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Title: Euler solutions for transonic oscillating cascade flows using dynamic triangular meshes

Abstract

The modified total-variation-diminishing scheme and an improved dynamic triangular mesh algorithm are presented to investigate the transonic oscillating cascade flows. In a Cartesian coordinate system, the unsteady Euler equations are solved. To validate the accuracy of the present approach, transonic flow around a single NACA 0012 airfoil pitching harmonically about the quarter chord is computed first. The calculated instantaneous pressure coefficient distribution during a cycle of motion compare well with the related numerical and experimental data. To evaluate further the present approach involving nonzero interblade phase angle, the calculations of transonic flow around an oscillating cascade of two unstaggered NACA 0006 blades with interblade phase angle equal to 180 deg are performed. From the instantaneous pressure coefficient distributions and time history of lift coefficient, the present approach, where a simple spatial treatment is utilized on the periodic boundaries, gives satisfactory results. By using this solution procedure, transonic flows around an oscillating cascade of four biconvex blades with different oscillation amplitudes, reduced frequencies, and interblade phase angles are investigated. From the distributions of magnitude and phase angle of the dynamic pressure difference coefficient, the present numerical results show better agreement with the experimental data than those from the linearized theory inmore » most of the cases. For every quarter of one cycle, the pressure contours repeat and proceed one pitch distance in the upward or downward direction for interblade phase angle equal to {minus}90 deg or 90 deg, respectively. The unsteady pressure wave and shock behaviors are observed. From the lift coefficient distributions, it is further confirmed that the oscillation amplitude, interblade phase angle, and reduced frequency all have significant effects on the transonic oscillating cascade flows.« less

Authors:
;  [1]
  1. National Cheng Kung Univ., Tainan (Taiwan, Province of China). Institute of Aeronautics and Astronautics
Publication Date:
Sponsoring Org.:
USDOE
OSTI Identifier:
103656
Report Number(s):
CONF-930502-
Journal ID: JOTUEI; ISSN 0889-504X; TRN: IM9541%%95
Resource Type:
Journal Article
Journal Name:
Journal of Turbomachinery
Additional Journal Information:
Journal Volume: 117; Journal Issue: 3; Conference: 38. ASME international gas turbine and aeroengine congress and exhibition, Cincinnati, OH (United States), 24-27 May 1993; Other Information: PBD: Jul 1995
Country of Publication:
United States
Language:
English
Subject:
20 FOSSIL-FUELED POWER PLANTS; TRANSONIC FLOW; CALCULATION METHODS; TURBOMACHINERY; MECHANICAL VIBRATIONS; UNSTEADY FLOW; OSCILLATIONS

Citation Formats

Hwang, C J, and Yang, S Y. Euler solutions for transonic oscillating cascade flows using dynamic triangular meshes. United States: N. p., 1995. Web. doi:10.1115/1.2835674.
Hwang, C J, & Yang, S Y. Euler solutions for transonic oscillating cascade flows using dynamic triangular meshes. United States. https://doi.org/10.1115/1.2835674
Hwang, C J, and Yang, S Y. 1995. "Euler solutions for transonic oscillating cascade flows using dynamic triangular meshes". United States. https://doi.org/10.1115/1.2835674.
@article{osti_103656,
title = {Euler solutions for transonic oscillating cascade flows using dynamic triangular meshes},
author = {Hwang, C J and Yang, S Y},
abstractNote = {The modified total-variation-diminishing scheme and an improved dynamic triangular mesh algorithm are presented to investigate the transonic oscillating cascade flows. In a Cartesian coordinate system, the unsteady Euler equations are solved. To validate the accuracy of the present approach, transonic flow around a single NACA 0012 airfoil pitching harmonically about the quarter chord is computed first. The calculated instantaneous pressure coefficient distribution during a cycle of motion compare well with the related numerical and experimental data. To evaluate further the present approach involving nonzero interblade phase angle, the calculations of transonic flow around an oscillating cascade of two unstaggered NACA 0006 blades with interblade phase angle equal to 180 deg are performed. From the instantaneous pressure coefficient distributions and time history of lift coefficient, the present approach, where a simple spatial treatment is utilized on the periodic boundaries, gives satisfactory results. By using this solution procedure, transonic flows around an oscillating cascade of four biconvex blades with different oscillation amplitudes, reduced frequencies, and interblade phase angles are investigated. From the distributions of magnitude and phase angle of the dynamic pressure difference coefficient, the present numerical results show better agreement with the experimental data than those from the linearized theory in most of the cases. For every quarter of one cycle, the pressure contours repeat and proceed one pitch distance in the upward or downward direction for interblade phase angle equal to {minus}90 deg or 90 deg, respectively. The unsteady pressure wave and shock behaviors are observed. From the lift coefficient distributions, it is further confirmed that the oscillation amplitude, interblade phase angle, and reduced frequency all have significant effects on the transonic oscillating cascade flows.},
doi = {10.1115/1.2835674},
url = {https://www.osti.gov/biblio/103656}, journal = {Journal of Turbomachinery},
number = 3,
volume = 117,
place = {United States},
year = {Sat Jul 01 00:00:00 EDT 1995},
month = {Sat Jul 01 00:00:00 EDT 1995}
}