Research Papers

Influence of Turbocharger Turbine Blade Geometry on Vibratory Blade Stresses

[+] Author and Article Information
Pavan Naik

Continental Automotive GmbH,
Regensburg 93055, Germany
e-mail: pavan.naik@continental-corporation.com

Bernhard Lehmayr, Stefan Homeier, Michael Klaus

Continental Automotive GmbH,
Regensburg 93055, Germany

Damian M. Vogt

ITSM—Institute of Thermal Turbomachinery
and Machinery Laboratory,
University of Stuttgart,
Stuttgart 70569, Germany
e-mail: damian.vogt@itsm.uni-stuttgart.de

1Corresponding author.

Manuscript received June 29, 2018; final manuscript received July 24, 2018; published online October 4, 2018. Editor: Jerzy T. Sawicki.

J. Eng. Gas Turbines Power 141(2), 021015 (Oct 04, 2018) (9 pages) Paper No: GTP-18-1404; doi: 10.1115/1.4041152 History: Received June 29, 2018; Revised July 24, 2018

In this paper, a method to influence the vibratory blade stresses of mixed flow turbocharger turbine blade by varying the local blade thickness in spanwise direction is presented. Such variations have an influence on both the static and the vibratory stresses and therefore can be used for optimizing components with respect to high-cycle fatigue (HCF) tolerance. Two typical cyclic loadings that are of concern to turbocharger manufacturers have been taken into account. These loadings arise from the centrifugal forces and from blade vibrations. The objective of optimization in this study is to minimize combined effects of centrifugal and vibratory stresses on turbine blade HCF and moment of inertia. Here, the conventional turbine blade design with trapezoidal thickness profile is taken as baseline design. The thicknesses are varied at four spanwise equally spaced planes and three streamwise planes to observe their effects on static and vibratory stresses. The summation of both the stresses is referred to as combined stress. In order to ensure comparability among the studied design variants, a generic and constant excitation order-dependent pressure field is used at a specific location on blade. The results show that the locations of static and vibratory stresses, and hence the magnitude of the combined stresses, can be influenced by varying the blade thicknesses while maintaining the same eigenfrequencies. By shifting the maximum vibratory stresses farther away from the maximum static stresses, the combined stresses can be reduced considerably, which leads to improved HCF tolerance.

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Fig. 2

Location of maximum stresses

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Fig. 1

Interdependence of design parameters

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Fig. 3

Simulation process

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Fig. 12

Temperature profile over blade surface

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Fig. 4

CFD model for URANS simulations

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Fig. 5

Blade mesh for CFD simulations

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Fig. 6

Two-dimensional blade profile showing planes and points for DOE sampling

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Fig. 7

Streamwise blade thickness points

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Spanwise blade thickness points

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Generic load application points

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Load factors at different locations of blade

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Fig. 21

Design comparison for moment of inertia

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Correlation coefficients of moment of inertia

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Fig. 19

Blade thickness variations

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Fig. 20

Design comparison for total stresses

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Schematic representation of MAC variation

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Fig. 14

Correlation coefficients of static stresses on blade

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Fig. 15

Correlation coefficients of vibratory stresses on blade

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Fig. 16

Correlation coefficients of total stress on blade

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Fig. 17

Haigh diagram representing stresses inhibited by design set

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Fig. 22

Design comparison for reduced mass flow

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Fig. 23

Design comparison for turbine efficiency

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Fig. 24

Anthill plot representing the influence of distance of maximum vibratory stress location from blade hub

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Fig. 25

Modal assurance criterion—distributions



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