Aerodynamic Design Optimization of an Axial Flow Compressor Rotor

Ahn, Chang-Soo; Kim, Kwang‐Yong

doi:10.1115/gt2002-30445

Cited by 25 publications

(17 citation statements)

References 10 publications

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“…This reduced the aerodynamic shock losses and entropy generation, showing in some cases a peak efficiency increment of over 1% at design speed . Similar results were previously obtained using a numerical optimization algorithm (Ahn & Kim, 2002). Fig.…”

Section: Three-dimensional Shaped Bladingssupporting

confidence: 80%

State-of-Art of Transonic Axial Compressors

Biollo¹,

Benini²

2011

Advances in Gas Turbine Technology

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Section: Three-dimensional Shaped Bladingssupporting

confidence: 80%

State-of-Art of Transonic Axial Compressors

Biollo¹,

Benini²

2011

Advances in Gas Turbine Technology

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“…These experimental measurements now serve as a basis for the validation of numerical methods [30]. As a classical test case representative of complex three-dimensional viscous flow in transonic bladings [31], rotor 37 is also used as an application case for aerodynamic optimization methods [31,32,41]. In this sense, rotor 37 constitutes a standard test case in aerodynamics.…”

Section: Resultsmentioning

confidence: 99%

“…The goal of this paper is to propose an open and realistic test case to serve as a benchmark for contact simulations. Such test cases are commonly used in aerodynamics for example, where NASA rotor 37 (a compressor blade) and NASA rotor 67 (a fan blade) are often used to validate numerical methods or to serve as a basis for studies on blade design [30,31,32]. The systematic use of a few open geometries not only allows validating numerical methods, it also leads to a sum of works that are directly comparable, that provide a better understanding of the phenomena at stake, and that can be used utimately to extract design guidelines.…”

Section: Introductionmentioning

confidence: 99%

Blade/casing rubbing interactions in aircraft engines: Numerical benchmark and design guidelines based on NASA rotor 37

Piollet

Nyssen

Batailly

2019

Journal of Sound and Vibration

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Blade/casing rubbing interactions in aircraft engines: Numerical benchmark and design guidelines based on NASA rotor 37. Journal of Sound and Vibration, Elsevier, 2019, 460, pp.Abstract In order to improve the efficiency of aircraft engines, the reduction of clearances between blade tips and their surrounding casing is one avenue manufacturers consider to lower aerodynamic losses. This reduction increases the risk of blade tip/casing contact interactions under nominal operating conditions. Designers need tools to accurately predict subsequent nonlinear vibrations. Engineers and researchers have developed a variety of sophisticated numerical models to predict blades' responses. These models are related to distinct frameworks (time/frequency domain) and various solution algorithms (explicit/implicit time integration schemes, penalty/Lagrange multiplier contact treatment...) which calls for comparative analyses. However, published results are often limited for the sake of confidentiality thus preventing any detailed confrontation. While qualitative understanding can be gained from simplified academic models, full scale models are needed to predict complex interactions in a realistic manner. In this context, this paper proposes a benchmark featuring detailed simulations and analyses of a full 3D finite element model based on the open NASA rotor 37 compressor blade to facilitate reproducibility and collaboration across the research community. NASA rotor 37, a compressor stage widely used as a test case in aerodynamic simulations and validations, has the advantage of presenting a realistic blade geometry. The geometry of the blade is built from publicly available reports. The paper provides details on the geometry, the numerical model and the results to allow an easy use of this model across the fields of structural dynamics. Two contact scenarios are investigated: one with direct contact against the casing, and one with abradable material deposited on the casing to mitigate contact severity through wear. The nonlinear vibration response of the blade is simulated in the time domain. It is evidenced that the addition of the abradable material decreases the amplitude of vibration for most of the angular speeds investigated. However, new interactions appear for some angular speeds. The obtained results are consistent with previous simulations on industrial geometries. Based on works showing improved aerodynamic performances when the blade is tilted, a total of seven geometries are investigated: the reference blade, with a straight vertical stacking line similar to the original rotor 37, two forward-leaned blades, two backward-swept blades and two full forward chordwise swept blades. The sweep and lean variations are shown to have a dramatic impact on the vibration response: the backward sweep results in an increased blade's robustness to contact events and the full forward chordwise sweep in a reduced robustness, while the forward lean leads to a robustness similar to the reference blade. RésuméLa réduction des jeux au...

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“…Some works on numerical optimization of stacking line of blade based on threedimensional RANS (Reynolds-averaged Navier-Stokes equations) analysis have been performed. Ahn and Kim [9] improved performance of an axial flow compressor by optimizing skewed stacking line of rotor blade using three-dimensional thin-layer Navier-Stokes analysis and RSM [7].…”

Section: Introductionmentioning

confidence: 99%

Design optimization of a low-speed fan blade with sweep and lean

Seo

Choi

Kim

2008

Proceedings of the Institution of Mechanical Engineers, Part A:

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The present work performs numerical optimization for design of blade stacking line for an axial flow fan with response surface method using three-dimensional Navier -Stokes analysis, and evaluates the effects of sweep and lean on the performance of the fan blade. Reynolds-averaged Navier -Stokes equations are discretized with finite-volume approximations using unstructured grids. Four geometric variables concerning spanwise distributions of sweep and lean of blade stacking line are chosen as design variables to find maximum efficiency. The computational results show good agreements with experimental data. The total efficiency is successfully increased in comparison with the reference fan by optimizing threedimensional stacking line with sweep and lean. Coupling of sweep and lean also improves off-design performance of the blade remarkably.

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Aerodynamic Design Optimization of an Axial Flow Compressor Rotor

Cited by 25 publications

References 10 publications

State-of-Art of Transonic Axial Compressors

State-of-Art of Transonic Axial Compressors

Blade/casing rubbing interactions in aircraft engines: Numerical benchmark and design guidelines based on NASA rotor 37

Design optimization of a low-speed fan blade with sweep and lean

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