Simulation of Three-Dimensional Viscous Flow Within a Multistage Turbine

Adamczyk, John J.; Celestina, Mark L.; Beach, T. A.; Barnett, Mark A.

doi:10.1115/89-gt-152

Cited by 63 publications

(56 citation statements)

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“…This technique is used in a marching scheme starting at the most upstream component and traversing through the engine to the most downstream component to generate the flow through the engine. In some schemes multiple passes through the engine are made through the engine to improve accuracy [6,7].…”

Section: Introductionmentioning

confidence: 99%

A Lagrangian parcel based mixing plane method for calculating water based mixed phase particle flows in turbo-machinery

Bidwell

2015

Comp. Part. Mech.

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A method for calculating particle transport through turbo-machinery using the mixing plane analogy was developed and used to analyze the energy efficient engine (E 3 ). This method allows the prediction of temperature and phase change of water based particles along their path and the impingement efficiency and particle impact property data on various components in the engine. This methodology was incorporated into the LEWICE3D V3.5 software. The method was used to predict particle transport in the low pressure compressor of the E 3 . The E 3 was developed by NASA and GE in the early 1980s as a technology demonstrator and is representative of a modern high bypass turbofan engine. The E 3 flow field was calculated using the NASA Glenn ADPAC turbo-machinery flow solver. Computations were performed for a Mach 0.8 cruise condition at 11,887 m assuming a standard warm day for ice particle sizes of 5, 20 and 100 microns and a free stream particle concentration of 0.3 g/m 3 . The impingement efficiency results showed that as particle size increased average impingement efficiencies and scoop factors increased for the various components. The particle analysis also showed that the amount of mass entering the inner core decreased with increased particle size because the larger particles were less able to negotiate the turn into the inner core due to particle inertia. The particle phase change analysis results showed that the larger particles warmed less as they were transported through the low pressure compressor. Only the smallest 5 micron particles were warmed enough to produce melting with a maximum average melting fraction of 0.18. The results also showed an appreciable amount of particle sublimation and evaporation for the 5 micron particles entering the engine core (22.6 %).

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Section: Introductionmentioning

confidence: 99%

A Lagrangian parcel based mixing plane method for calculating water based mixed phase particle flows in turbo-machinery

Bidwell

2015

Comp. Part. Mech.

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“…The CFD simulations were performed using the APNASA code, Adamczyk et al (1990). The APNASA code solves the average passage equation system as formulated by Adamczyk (1985).…”

Section: Copyright @)200by Asmementioning

confidence: 99%

An Engine Research Program Focused on Low Pressure Turbine Aerodynamic Performance

Castner

Chiappetta²,

Wyzykowski³

et al. 2002

Volume 1: Turbo Expo 2002

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A comprehensive test program was performed in the Propulsion Systems Laboratory at the NASA Glenn Research Center, Cleveland Ohio using a highly instrumented Pratt and Whitney Canada PW 545 turbofan engine. A key objective of this program was the development of a high-altitude database on small, highbypass ratio engine performance and operability. In particular, the program documents the impact of altitude (Reynolds Number) on the aero-performance of the lowpressure turbine (fan turbine). A second objective was to assess the ability of a state-of-the-art CFD code to predict the effect of Reynolds number on the efficiency of the lowpressure turbine. CFD simulation performed prior and after the engine tests will be presented and discussed.

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“…Three-dimensional steady Reynolds Averaged Navier-Stokes (RANS) simulations of the compressor stage were done with APNASA (version 1.13) developed by Adamczyk [15]. APNASA is a unique multi-stage turbomachinery solver that models the influence of neighboring blade rows by the use of body forces and deterministic stress terms.…”

Section: Numerical Codesmentioning

confidence: 99%

Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

Zante

Chen

2002

Volume 5: Turbo Expo 2002, Parts a and B

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Blade row interaction effects on loss generation in compressors have received increased attention as compressor work-per-stage and blade loading have increased. Two dimensional Laser Doppler Velocimeter measurements of the velocity field in a NASA transonic compressor stage show the magnitude of interactions in the velocity field at the peak efficiency and near stall operating conditions. The experimental data are presented along with an assessment of the velocity field interactions. In the present study the experimental data are used to confirm the fidelity of a three-dimensional, time-accurate, Navier Stokes calculation of the stage using the MSU-TURBO code at the peak efficiency and near stall operating conditions. The simulations are used to quantify the loss generation associated with interaction phenomena. At the design point the stator pressure field has minimal effect of the rotor performance. The rotor wakes do have an impact on loss production in the stator passage at both operating conditions. A method for determining the potential importance of blade row interactions on performance is presented.

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Simulation of Three-Dimensional Viscous Flow Within a Multistage Turbine

Cited by 63 publications

References 0 publications

A Lagrangian parcel based mixing plane method for calculating water based mixed phase particle flows in turbo-machinery

A Lagrangian parcel based mixing plane method for calculating water based mixed phase particle flows in turbo-machinery

An Engine Research Program Focused on Low Pressure Turbine Aerodynamic Performance

Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

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