Sensitivity analysis of unsteady inviscid flow through turbomachinery cascades

AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 1047-1056
Author(s):  
Razvan Florea ◽  
Kenneth C. Hall
Keyword(s):  
Sensitivity Analysis ◽  
Inviscid Flow ◽  
Flow Through ◽  
Turbomachinery Cascades

Sensitivity Analysis of Unsteady Inviscid Flow Through Turbomachinery Cascades

AIAA Journal ◽  
2001 ◽  
Vol 39 (6) ◽  
pp. 1047-1056 ◽  
Author(s):  
Razvan Florea ◽  
Kenneth C. Hall
Keyword(s):  
Sensitivity Analysis ◽  
Inviscid Flow ◽  
Flow Through ◽  
Turbomachinery Cascades

Mach Number Influence on Reduced-Order Models of Inviscid Potential Flows in Turbomachinery

2002 ◽  
Vol 124 (4) ◽  
pp. 977-987 ◽  
Author(s):  
Bogdan I. Epureanu ◽  
Earl H. Dowell ◽  
Kenneth C. Hall
Keyword(s):  
Mach Number ◽  
Steady Flow ◽  
Inviscid Flow ◽  
Reduced Order Models ◽  
Reduced Order ◽  
Spatial Gradients ◽  
Potential Flows ◽  
Proper Orthogonal Decomposition Technique ◽  
Flow Through ◽  
Phase Angles

An unsteady inviscid flow through a cascade of oscillating airfoils is investigated. An inviscid nonlinear subsonic and transonic model is used to compute the steady flow solution. Then a small amplitude motion of the airfoils about their steady flow configuration is considered. The unsteady flow is linearized about the nonlinear steady response based on the observation that in many practical cases the unsteadiness in the flow has a substantially smaller magnitude than the steady component. Several reduced-order modal models are constructed in the frequency domain using the proper orthogonal decomposition technique. The dependency of the required number of aerodynamic modes in a reduced-order model on the far-field upstream Mach number is investigated. It is shown that the transonic reduced-order models require a larger number of modes than the subsonic models for a similar geometry, range of reduced frequencies and interblade phase angles. The increased number of modes may be due to the increased Mach number per se, or the presence of the strong spatial gradients in the region of the shock. These two possible causes are investigated. Also, the geometry of the cascade is shown to influence strongly the shape of the aerodynamic modes, but only weakly the required dimension of the reduced-order models.

Inviscid Flow through a Sudden Contraction

1972 ◽  
Vol 11 (4) ◽  
pp. 590-593 ◽  
Author(s):  
J. Larry Duda ◽  
James S. Vrentas
Keyword(s):  
Inviscid Flow ◽  
Sudden Contraction ◽  
Flow Through

scholarly journals Solution of Turbine Blade Cascade Flow Using an Improved Panel Method

2015 ◽  
Vol 2015 ◽  
pp. 1-6 ◽  
Author(s):  
Zong-qi Lei ◽  
Guo-zhu Liang
Keyword(s):  
Turbine Blade ◽  
Inviscid Flow ◽  
Panel Method ◽  
Experiment Data ◽  
Blade Cascade ◽  
Comparison With Experiment ◽  
Cascade Flow ◽  
Mesh Free ◽  
Blade Row ◽  
Flow Through

An improved panel method has been developed to calculate compressible inviscid flow through a turbine blade row. The method is a combination of the panel method for infinite cascade, a deviation angle model, and a compressibility correction. The resulting solution provides a fast flexible mesh-free calculation for cascade flow. A VKI turbine blade cascade is used to evaluate the method, and the comparison with experiment data is presented.

Heat Flow Through Pelage of Calves A Sensitivity Analysis

1984 ◽  
Vol 27 (4) ◽  
pp. 1140-1143 ◽  
Author(s):  
K. G. Gebremedhin ◽  
W. P. Porter
Keyword(s):  
Sensitivity Analysis ◽  
Heat Flow ◽  
Flow Through

Inviscid Flow through Cascades in Oscillatory and Distorted Flow

AIAA Journal ◽  
1971 ◽  
Vol 9 (10) ◽  
pp. 2043-2050 ◽  
Author(s):  
B. SCHORR ◽  
K. C. REDDY
Keyword(s):  
Inviscid Flow ◽  
Flow Through

scholarly journals Computation of Transonic Flows in and About Turbine Cascades With Viscous Effects

1984 ◽  
Author(s):  
U. K. Singh
Keyword(s):  
Inviscid Flow ◽  
Viscous Effects ◽  
Trailing Edge ◽  
Pressure Surface ◽  
Integral Methods ◽  
Interaction Treatment ◽  
Time Marching ◽  
Flow Through ◽  
Turbine Cascades ◽  
Good Agreement

An inviscid-viscous interaction treatment has been developed to predict the flow through transonic axial turbine blade cascades. The treatment includes a trailing-edge base pressure model. This model is based on treating the area between the points of flow separation on the blade surfaces at the trailing-edge and the point of downstream confluence of the suction and pressure surface flows as a region of constant pressure. A time marching technique is used to calculate the inviscid flow and viscous flow is calculated by integral methods for laminar and turbulent boundary layers. Good agreement with experimental data has been obtained.

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