Research Papers

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

[+] Author and Article Information
Rahul Rajasekharan

School of Engineering and Informatics,
University of Sussex,
Brighton BN1 9RH, UK
e-mail: R.Rajasekharan-Nair@sussex.ac.uk

E. P. Petrov

School of Engineering and Informatics,
University of Sussex,
Brighton BN1 9RH, UK
e-mail: Y.Petrov@sussex.ac.uk

Manuscript received June 22, 2018; final manuscript received July 4, 2018; published online December 3, 2018. Editor: Jerzy T. Sawicki.

J. Eng. Gas Turbines Power 141(4), 041016 (Dec 03, 2018) (10 pages) Paper No: GTP-18-1302; doi: 10.1115/1.4040906 History: Received June 22, 2018; Revised July 04, 2018

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) nonlinear friction contact conditions at blade roots and shrouds are considered. The following two kinds of analysis are performed: (i) local sensitivity analysis (LSA), based on first-order derivatives of system response with respect to design parameters, and (ii) statistical analysis using polynomial chaos expansion (PCE). The PCE 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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Fig. 1

Geometry of (a) full bladed disk and (b) a single blade showing crystallographic axis orientation

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Fig. 2

(a) Finite element mesh of bladed disk model and (b) schematic diagram of fir-tree root geometry

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Fig. 3

Normalized anisotropy angles for all blades in the mistuned bladed disk

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Fig. 4

Sensitivity of displacements at tip node of blade#1 due to angle (a) α, (b) β, and (c) ζ in tuned linear bladed disk

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Fig. 5

Sensitivity of displacements at blade tip of blade#1 to anisotropy angle (a) α, (b) β, and (c) ζ of all blades in a mistuned linear bladed disk

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Fig. 6

Displacements at blade tip of all blades in (a) radial, (b) tangential, and (c) axial direction in a mistuned bladed disk

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Fig. 7

(a) Axial displacement and, its sensitivity to blade#1 anisotropy angles, (b) α, and (c) β in a mistuned bladed disk

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Fig. 8

Sensitivity of stresses at blade root of blade#1 to anisotropy angle (a) α, (b) β, and (c) ζ of all blades in a mistuned bladed disk

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Fig. 9

Polynomial chaos expansion and gradPCE approximations for (a) axial and (b) radial displacement at blade tip of blade#1

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Fig. 10

Standard deviation for displacements with respect to number of evaluations of mistuned bladed disk



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