An Effective Turbine Blade Parameterization and Aerodynamic Optimization Procedure Using an Improved Response Surface Method

Chen, Naixing; Zhang, Hongwu; Ning, Fangfei; Xu, Yu; Huang, Wenhao

doi:10.1115/gt2006-90104

Cited by 10 publications

(8 citation statements)

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“…The reduction of fuel consumption is a driving factor in the design of turbomachinery, both for environmental and economic reasons. As the aerodynamic performance of rotating blades is one of the key parameters in the overall engine efficiency, it is one of the main focuses of rotor design, relating to fan [1], compressor [2,3,4] or turbine [5,6] stages. In particular, tighter operating clearances are desirable between rotating blades and the surrounding casing to reduce tip losses [7].…”

Section: Introductionmentioning

confidence: 99%

Blackbox Optimization for Aircraft Engine Blades With Contact Interfaces

Lainé

Piollet

Nyssen

et al. 2019

Journal of Engineering for Gas Turbines and Power

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In modern aircraft engines, reduced operating clearances between rotating blade tips and the surrounding casing increase the risk of blade/casing structural contacts, which may lead to high blade vibration levels. Therefore, structural contacts must now be accounted for as early as in the engine design stage. As the vibrations resulting from contact are intrinsically nonlinear, direct optimization of blade shapes based on vibration simulation is not realistic in an industrial context. A recent study on a blade featuring significantly lower vibration levels following contact event identified a potential criterion to estimate a blade sensitivity to contact interactions. This criterion is based on the notion of dynamic clearance, a quantity describing the evolution of the blade/casing clearance as the blade vibrates along one of its free-vibration modes. This paper presents an optimization procedure, which minimizes the dynamic clearance as a first step toward the integration of structural criteria in blade design. A dedicated blade geometry parameterization is introduced to allow for an efficient optimization of the blade shape. The optimization procedure is applied to the three-dimensional (3D) properties of two different blades. In both cases, initial and optimized blades are compared by means of an in-house numerical tool dedicated to the simulation of structural contact events with a surrounding casing. The simulations focus on rubbing phenomena, involving the vibration of a single blade. Simulation results show a significant reduction of vibration levels following contact interactions for the optimized blades. Critical speeds related to the mode on which the dynamic clearance is computed are successfully eliminated by the blade shape optimization. For the investigated blade geometries, backward sweep and backward lean angles are associated with reduced contact interactions compared to forward sweep and forward lean angles.

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Section: Introductionmentioning

confidence: 99%

Blackbox Optimization for Aircraft Engine Blades With Contact Interfaces

Lainé

Piollet

Nyssen

et al. 2019

Journal of Engineering for Gas Turbines and Power

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“…A parameterization method, suggested in the papers [22,23,25], was applied to construct a compressor blading with a set of polynomials.…”

Section: Introductionmentioning

confidence: 99%

Blade parameterization and aerodynamic design optimization for a 3D transonic compressor rotor

Chen

Zhang

et al. 2007

J. of Therm. Sci.

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The present paper describes an optimization methodology for aerodynamic design of turbomachinery combined with a rapid 3D blade and grid generator (RAPID3DGRID), a N.S. solver, a blade parameterization method (BPM), a gradient-based parameterization-analyzing method (GPAM), a response surface method (RSM) with zooming algorithm and a simple gradient method. By the use of blade parameterization method a transonic compressor rotor can be expressed by a set of polynomials, and then it enables us to transform coordinate-expressed blade data to parameter-expressed and then to reduce the number of parameters. With changing any one of the parameters and by applying grid generator and N.S. solver, we can obtain several groups of samples. Here only ten parameters were considered to search an optimized compressor rotor. As a result of optimization, the adiabatic efficiency was increased by 1.73%.

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“…In an increasingly competitive global market, aircraft engines manufacturers must design more efficient engines in order to reduce their fuel consumption both for economic and environmental reasons. Over the past decade, mainly two avenues have been considered to achieve this goal: (1) the use of novel and lighter materials [1] and, (2) the reduction of aerodynamic losses [2,3], specifically in compressor stages [4,5,6].…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical characterization of a ceramic matrix composite shroud segment under impact loading

Nyssen

Tableau

Lavazec

et al. 2020

Journal of Sound and Vibration

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This work focuses on the experimental and numerical characterization of stress levels within a shroud segment made of ceramic matrix composite (CMC) material undergoing repeated blade contacts. The dedicated experimental setup consists in a rotating disk with three notched mock blades that impact the shroud segment as they rotate. The underplatform on which the shroud is fixed progressively gets closer to the blades, so that the abradable layer deposited onto the shroud is progressively worn out from a blade revolution to another. Four sensors, located under the shroud segment, are used to record forces during the experiments. Different blade/shroud relative positions are tested, in such a way that impacts may occur at distinct locations. In addition to the experimental tests, a numerical model is built based on both reduced order models of the blade and the shroud segment, in order to numerically predict the forces at the four sensors. This numerical model is first calibrated based on a single reference test case to retrieve the same force magnitude at each sensor. Then, the other tests are simulated using the calibrated model. Predicted contact forces are in good agreement with experimental data, which validates the numerical model. Finally, simulations are carried out considering engine-like conditions, which could not be reproduced using the experimental test bench. The influence of several parameters (radial velocity, impact location, number of blades in contact and angular speed) is analyzed in detail.

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An Effective Turbine Blade Parameterization and Aerodynamic Optimization Procedure Using an Improved Response Surface Method

Cited by 10 publications

References 0 publications

Blackbox Optimization for Aircraft Engine Blades With Contact Interfaces

Blackbox Optimization for Aircraft Engine Blades With Contact Interfaces

Blade parameterization and aerodynamic design optimization for a 3D transonic compressor rotor

Experimental and numerical characterization of a ceramic matrix composite shroud segment under impact loading

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