A New Multistage Axial Compressor Designed With the APNASA Multistage CFD Code: Part 2 — Application to a New Compressor Design

Dong, Yuan; Mansour, M. L.; Hingorani, S.; Hayes, J.

doi:10.1115/2001-gt-0350

Cited by 3 publications

(1 citation statement)

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“…Lee and Kim [4] combined an optimization technique with a three-dimensional thin-layer Navier-Stokes solver to optimize the blade shape of the axial-compressor. Dong et al [5] utilized the code to design a new multi-stage compressor for a modern turbofan engine. They started with a mean-line model, and then used the streamline-curvature flow solver.…”

Section: Introductionmentioning

confidence: 99%

Preliminary Design Optimization of a Gas Turbine Multi-Stage Compressor

Tahsini

2020

JGPP

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In the present study, the preliminary design optimization of an axial-compressor is considered. The axisymmetric flow solver is developed to simulate the flow field within the compressor to predict quickly some important drawbacks of the conceptual design and treat them in preliminary design phase where the conceptual design is made by the mean-line method and the free-vortex assumption is utilized to find the radial distribution of the flow deflection angles. The finite volume scheme is used in this numerical procedure of the inviscid flow simulation where the advection upstream splitting method is used to calculate the fluxes. The focus is on the axial velocity changes along the compressor, and the optimization target of the preliminary design is to increase the minimum axial velocity with the criteria of keeping the mass flow rate and the total pressure ratio constant. The results demonstrate that this target is achieved by minor modification in flow deflection angles to improve the variation of the axial velocity, which can be more important especially in off-design performance of the compressor.

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Section: Introductionmentioning

confidence: 99%

Preliminary Design Optimization of a Gas Turbine Multi-Stage Compressor

Tahsini

2020

JGPP

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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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Aerodynamic Analysis and Three-Dimensional Redesign of a Multi-Stage Axial Flow Compressor

Tao

et al. 2016

Energies

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This paper describes the introduction of three-dimension (3-D) blade designs into a 5-stage axial compressor with multi-stage computational fluid dynamic (CFD) methods. Prior to a redesign, a validation study is conducted for the overall performance and flow details based on full-scale test data, proving that the multi-stage CFD applied is a relatively reliable tool for the analysis of the follow-up redesign. Furthermore, at the near stall point, the aerodynamic analysis demonstrates that significant separation exists in the last stator, leading to the aerodynamic redesign, which is the focus of the last stator. Multi-stage CFD methods are applied throughout the three-dimensional redesign process for the last stator to explore their aerodynamic improvement potential. An unconventional asymmetric bow configuration incorporated with leading edge re-camber and re-solidity is employed to reduce the high loss region dominated by the mainstream. The final redesigned version produces a 13% increase in the stall margin while maintaining the efficiency at the design point.

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A New Multistage Axial Compressor Designed With the APNASA Multistage CFD Code: Part 2 — Application to a New Compressor Design

Cited by 3 publications

References 0 publications

Preliminary Design Optimization of a Gas Turbine Multi-Stage Compressor

Preliminary Design Optimization of a Gas Turbine Multi-Stage Compressor

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

Aerodynamic Analysis and Three-Dimensional Redesign of a Multi-Stage Axial Flow Compressor

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