Flutter analysis of propfans using a three-dimensional Euler solver

1996 ◽  
Vol 12 (2) ◽  
pp. 267-273 ◽  
Author(s):  
R. Srivastava ◽  
T. S. R. Reddy ◽  
O. Mehmed
Keyword(s):  
Three Dimensional ◽  
Flutter Analysis ◽  
Euler Solver

A Three-Dimensional Viscous Transonic Inverse Design Method

2000 ◽  
Author(s):  
W. T. Tiow ◽  
M. Zangeneh
Keyword(s):  
Design Method ◽  
Flow Analysis ◽  
Three Dimensional ◽  
Viscous Effects ◽  
Flow Equations ◽  
Flow Solution ◽  
Turbomachinery Blades ◽  
A Cell ◽  
Inverse Design Method ◽  
Euler Solver

The development and application of a three-dimensional inverse methodology is presented for the design of turbomachinery blades. The method is based on the mass-averaged swirl, rV~θ distribution and computes the necessary blade changes directly from the discrepancies between the target and initial distributions. The flow solution and blade modification converge simultaneously giving the final blade geometry and the corresponding steady state flow solution. The flow analysis is performed using a cell-vertex finite volume time-marching algorithm employing the multistage Runge-Kutta integrator in conjunction with accelerating techniques (local time stepping and grid sequencing). To account for viscous effects, dissipative forces are included in the Euler solver using the log-law and mixing length models. The design method can be used with any existing solver solving the same flow equations without any modifications to the blade surface wall boundary condition. Validation of the method has been carried out using a transonic annular turbine nozzle and NASA rotor 67. Finally, the method is demonstrated on the re-design of the blades.

An Accurate and Efficient Euler Solver for Three-Dimensional Turbomachinery Flows

1986 ◽  
Author(s):  
C. F. Shieh ◽  
R. A. Delaney
Keyword(s):  
Numerical Solution ◽  
Euler Equations ◽  
Numerical Scheme ◽  
Three Dimensional ◽  
Curvilinear Coordinates ◽  
Analysis Method ◽  
Surfaces Of Revolution ◽  
Conservative Form ◽  
Turbine Cascades ◽  
Euler Solver

Accurate and efficient Euler equation numerical solution techniques are presented for analysis of three-dimensional turbomachinery flows. These techniques include an efficient explicit hopscotch numerical scheme for solution of the 3-D time-dependent Euler equations and an O-type body-conforming grid system. The hopscotch scheme is applied to the conservative form of the Euler equations written in general curvilinear coordinates. The grid is constructed by stacking from hub to shroud 2-D O-type grids on equally spaced surfaces of revolution. Numerical solution results for two turbine cascades are presented and compared with experimental data to demonstrate the accuracy of the analysis method.

scholarly journals Three dimensional flutter analysis and wind-tunnel experiments of slender webs in cross flow

2017 ◽  
Vol 83 (852) ◽  
pp. 17-00025-17-00025 ◽  
Author(s):  
Keiichi HIROAKI ◽  
Nobuhito KAWAI ◽  
Masahiro WATANABE
Keyword(s):  
Wind Tunnel ◽  
Three Dimensional ◽  
Cross Flow ◽  
Wind Tunnel Experiments ◽  
Flutter Analysis

Three-Dimensional Viscous Flutter Analysis of Standard Configuration 10

2007 ◽  
Author(s):  
Paul J. Petrie-Repar ◽  
Andrew McGhee ◽  
Peter A. Jacobs
Keyword(s):  
Unsteady Flow ◽  
Three Dimensional ◽  
Design Flow ◽  
Suction Surface ◽  
Corner Separation ◽  
Aerodynamic Damping ◽  
Flutter Analysis ◽  
Standard Configuration ◽  
Phase Angles ◽  
2D And 3D

The results of a three-dimensional (3D) viscous flutter analysis for a compressor stage, Standard Configuration 10, are presented. The unsteady flow simulations were performed by a 3D linearized Navier-Stokes flow solver using the Spalart and Allmaras turbulence model. Significant flow blockage due to corner separation at the hub on the suction surface was predicted by the steady-state 3D viscous simulation at a design condition. Corner separation was not predicted by 3D inviscid or two-dimensional (2D) viscous simulations. The corner separation was found to have a destabilizing effect and changed the nature of the unsteady flow. In fact, the 3D viscous simulations predicted negative aerodynamic damping for almost half of the inter-blade phase angles, while the 2D and 3D inviscid simulations predicted stable positive aerodynamic damping for all inter-blade phase angles. An off-design flow condition was also examined and significant differences between the 2D and 3D viscous simulations were found.

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