Contact Stresses in Dovetail Attachments: Physical Modeling

Sinclair, G. B.; Cormier, N. G.

doi:10.1115/2000-gt-0356

Cited by 7 publications

(6 citation statements)

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“…The higher normal contact loads are predicted at points located closer to the rotation axis, in accordance with the existing literature on the distribution of dovetail contact stresses [21].…”

Section: Resultssupporting

confidence: 90%

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Numerical assessment of friction damping at turbine blade root joints by simultaneous calculation of the static and dynamic contact loads

2011

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In turbomachinery, the perfect detuning of turbine blades in order to avoid high cycle fatigue damage due to resonant vibration is often unfeasible due to the high modal density of bladed disks.To obtain reliable predictions of resonant stress levels of turbine blades, accurate modeling of friction damping is mandatory.Blade root is one of the most common sources of friction damping in turbine blades; energy is dissipated by friction due to microslip between the blade and the disk contact surfaces held in contact by the centrifugal force acting on the blade.In this paper, a method is presented to compute the friction forces occurring at blade root joints and to evaluate their effect on the blade dynamics. The method is based on a refined version of the state-ofthe-art contact model, currently used for the nonlinear dynamic analysis of turbine blades. The refined contact model is implemented in a numerical solver based on the harmonic balance method able to compute the steady-state dynamic response of turbine bladesThe proposed method allows solving the static and the dynamic balance equations of the blade and of the disk, without any preliminary static analysis to compute the static loads acting at the contact interfaces.

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Section: Resultssupporting

confidence: 90%

“…11 shows the ratio of T L , what is typical for the static loading [21]. On the contrary, in the second case, due to the large relative vibration amplitude of the contact nodes, the value of T (0) L is significantly lower than μN (0) L , mainly in the upper right part of the contact area characterized by larger relative vibration amplitudes.…”

Section: Resultsmentioning

confidence: 93%

Numerical assessment of friction damping at turbine blade root joints by simultaneous calculation of the static and dynamic contact loads

2011

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“…3(a) to that of fig. 2, we note that the punch profile u p can equally well be interpreted as the amount the indentor would overlap or interpenetrate the half plane were it not for the compensating displacements in eqn (9). With this interpretation, it is of no consequence whether u p comes from interpenetration of the punch into the half plane or vice versa.…”

Section: An Analytical Approach For the Contact Stress Absent Bendingmentioning

confidence: 94%

Edge-of-contact stresses in blade attachments in gas turbines

Sinclair¹

2013

Surface Effects and Contact Mechanics XI

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By drawing on analytical solutions to contact problems in the literature, an approach is developed for obtaining two-dimensional, elastic, edge-of-contact stresses in blade attachments in gas turbines. The approach is validated on a benchmark problem. It uses stress resultants from finite element analysis (FEA): stress resultants converge more rapidly than stresses themselves, so that such FEA is less demanding. In addition to reducing FEA, the analytical approach reveals with explicit expressions the nature of edge-of-contact stresses in blade attachments. In particular in this regard, it identifies a hoop stress component right at the edge of contact that is potentially damaging to blades.

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“…As a result, bladed disc interfaces experience a combination of low cycle fatigue (LCF) due to major loading events, and high cycle fatigue (HCF) due to minor (amplitude) dynamic loads [13]. LCF and HCF loading combinations may result in the early fatigue lift of the blades, as much as 40% to 60% lower along with the crack initialization at the edges of the contact zone [14]. Moreover, bladed discs may also be subjected to unstable vibrations, which may lead to dramatic consequences like blade flutter or rotor instability with divergence [15].…”

Section: Vibrational Problemsmentioning

confidence: 99%

Efficient computational techniques for mistuning analysis of bladed discs: A review

Yuan

Scarpa

Allegri

et al. 2017

Mechanical Systems and Signal Processing

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This paper describes a review of the relevant literature about mistuning problems in bladed disc systems, and their implications for the uncertainty propagation associated to the dynamics of aeroengine systems. An emphasis of the review is placed on the developments of the multi-scale computational techniques to increase the computational efficiency for the linear mistuning analysis, especially with the respect to the reduced order modeling techniques and uncertainty quantification methods. The non-linearity phenomenon would not be considered in this paper. The first two parts describe the fundamentals of the mechanics of tuned and mistuned bladed discs, followed by a review of critical research efforts performed on the development of reduced order rotor models. The focus of the fourth part is on the review of efficient simulation methods for the stochastic analysis of mistuned bladed disc systems. After that, we will finally provide a view of the current state of the art associated to efficient inversion methods for the stochastic analysis, followed by a summary.

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Contact Stresses in Dovetail Attachments: Physical Modeling

Cited by 7 publications

References 0 publications

Numerical assessment of friction damping at turbine blade root joints by simultaneous calculation of the static and dynamic contact loads

Numerical assessment of friction damping at turbine blade root joints by simultaneous calculation of the static and dynamic contact loads

Edge-of-contact stresses in blade attachments in gas turbines

Efficient computational techniques for mistuning analysis of bladed discs: A review

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