Development of an efficient analysis for high Reynolds number inviscid/viscid interactions in cascades

Barnett, Mark A.; Verdon, Joseph M.; Ayer, Timothy C.

doi:10.2514/6.1992-3073

Cited by 2 publications

(4 citation statements)

References 5 publications

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“…16 In Ref. 16, the steady pressure, skin friction, and displacement thickness distributions predicted by the two analyses showed very good agreement for both test cases.…”

Section: Numerical Resultsmentioning

confidence: 63%

“…16 In Ref. 16, the steady pressure, skin friction, and displacement thickness distributions predicted by the two analyses showed very good agreement for both test cases. In an effort to compare the unsteady viscous flowfields predicted by the FCBR and LCBR methods in the current investigation, the unsteady displacement thickness and skin friction coefficient distributions were recorded and interrogated.…”

Section: Numerical Resultsmentioning

confidence: 63%

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Unsteady multistage analysis using a loosely coupled blade row approach

Dorney

Davis²,

Sharma

1996

Journal of Propulsion and Power

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The flow through gas-turbine compressors and turbines is dominated by unsteady and viscous phenomena. Accurately predicting the behavior of these complex multistage flows with unsteady rotor-stator interacting Navier-Stokes analyses can require enormous computer resources. In this investigation, an alternative method for calculating the unsteadiness associated with multiple-stage turbomachinery flows is presented. The method, called the loosely coupled blade row (LCBR) technique, utilizes single-blade row simulations coupled with the appropriate unsteady boundary conditions to predict the aerodynamic interaction effects of adjacent blade rows. The LCBR approach provides an efficient alternative to fully coupled interaction analyses while maintaining comparable accuracy. Nomenclature a = speed of sound P = static pressure U = rotor velocity u, v -x, y components of velocity a. = absolute reference frame flow angle /3 = relative reference frame flow angle 17 = efficiency p = density Subscripts t = stagnation quantity, time derivative x, y = first derivative with respect to jc, v 1 = inlet quantity 2 = exit quantity Superscripts = relative frame quantity; perturbation quantity "~ = average or mean value

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“…16 In Ref. 16, the steady pressure, skin friction, and displacement thickness distributions predicted by the two analyses showed very good agreement for both test cases.…”

Section: Numerical Resultsmentioning

confidence: 63%

Section: Numerical Resultsmentioning

confidence: 63%

Unsteady multistage analysis using a loosely coupled blade row approach

Dorney

Davis²,

Sharma

1996

Journal of Propulsion and Power

View full text Add to dashboard Cite

show abstract

“…Consider the approximate factorization scheme of Beam and Warming (1977), which can be represented in semi-discretized form using only one Newton iteration as…”

Section: Numerical Integration Proceduresmentioning

confidence: 99%

“…In the viscous NGUST simulation, boundary layer blockage reduces the blade pressure loading, especially in the trailing edge region. It should be noted that the viscous NGUST results have been compared recently with the results of an inviscid/viscid interaction (IVI) analysis (Barnett et al, 1992) for both the EGV cascade and a high speed compressor cascade. The steady pressure, skin friction, and displacement thickness distributions predicted by the Navier-Stokes and IVI analyses showed very good agreement for the two test cases.…”

Section: Compressor Exit Guide Vane (Egv) Simulationsmentioning

confidence: 99%

Numerical Simulations of Unsteady Cascade Flows

Dorney¹,

Verdon²

1993

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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A time-accurate Navier-Stokes analysis is needed for understanding the relative importance of nonlinear and viscous effects on the unsteady flows associated with turbomachinery blade vibration and blade-row noise generation. For this purpose an existing multi-blade-row Navier-Stokes analysis has been modified and applied to predict unsteady flows excited by entropic, vortical, and acoustic disturbances through isolated, two-dimensional blade rows. In particular, time-accurate, nonreflecting inflow and outflow conditions have been implemented to allow specification of vortical, entropic, and acoustic excitations at the inlet, and acoustic excitations at the exit, of a cascade. To evaluate the nonlinear analysis, inviscid and viscous numerical simulations were performed for benchmark unsteady flows and the predicted results were compared with analytical and numerical results based on linearized inviscid flow theory. For small amplitude unsteady excitations, the unsteady pressure responses predicted with the nonlinear analysis show very good agreement, both in the field and along the blade surfaces, with linearized inviscid solutions. Based on a limited range of parametric studies, it was also found that the unsteady responses to inlet vortical and acoustic excitations are linear over a surprisingly wide range of excitation amplitudes, but acoustic excitations from downstream produce responses with significant nonlinear content.

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Development of an efficient analysis for high Reynolds number inviscid/viscid interactions in cascades

Cited by 2 publications

References 5 publications

Unsteady multistage analysis using a loosely coupled blade row approach

Unsteady multistage analysis using a loosely coupled blade row approach

Numerical Simulations of Unsteady Cascade Flows

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