PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 5 (2017) 1349–1354 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i ir t. Structural Integrity Procedia 00 (2017) 000 – 000

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XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal Thermo-mechanical modeling of a high pressure turbine blade of an airplane gas turbine engine P. Brandão a , V. Infante b , A.M. Deus c * a Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal b IDMEC, Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal c CeFEMA, Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal Abstract During their operation, modern aircraft engine components are subjected to increasingly demanding operating conditions, especially the high pressure turbine (HPT) blades. Such conditions cause these parts to undergo different types of time-dependent degradation, one of which is creep. A model using the finite element method (FEM) was developed, in order to be able to predict the creep behaviour of HPT blades. Flight data records (FDR) for a specific aircraft, provided by a commercial aviation company, were used to obtain thermal and mechanical data for three different flight cycles. In order to create the 3D model needed for the FEM analysis, a HPT blade scrap was scanned, and its chemical composition and material properties were obtained. The data that was gathered was fed into the FEM model and different simulations were run, first with a simplified 3D rectangular block shape, in order to better establish the model, and then with the real 3D mesh obtained from the blade scrap. The overall expected behaviour in terms of displacement was observed, in particular at the trailing edge of the blade. Therefore such a model can be useful in the goal of predicting turbine blade life, given a set of FDR data. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Torsion vibrations monitoring of turbine shafts Jar slav Václavík* , Jan Chvojan Dynamic Testing Laboratory, Výzkumný a zkušební ústav Plzeň s.r.o., 301 00 Plzeň, Czech Republic, vaclavik@vzuplzen.cz The objective of this article is to describe the on-line measurement system, which was installed in one of Czech nuclear power stations for continuous monitori g of torsional vibrations of the turbine-ge erator and to give some results, obtained from more than four years system operations. The goal of the measurement system is to look for high stress peaks, calculate the basic rainflow matrix applicable for damage accumulation estimation at desired point on the structure and follow the specific frequencies in the torsional spectra, which can be responsible for or can detect the damage of LP turbine blades. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: structure health monitoring; torsional vibrations; turbine; generator; shaft 1. Introduction The shaft systems o large grid-connected steam turbine generators are subjected to dynamic torque oscillations caused by line faults, phase imbalance or negative sequence currents in the generator. These currents can be grid induced, or caused by unbalanced electrical shorts in the windings. The resulting torsional impulse is applied to the generator rotor at twice the line frequency and transmitted along the turbine generator shaft train responding as a torsional spring-mass system. This torsional response can be amplified if this impulse frequency is aligned clos ly with a natural frequency of the lightly damped shaft dynamic system. La g torsio al vibration can cause th accumulation of high cycle fatigue damage in the large low pressure turbine blades, retaining rings, shaft sections, and other components. tr t r l I t rit , I I , - t r , l, ir , rtugal l l í , j yna ic esting aboratory, ýzkumný a zkušební ústav Plzeň s.r.o., 301 00 Plzeň, Czech Republic, vaclavik@vzuplzen.cz str ct The objective of this article is to escri e t e n-line measurement system, which was installed in one of zec clear er stati s f r c ti s it ri f t rsi al i rati s f t e t r i e- enerat r a t i e s e res lts, tai e fr re t a f r ears s ste erati s. e al f t e eas re e t s ste is t l f r i stress ea s, calc late t e asic rai fl atri a lica le f r a a acc lati esti ati at esi e i t t e str ct re a f ll t e s ecific fre e cies i t e t rsi al s ectra, ic ca e res si le f r r ca etect t e a a e f t r i e la es. © 2017 The Authors. Published by Elsevier B.V. Peer-revie u er res si ilit f t e cie tific ittee f I I . ey ords: structure health onitoring; torsional vibrations; turbine; generator; shaft . I t ti s ft s st s l r ri - t st t r i r rs r s j t t i r s ill ti s s li f lts, i l r ti s rr ts i t r t r. s rr ts ri - i , r s l l tri l s rts i t i i s. The resulting torsional i ls is li t t r t r r t r t t i t li fr tr s itt l t t r i r t r s ft tr i r s i s t rsi l s ri - ss s st . is t rsi l r s s lifi if t is i ls fr is li l sel it t r l fr f t li tl s ft i s st . r e t rsi n l i r ti s t l ti f i l f ti i t l r l r ss r t r i l s, r t i i ri s, s ft s ti s, t r ts. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Abstract I t r ti l f r

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +420-605-221-757. E-mail address: vaclavik@vzuplzen.cz * orresponding author. el.: 420-605-221-757. - ail address: vaclavik vzuplzen.cz

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.197 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 2017 he uthors. ublished by lsevier . . eer-re ie er res si ilit f t e cie tific ittee f I I .