Calculation of Two-Dimensional Potential Cascade Flow Using Finite Area Methods

Caspar, J. R.; Hobbs, D. E.; Davis, Roger L.

doi:10.2514/3.50738

Cited by 38 publications

(27 citation statements)

References 6 publications

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“…The predicted blade surface Mach number distribution for this mesh is shown in figure 3. Also shown is a prediction obtained from the steady velocity potential model, CASPOF, developed by Caspar, Hobbs, & Davis (1980). It should be noted that CASPOF also uses both a global H-mesh and a local C-mesh; however, the two meshes do not overlap, and the governing equations are not solved simultaneously on both meshes as it is in the present analysis.…”

Section: Naca 0006mentioning

confidence: 99%

Development of a Steady Potential Solver for Use with Linearized Unsteady Aerodynamic Analyses

Hoyniak

Verdon²

1993

Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers

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A full potential steady flow solver (SFLOW) developed explicitly for use with an inviscid unsteady aerodynamic analysis (LINFLO) is described herein. The steady solver uses the nonconservative form of the nonlinear potential flow equations together with an implicit, least-squares, finite-difference approximation to solve for the steady flow field. The difference equations were developed on a composite mesh which consists of a C-grid embedded in a rectilinear (H-grid) cascade mesh. The composite mesh is capable of resolving blade-to-blade and far-field phenomena on the H-grid, while accurately resolving local phenomena on the C-grid. The resulting system of algebraic equations is arranged in matrix form using a sparse matrix package and solved by Newton's method.Steady and unsteady results are presented for two cascade configurations: a high-speed compressor and a turbine with high exit Mach number.

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Section: Naca 0006mentioning

confidence: 99%

Development of a Steady Potential Solver for Use with Linearized Unsteady Aerodynamic Analyses

Hoyniak

Verdon²

1993

Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers

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“…Simulation values are in agreement except for a small region on the pressure side where the peak amplitude is shifted to the left of the experimental one. Comparison is also made with the potential flow calculation presented by Caspar et al [13]. Overall, the match between the simulation and experimentation is good in both rotor and stator cases.…”

Section: Validationmentioning

confidence: 81%

Effect of Axial Spacing between the Components on the Performance of a Counter Rotating Turbine

Subbarao¹,

Govardhan²

2013

International Journal of Fluid Machinery and Systems

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Counter Rotating Turbine (CRT) is an axial turbine with a nozzle followed by a rotor and another rotor that rotates in the opposite direction of the first one. Axial spacing between blade rows plays major role in its performance. Present work involves computationally studying the performance and flow field of CRT with axial spacing of 10, 30 and 70% for different mass flow rates. The turbine components are modeled for all the three spacing. Velocity, pressure, entropy and Mach number distributions across turbine stage are analyzed. Effect of spacing on losses and performance in case of stage, Rotor1 and Rotor2 are elaborated. Results confirm that an optimum axial spacing between turbine components can be obtained for the improved performance of CRT.

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“…9 ( Fig. 13.2) suggests the following expression for the temperature (and density) dependence of absolute viscosity: 0.684(y-l) (7) These expressions can be combined to produce the following: r-(7-7) (0.684) r \V\ (9) All information related to the nature of the particle is contained in the two bracketed dimensionless ratios in Eqs. (8 and 9).…”

Section: Discussionmentioning

confidence: 99%

“…For the present analysis these results were determined by applying the analysis of Caspar et al 9 This is a two-dimensional compressible potential flow analysis which, in addition to a preliminary analysis over the entire domain, permits one to perform a fine-scale detailed reanalysis around important regions such as the airfoil leading edge. This was important to the present work, particularly for cases where the particles followed the fluid streamlines closely.…”

Section: Discussionmentioning

confidence: 99%

Particle trajectories in turbine cascades

1979

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An analytical investigation into the nature of particle trajectories in cascades of airfoils has been carried out in order to predict the location, velocity, and angle of particle impact on the airfoils of turbines. As a result of this analysis it has been shown that for any given inviscid flow, particle trajectories are uniquely determined by the specification of only two dimensionless parameters, the most important of which is the Stokes number. In addition, computed results have indicated that particle trajectories are virtually invariant with cascade Mach number. Finally, a comparison of analytically and experimentally determined trajectories for the flow around the circular leading edge of a blunt body has shown excellent agreement over a wide range of Stokes number. Nomenclature A c = particle frontal area b x -cascade airfoil axial chord C D = particle drag coefficient D = blunt-body leading edge diameter D p = particle diameter M = Mach number Re b = airfoil inlet Reynolds number = -p f VD Re = particle Reynolds number = ----M 5 = airfoil surface arc length p U,D 2 St = Stokes number = p p U= fluid velocity vector V = particle velocity vector relative to fluid v = particle volume X -particle position vector X = particle velocity vector X = particle acceleration vector ft = gas flow angle (from tangential) 7 = specific heat ratio = C p /C v p = density /A = absolute viscosity r = cascade pitch Subscripts f = fluid p = particle / = cascade inlet conditions 2 = cascade exit conditions Superscripts (' ) = derivatives with respect to time ("* ) = vector ( ~ ) =nondimensional

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Calculation of Two-Dimensional Potential Cascade Flow Using Finite Area Methods

Cited by 38 publications

References 6 publications

Development of a Steady Potential Solver for Use with Linearized Unsteady Aerodynamic Analyses

Development of a Steady Potential Solver for Use with Linearized Unsteady Aerodynamic Analyses

Effect of Axial Spacing between the Components on the Performance of a Counter Rotating Turbine

Particle trajectories in turbine cascades

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