scholarly journals Solution of Plane Cascade Flow Using Improved Surface Singularity Methods

1982 ◽  
Vol 104 (3) ◽  
pp. 668-674 ◽  
Author(s):  
E. R. McFarland
Keyword(s):  
Solution Method ◽  
Inviscid Flow ◽  
External Flow ◽  
Surface Singularity ◽  
Solution Technique ◽  
Linear Cascade ◽  
Cascade Flow ◽  
Flow Through

A solution method has been developed for calculating compressible inviscid flow through a linear cascade of arbitrary blade shapes. The method uses advanced surface singularity formulations which were adapted from those found in current external flow analyses. The resulting solution technique provides a fast flexible calculation for flows through turbomachinery blade rows. The solution method and some examples of the method’s capabilities are presented.

scholarly journals Solution of Plane Cascade Flow Using Improved Surface Singularity Methods

1981 ◽  
Author(s):  
E. R. McFarland
Keyword(s):  
Solution Method ◽  
External Flow ◽  
Surface Singularity ◽  
Solution Technique ◽  
Linear Cascade ◽  
Cascade Flow ◽  
Flow Through

A solution method has been developed for calculating compressible in viscid flow through a linear cascade of arbitrary blade shapes. The method uses advanced surface singularity formulations which were adapted from those found in current external flow analyses. The resulting solution technique provides a fast flexible calculation for flows through turbomachinery blade rows. The solution method and some examples of the method’s capabilities are presented.

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.

Flow through axial-flow-turbomachinery blading

2018 ◽  
Author(s):  
Marcel Escudier
Keyword(s):  
Flow Velocity ◽  
Compressible Flow ◽  
Dimensional Analysis ◽  
Incompressible Flow ◽  
Compressible Fluid ◽  
Axial Flow ◽  
Linear Cascade ◽  
Dimensional Parameters ◽  
Flow Through

This chapter is concerned primarily with the flow of a compressible fluid through stationary and moving blading, for the most part using the analysis introduced in Chapter 11. The principles of dimensional analysis are applied to determine the appropriate non-dimensional parameters to characterise the performance of a turbomachine. The analysis of incompressible flow through a linear cascade of aerofoil-like blades is followed by the analysis of compressible flow. Velocity triangles for flow relative to blades, and Euler’s turbomachinery equation, are introduced to analyse flow through a rotor. The concepts introduced are applied to the analysis of an axial-turbomachine stage comprising a stator and a rotor, which applies to either a compressor or a turbine.

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.

scholarly journals Limiting Vibroisolation Control of an Oscillating String on a Moving Base

1995 ◽  
Vol 2 (2) ◽  
pp. 163-171 ◽  
Author(s):  
Dmitry V. Balandin
Keyword(s):  
Solution Method ◽  
Solution Technique ◽  
Quadratic Functional ◽  
Numerical Example ◽  
Guaranteed Quality ◽  
Moving Base ◽  
Elastic Object

The vibroisolating capability of an elastic object that is assumed to be protected against a class of excitations is studied. It is proposed that this capability be estimated by a quadratic functional. The solution method gives an estimate of the optimal isolation with a criterion of minimum guaranteed quality. A numerical example of the solution technique is presented.

scholarly journals Numerical Simulation of Cascade Flow: Vortex Element Method for Inviscid Flow Analysis and Axial Turbine Blade Design

2021 ◽  
Vol 85 (2) ◽  
pp. 14-23
Author(s):  
Nono Suprayetno ◽  
Priyono Sutikno ◽  
Nathanael P. Tandian ◽  
Firman Hartono
Keyword(s):  
Best Practice ◽  
Lift Coefficient ◽  
Flow Analysis ◽  
Three Dimensional ◽  
Inviscid Flow ◽  
Turbine Rotor ◽  
Design Stage ◽  
Outer Diameter ◽  
Axial Turbine ◽  
Cascade Flow

This study aims to design an axial turbine rotor blade and predict the turbine performance at preliminary design stage. Quasi three dimensional method was applied to design including blade to blade flow analysis. The blade profile uses a NACA 0015 airfoil by varying the profile thickness from hub to tip. The profile is divided into eleven segments which has different parameters. The profile was analysed using blade to blade flow/cascade flow analysis called vortex panel method to obtain lift coefficient. The analysis of cascade flow was performed in potential flow and prediction of turbine perfomance is carried out involving common best practice to give drag effect on the blade. The design of the turbine was applied on three different rotors, which also have a different discharge, head, and design rotation. The outer diameter of turbine 1 is 0.65 m, while turbine 2 and turbine 3 have an outer diameter of 0,60 m. The calculation result show that the efficiency of turbines 1, 2, and 3 were 88,32%, 89,67%, and 89,04%, respectively.

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

Dynamic Forces From Single Gland Labyrinth Seals: Part I—Ideal and Viscous Decomposition

1994 ◽  
Vol 116 (4) ◽  
pp. 686-693 ◽  
Author(s):  
K. T. Millsaps ◽  
M. Martinez-Sanchez
Keyword(s):  
Inviscid Flow ◽  
Labyrinth Seal ◽  
Lumped Parameter Model ◽  
Solution Technique ◽  
Linear Perturbation ◽  
Labyrinth Seals ◽  
Frequency Dependent ◽  
Lumped Parameter ◽  
Reduced Parameters ◽  
Force Decomposition

A theoretical and experimental investigation on the aerodynamic forces generated by a single gland labyrinth seal executing a spinning/whirling motion has been conducted. A lumped parameter model, which includes the kinetic energy carryover effect, is presented along with a linear perturbation solution technique. The resulting system is nondimensionalized and the physical significance of the reduced parameters is discussed. Closed-form algebraic formulas are given for some simple limiting cases. It is shown that the total cross force predicted by this model can be represented as the sum of an ideal component due to an inviscid flow with entry swirl and a viscous part due to the change in swirl created by friction inside the gland. The frequency-dependent ideal part is solely responsible for the rotordynamic direct damping. The facility designed and built to measure these frequency dependent forces is described. Experimental data confirm the validity and usefulness of this ideal/viscous decomposition. A method for calculating the damping coefficients based on the force decomposition using the static measurements only is presented.

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
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