Validation and Calibration of Modern CFD RANS Codes for the Prediction of Transonic Axial-Centrifugal Compressors

Mansour, M. L.; Holbrook, Greg; Gunaraj, John; Qizar, Mohamed; Mangat, Vikram

doi:10.1115/gt2008-50652

Cited by 3 publications

(2 citation statements)

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“…• The objective function and aerodynamic performances of blade sample database were calculated by CFD solver. FINE/TURBO [17,18] was employed as an available CFD solver. The internal flow of the blade was simulated by using the structured mesh and second order cell-vertex finite volume discretization method.…”

Section: Optimization Algorithmmentioning

confidence: 99%

An integrated blade optimization approach based on parallel ANN and GA with hierarchical fair competition dynamic-niche

Zhang

Wang

et al. 2011

J Mech Sci Technol

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This work presented an available multi-point blade optimization procedure for better aerodynamic performances. Based on the proposed Parallel ANN and GA with hierarchical fair competition dynamic-niche (GA-HFCDN), an integrated approach for the blade optimization design was put forward by combining Bezier parameterization with FINE/TURBO solver. In the optimization design, parallel ANN was employed to build a more proper approximate model. GA-HFCDN was proposed to obtain the global optimization solution more efficiently for the blade design. Two research cases, including plane cascades blade optimization and the optimization and experimental study of a low specific speed centrifugal blower blade, were performed by using the above approach. The conclusions showed the rationality and validity of the optimization approach.

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Section: Optimization Algorithmmentioning

confidence: 99%

An integrated blade optimization approach based on parallel ANN and GA with hierarchical fair competition dynamic-niche

Zhang

Wang

et al. 2011

J Mech Sci Technol

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“…Van Zante et al [4] performed tip clearance flow LDV measurements on an existing NASA Rotor 35 to assess the accuracy of numerical tip clearance flow predictions. To validate numerical simulations of more complex compressors, Mansour et al [5] and Cornelius et al [6] validated their computational solutions with measurements obtained from their multistage transonic compressor rig.…”

Section: Introductionmentioning

confidence: 99%

Low-Cost Rotating Experimentation in Compressor Aerodynamics Using Rapid Prototyping

Michaud

Milan

2016

International Journal of Rotating Machinery

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With the rapid evolution of additive manufacturing, 3D printed parts are no longer limited to display purposes but can also be used in structural applications. The objective of this paper is to show that 3D prototyping can be used to produce low-cost rotating turbomachinery rigs capable of carrying out detailed flow measurements that can be used, among other things, for computational fluid dynamics (CFD) code validation. A fully instrumented polymer two-stage axial-mixed flow compressor test rig was designed and fabricated with stereolithography (SLA) technology by a team of undergraduate students as part of a senior-year design course. Experiments were subsequently performed on this rig to obtain both the overall pressure rise characteristics of the compressor and the stagnation pressure distributions downstream of the blade rows for comparison with CFD simulations. In doing so, this work provides a first-of-a-kind assessment of the use of polymer additive technology for low-cost rotating turbomachinery experimentation with detailed measurements.

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Study of Steady State and Transient Blade Row CFD Methods in a Moderately Loaded NASA Transonic High-Speed Axial Compressor Stage

Qizar

Mansour

Goswami

2013

Volume 6B: Turbomachinery

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The effect of blade row interaction and hub leakage flow on the performance of moderately loaded NASA transonic hybrid compressor stage (Rotor 35 / Stator 37) is investigated through three-dimensional steady state and time-accurate, Navier Stokes calculations of the stage using the ANSYS CFX code at peak efficiency and near stall operating conditions. Understanding unsteady flow phenomena in compressor stages requires the use of time-accurate CFD simulations. Due to the inherent differences in blade counts between adjacent blade rows, the flow conditions at any given instant in adjacent blade rows differ. Depending on the blade counts, it may be necessary to model the entire annulus of the stage; however, this requires considerable computational time and memory resources. Several methods for modeling the transient flow in turbo machinery stages which require a minimal number of blade passages per row, and therefore reduced computational demands, have been presented in the literature. Recently, some of these methods have become available in commercial CFD solvers. The paper describes the steady and the unsteady CFD approaches used for investigating the ability to predict the measured performance of the NASA transonic axial stage design known as the hybrid stage, which consists of the axial Rotor35 and the axial stator 37. The steady approach employs the mixing-plane while the unsteady approaches are URANS with one based on full annulus simulation for the stage and the second enables simulations for the stage using reduced computational model, with a single passage from each blade row based on the time-tilting or the time-transformation technique. The above methods are evaluated and compared in terms of computational efficiency and comparison is made to steady stage simulations. Comparisons to overall performance data and two-dimensional Laser Doppler Velocimeter measurements of the velocity field are used to assess the predictive capabilities of the methods. Computed flow features are examined, and compared with reported measurements. This paper presents validation and calibration of methods used for determining blade row interactions and the respective predictive capabilities against the full annulus and the experimental test data.

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Validation and Calibration of Modern CFD RANS Codes for the Prediction of Transonic Axial-Centrifugal Compressors

Cited by 3 publications

References 0 publications

An integrated blade optimization approach based on parallel ANN and GA with hierarchical fair competition dynamic-niche

An integrated blade optimization approach based on parallel ANN and GA with hierarchical fair competition dynamic-niche

Low-Cost Rotating Experimentation in Compressor Aerodynamics Using Rapid Prototyping

Study of Steady State and Transient Blade Row CFD Methods in a Moderately Loaded NASA Transonic High-Speed Axial Compressor Stage

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