PSI - Issue 18

Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2019) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2019) 000–000 Available online at www.sciencedirect.com ScienceDirect

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ScienceDirect

Procedia Structural Integrity 18 (2019) 322–329

25th International Conference on Fracture and Structural Integrity Failure analysis of an aircraft GTE compressor disk on the base of imitation modeling principles V.N. Shlyannikov, R.R. Yarullin*, I.S. Ishtyryakov Institute of Power Engineering and Advanced Technologies FRC Kazan Scientific Center, Russian Academy of Sciences, Lobachevsky Street, 2/31 - 420111 Kazan, Russia Abstract This study is concerned with failure analysis of an aircraft gas turbine engine (GTE) compressor disk made from titanium alloy on the base of imitation modeling principles. The failures have occurred by part-through surface cracks in a disk and blade “dovetail type” attachment. On the base of this attachment dimensions the two geometries of imitation models of GTE compressor disk are developed. The loading conditions of the imitation models are found and numerically verified to reproduce the loading conditions in the compressor disk at operation. The comparisons of stress-strain state at critical zones of compressor disk and imitation models are presented. Experimental fixtures are designed to reproduce operation loading conditions in compressor disk during the tests on a servo-hydraulic test system. It is demonstrated that proposed imitation modeling principles allow estimating residual life of compressor disk with taking into account crack initiation and growth at critical zones. The possibility of using experimental imitation modeling for calibration of the theoretical crack growth rate model including the fracture process zone sizes and nonlinear fracture resistance parameters is considered. 25th International Conference on Fracture and Structural Integrity Failure analysis of an aircraft GTE compressor disk on the base of imitation modeling principles V.N. Shlyannikov, R.R. Yarullin*, I.S. Ishtyryakov Institute of Power Engineering and Adv nc d Technologies FRC Kazan Scientific Center, Russian Academy of Sciences, Lobachevsky Street, 2/31 - 420111 Kazan, Russia Abstract This study is concerned with failure analysis of an aircraft gas turbine engine (GTE) c mpressor disk made from titanium alloy on the base of imitation modeling principles. The failures have occurred by part-through surface cracks i a disk and blade “dovetail type” ttachment. On the base of this attachment dimensions the two geometries of imitation models of GTE compressor disk are developed. The loading conditions of the imitation models are found and numerically verified to reproduce the loading conditions in the compressor isk at operation. The comparisons of stress-strain state at critical zones of compressor disk and imitation models are presented. Experimental fixtures are designed to reproduce operation loading conditions in compr ssor disk during the tests on a servo-hy raulic test system. It is demonstrated that proposed imitation modeling principles allow estimating residual lif of compressor disk with taking int account crack initiation and growth at critical zones. T possibility of using exp rimental imit tion modeling for calibration of the theoretical crack growth rate model including the fracture process zone sizes and nonlinear fracture resistance parameters is considered.

© 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo.

Keywords: Gas turbine engine; compressor disk; titanium alloy; imitation model; stress-strain state; biaxial loading; fracture surface. Keywords: Gas turbine engine; compressor disk; titanium alloy; imitation model; stress-strain state; biaxial loading; fracture surface.

1. Introduction Today civil aviation gas turbine engine (GTE) components design becomes very demanding due to high temperatures, complex mechanical loads, corrosive environment and long expected lifetimes. Such loading 1. Introduction Today civil aviation gas turbine engine (GTE) components design becomes very demanding due to high temperatures, complex mechanical loads, corrosive environment and long expected lifetimes. Such loading

2452-3216 © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. 2452-3216 © 2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. * Correspon ing author. +7-843-236-31-02; fax: +7-843-236-31-02. E-mail address: yarullin_r@mail.ru * Corresponding author. +7-843-236-31-02; fax: +7-843-236-31-02. E-mail address: yarullin_r@mail.ru

2452-3216  2019 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. 10.1016/j.prostr.2019.08.172