Blade protection and efficiency preservation of a turbine by a sacrificial material coating

Bounazef, Mokhtar; Guessasma, Sofiane; Bedia, E.A. Adda

doi:10.1163/156855207780208583

Cited by 22 publications

(9 citation statements)

References 4 publications

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“…rubbing of a small incurved abradable coated segment against a rigid blade at in-service sliding speed and incursion rate. Experiments focusing low compressor stages of the engine have pointed out the influential parameters and ranges, 7,12,13 including:…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of the blade/seal interaction

Baiz

Fabis

Boidin

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part J:

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International audienceThe use of dynamic seals to reduce the rotor/stator dynamic clearance in jet engine compressor stages leads to a higher rubbing occurrence between each blade and the coated inside of the casing. This article describes the development of a test rig capable to investigate forces and wear at the dynamic blade/seal interaction, in conjunction with blade kinetics. Testing conditions are consistent with those of low-pressure compressor stages of jet engines: high-speed rubbing occurs between a TA6V blade substitute and an aluminium-silicon/boron nitride abradable seal. The platform is instrumented to allow a dynamic measurement of forces and displacements as well as high-speed imaging of the blade/seal interaction zone throughout the experiment. The experiments showed that the blade incursion speed and penetration depth in the abradable seal both affect the amplitude and frequency of blade vibration. The amount and severity of blade incursions into the abradable seal have an impact on seal wear type and intensity, which can in turn increase blade excitation

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Section: Introductionmentioning

confidence: 99%

Experimental investigation of the blade/seal interaction

Baiz

Fabis

Boidin

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part J:

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show abstract

“…Even though this technique has proved to be effective in minimizing the radial gap, there are two main concerns associated with it: (i) the possibility of the abradable material sticking to the blades, thereby inducing turbulence in the gas flow, and (ii) the phenomenon of blade wear due to friction between blades and abradable material. 26 However, for a mistuned bladed disk with significant scatter in blade mechanical properties, each blade will have marginally different radial elongation, which then precludes the possibility of creating an optimal gap. In this case, the blade with the largest radial elongation will determine the amount of abradable material removed, thereby creating a suboptimal tip-casing gap for other blades in the bladed disk.…”

Section: Background and Motivationmentioning

confidence: 99%

“…Modern gas‐turbine engines use an abradable material seal that allows the formation of an optimal gap between blades and casing during the initial runs. Even though this technique has proved to be effective in minimizing the radial gap, there are two main concerns associated with it: (i) the possibility of the abradable material sticking to the blades, thereby inducing turbulence in the gas flow, and (ii) the phenomenon of blade wear due to friction between blades and abradable material . However, for a mistuned bladed disk with significant scatter in blade mechanical properties, each blade will have marginally different radial elongation, which then precludes the possibility of creating an optimal gap.…”

Section: Introductionmentioning

confidence: 99%

Uncertainty and global sensitivity analysis of bladed disk statics with material anisotropy and root geometry variations

Rajasekharan

Petrov

2019

Engineering Reports

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Monocrystalline blades used in gas turbines exhibit material anisotropy, and the orientation of the anisotropy axis affects the deformation of the bladed disk. Considering the orientation of the anisotropy axis as a random design parameter, the uncertainty and sensitivity analysis for static blade deformations are presented for the first time. The following two cases are analyzed using a realistic bladed disk model with friction contacts: (i) deformation of the tuned bladed disks considering the uncertainty in anisotropy orientation and variations in fir tree root geometry and (ii) deformation of mistuned bladed disks with uncertain blade crystal orientations. For efficient uncertainty and sensitivity analysis, the applicability of the following surrogate models are explored: (i) an ensemble of regression trees (random forest) and (ii) gradient‐based polynomial chaos expansion. Faster convergence in statistical characteristics has been obtained using a surrogate model compared to that obtained from finite element model based Monte Carlo simulation. From sensitivity analysis, it has been inferred that the uncertainty in static displacements of a blade in a bladed disk is primarily due to the uncertainty in anisotropy angles of that blade itself and secondarily due to the interaction of different blade anisotropy angles.

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“…Modern gasturbine engines use an abradable material seal which allows the formation of an optimal gap between blades and casing during the initial runs. Even though this technique has proved to be effective in minimizing the radial gap, there are two main concerns associated with it: (i) the possibility of the abradable material sticking to the blades, thereby, inducing turbulence in gas flow, and (ii) the phenomenon of blade wear due to friction between blades and abradable material [2]. However for a mistuned bladed disk with significant scatter in blade mechanical properties, each blade will have marginally different radial elongation which then precludes the possibility of creating an optimal gap.…”

Section: Background and Motivationmentioning

confidence: 99%

Analysis of Deformation of Mistuned Bladed Disks With Friction and Random Crystal Anisotropy Orientation Using Gradient-Based Polynomial Chaos Expansion

Rajasekharan

Petrov

2018

Volume 7C: Structures and Dynamics

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Single crystal blades used in high pressure turbine bladed disks of modern gas-turbine engines exhibit material anisotropy. In this paper the sensitivity analysis is performed to quantify the effects of blade material anisotropy orientation on deformation of a mistuned bladed disk under static centrifugal load. For a realistic, high fidelity model of a bladed disk both: (i) linear, and (ii) non-linear friction contact conditions at blade roots and shrouds are considered. The following two kinds of analysis are performed: (i) local sensitivity analysis, based on first order derivatives of system response w.r.t design parameters, and (ii) statistical analysis using polynomial chaos expansion. The polynomial chaos expansion is used to transfer the uncertainty in random input parameters to uncertainty in static deformation of the bladed disk. An effective strategy, using gradient information, is proposed to address the “curse of dimensionality” problem associated with statistical analysis of realistic bladed disk.

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Blade protection and efficiency preservation of a turbine by a sacrificial material coating

Cited by 22 publications

References 4 publications

Experimental investigation of the blade/seal interaction

Experimental investigation of the blade/seal interaction

Uncertainty and global sensitivity analysis of bladed disk statics with material anisotropy and root geometry variations

Analysis of Deformation of Mistuned Bladed Disks With Friction and Random Crystal Anisotropy Orientation Using Gradient-Based Polynomial Chaos Expansion

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