysis of the impact of permeability on trailing-edge noise

2018 ◽  
Vol 421 ◽  
pp. 348-376 ◽  
Author(s):  
Seong Ryong Koh ◽  
Matthias Meinke ◽  
Wolfgang Schröder
Keyword(s):  
Numerical Analysis ◽  
Trailing Edge ◽  
Trailing Edge Noise ◽  
The Impact

Numerical analysis of the impact of variable porosity on trailing-edge noise

2018 ◽  
Vol 167 ◽  
pp. 66-81 ◽  
Author(s):  
Seong Ryong Koh ◽  
Beckett Zhou ◽  
Matthias Meinke ◽  
Nicolas Gauger ◽  
Wolfgang Schröder
Keyword(s):  
Numerical Analysis ◽  
Trailing Edge ◽  
Trailing Edge Noise ◽  
Variable Porosity ◽  
The Impact

scholarly journals Numerical Analysis of Metal-Foam Application for Trailing Edge Noise Reduction

2019 ◽  
Author(s):  
Christopher Teruna ◽  
Farhan A. Manegar ◽  
Francesco Avallone ◽  
Damiano Casalino ◽  
Daniele Ragni ◽  
...  
Keyword(s):  
Numerical Analysis ◽  
Noise Reduction ◽  
Metal Foam ◽  
Trailing Edge ◽  
Trailing Edge Noise

Numerical Analysis of Airfoil Trailing-Edge Noise for Straight and Serrated Edges at Incidence

AIAA Journal ◽  
2021 ◽  
pp. 1-20
Author(s):  
Gianluca Romani ◽  
Damiano Casalino ◽  
Wouter van der Velden
Keyword(s):  
Numerical Analysis ◽  
Trailing Edge ◽  
Trailing Edge Noise

Computation of trailing-edge noise due to turbulent flow over an airfoil

AIAA Journal ◽  
2002 ◽  
Vol 40 ◽  
pp. 2206-2216 ◽  
Author(s):  
A. Oberai ◽  
F. Roknaldin ◽  
T. J. R. Hughes
Keyword(s):  
Turbulent Flow ◽  
Trailing Edge ◽  
Trailing Edge Noise

Noise source location and scaling of subsonic upper-surface blowing

2020 ◽  
Vol 19 (3-5) ◽  
pp. 191-206
Author(s):  
Trae L Jennette ◽  
Krish K Ahuja
Keyword(s):  
Strouhal Number ◽  
Noise Source ◽  
Low Frequency ◽  
Directivity Pattern ◽  
Source Location ◽  
Dipole Source ◽  
Frequency Noise ◽  
Noise Sources ◽  
Trailing Edge ◽  
Trailing Edge Noise

This paper deals with the topic of upper surface blowing noise. Using a model-scale rectangular nozzle of an aspect ratio of 10 and a sharp trailing edge, detailed noise contours were acquired with and without a subsonic jet blowing over a flat surface to determine the noise source location as a function of frequency. Additionally, velocity scaling of the upper surface blowing noise was carried out. It was found that the upper surface blowing increases the noise significantly. This is a result of both the trailing edge noise and turbulence downstream of the trailing edge, referred to as wake noise in the paper. It was found that low-frequency noise with a peak Strouhal number of 0.02 originates from the trailing edge whereas the high-frequency noise with the peak in the vicinity of Strouhal number of 0.2 originates near the nozzle exit. Low frequency (low Strouhal number) follows a velocity scaling corresponding to a dipole source where as the high Strouhal numbers as quadrupole sources. The culmination of these two effects is a cardioid-shaped directivity pattern. On the shielded side, the most dominant noise sources were at the trailing edge and in the near wake. The trailing edge mounting geometry also created anomalous acoustic diffraction indicating that not only is the geometry of the edge itself important, but also all geometry near the trailing edge.

Impact of Different Film-Cooling Modes at Trailing Edge on the Aerodynamic Performance of Heavy Duty Gas Turbine Cascade

2011 ◽  
Vol 84-85 ◽  
pp. 259-263
Author(s):  
Xun Liu ◽  
Song Tao Wang ◽  
Xun Zhou ◽  
Guo Tai Feng
Keyword(s):  
Gas Turbine ◽  
Film Cooling ◽  
Large Mass ◽  
Turbine Cascade ◽  
Heavy Duty ◽  
Trailing Edge ◽  
Central Difference ◽  
Adiabatic Effectiveness ◽  
Heavy Duty Gas Turbine ◽  
The Impact

In this paper, the trailing edge film cooling flow field of a heavy duty gas turbine cascade has been studied by central difference scheme and multi-block grid technique. The research is based on the three-dimensional N-S equation solver. By way of analysis of the temperature field, the distribution of profile pressure, and the distribution of film-cooling adiabatic effectiveness in the region of trailing edge with different cool air injection mass and different angles, it is found that the impact on the film-cooling adiabatic effectiveness is slightly by changing the injection mass. The distribution of profile pressure dropped intensely at the pressure side near the injection holes line with the large mass cooling air. The cooling effect is good in the region of trailing edge while the injection air is along the direction of stream.

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