Because the coatings are likely to produce new mistuning which aggravates the vibration failure of coated blades, it is particularly important to study the mistuning identification for coated blades. In this study, the degrees of freedom of the whole disk of the coated blisk is completely constrained, and the orders of the dynamic model of the coated blisk based on component mode mistuning (CMM) method is further reduced. Based on this model, a novel mistuning identification method for the coated blade of the coated blisk by small amount of experimental data is proposed, which can identify the mass, stiffness and damping mistuning of the blade substrates and coatings. The input parameters with high amount of data, such as modal shape matrix, are removed from identification formulas, thus, both the amount of data for identification calculation and the workload of vibration testing are reduced. The mistuning identifications of the numerical case and actual case are carried out respectively, and the identification process of the mistuning identification method in this paper is compared with the one based on the classical CMM model. It is shown that the mistuning identification method is effective and feasible, and the identification efficiency is higher than the classical CMM identification method.
YuZYZhuSPLiuQ, et al.
A new energy-critical plane damage parameter for multiaxial fatigue life prediction of turbine blades. Materials2017;
10: 923.
2.
VyasNS, Sidharth and RaoJS.Dynamic stress analysis and a fracture mechanics approach to life prediction of turbine blades. Mech Mach Theory1997;
32: 511–527.
3.
ZhuSPYangYJHuangHZ, et al.
A unified criterion for fatigue–creep life prediction of high temperature components. Proc IMechE, Part G: J Aerospace Engineering2017;
231: 677–688.
4.
SalamITauqirAKhanAQ.Creep-fatigue failure of an aero engine turbine blades. Eng Fail Anal2002;
9: 335–347.
5.
GachonYIennyPFornerA, et al.
Erosion by solid particles of W/W–N multilayer coatings obtained by PVD process. Surf Coat Technol1999;
113: 140–148.
6.
XieYWangMZhangG, et al.
Analysis of superalloy turbine blade tip cracking during service. Eng Fail Anal2006;
13: 1429–1436.
7.
PoursaeidiENiaeiAMLashgariM, et al.
Experimental studies of erosion and corrosion interaction in an axial compressor first stage rotating blade material. Appl Phys A2018;
124: 629.
8.
TengLNakatomiDSeetharamanS.Oxidation behavior of TiAl-8Nb turbine blade alloy. Metall Mater Trans B2007;
38: 477–484.
9.
LinHGengHZhouX, et al. High cycle fatigue analysis of third stage blade based on shroud gap effect. In: 2016 IEEE International Conference on Mechatronics and Automation. Piscataway: IEEE, 2016, pp. 1781–1786.
10.
TangWEpureanuBIFilippiS.Models for blisks with large blends and small mistuning. Mech Syst Signal Process2017;
87: 161–179.
11.
MaywaldDITBeirowPIHBKühhornDIA.Mistuning and damping of turbine impellers. Mtz Worldw2015;
76: 40–47.
12.
HeZEpureanuBIPierreC.Parametric study of the aeroelastic response of mistuned bladed disks. Comput Struct2007;
85: 852–865.
13.
ChanYJEwinsDJ.Prediction of vibration response levels of mistuned integral bladed disks (blisks): robustness studies. J Turbomach2012;
134: 044501.
14.
LaxaldeDThouverezFSinouJJ, et al.
Qualitative analysis of forced response of blisks with friction ring dampers. Eur J Mech A/Solids2007;
26: 676–687.
15.
JiuzhouLIULinLIYuFAN, et al.
Research on vibration suppression of a mistuned blisk by a piezoelectric network. Chin J Aeronaut2018;
31: 285–299.
16.
ZhuSPYuePYuZY, et al.
A combined high and low cycle fatigue model for life prediction of turbine blades. Materials2017;
10: 698.
17.
SahooBPanigrahiSK.Low cycle fatigue behaviour of a turbine blade made of nickel base wrought alloy. AMR2014;
891–892: 506–511.
18.
WangZDLiJGuanZW, et al.
Fabrication and evaluation of an amino modified epoxy coating for anti-scouring and anti-corrosion application. Msf2015;
815: 684–689.
19.
TabakoffWMetwallyM.Coating effect on particle trajectories and turbine blade erosion. J Eng Gas Turb Power1992;
114: 250–257.
20.
ZhuWWangJWYangL, et al.
Modeling and simulation of the temperature and stress fields in a 3D turbine blade coated with thermal barrier coatings. Surf Coat Technol2017;
315: 443–453.
21.
FilippiSTorvikPJ.A methodology for predicting the response of blades with nonlinear coatings. J Eng Gas Turb Power2011;
133: 042503.
22.
VargiuPFirroneCMZuccaS, et al.
A reduced order model based on sector mistuning for the dynamic analysis of mistuned bladed disks. Int J Mech Sci2011;
53: 639–646.
23.
BattiatoGFirroneCMBerrutiTM, et al.
Reduction and coupling of substructures via gram–Schmidt interface modes. Comput Methods Appl Mech Eng2018;
336: 187–212.
24.
GaoFSunW.Reduced-order modeling for and vibration characteristics analysis of a hard-coated mistuned blisk. Coatings2017;
7: 103.
25.
LupiniAEpureanuBI.A conditioning technique for projection-based reduced order models. Comput Methods Appl Mech Eng2019;
349: 251–265.
26.
WeberRKühhornA.Mistuning identification approach with focus on high-speed centrifugal compressors. J Eng Gas Turb Power2019;
141: 032507.
27.
FeinerDMGriffinJH.Mistuning identification of bladed disks using a fundamental mistuning model—part I: theory. J Turbomach2004;
126: 150–158.
28.
FeinerDMGriffinJH.Mistuning identification of bladed disks using a fundamental mistuning model—part II: application. J Turbomach2004;
126: 159–165.
29.
GillaughDLKaszynskiAABrownJM, et al.
Mistuning evaluation comparison via as-manufactured models, traveling wave excitation, and compressor rigs. J Eng Gas Turb Power2019;
141: 061006.
30.
BhartiyaY.Single and multi-stage bladed rotors with geometric mistuning: reduced order modeling and mistuning identification.
State College:
The Pennsylvania State University, 2011.
31.
BhartiyaYSinhaA.Geometric mistuning identification of integrally bladed rotors using modified modal domain analysis. J Eng Gas Turb Power2014;
136: 122504.
32.
JudgeJAPierreCCeccioSL.Experimental mistuning identification in bladed disks using a component-mode-based reduced-order model. AIAA J2009;
47: 1277–1287.
33.
ZhangLHeYYuanH, et al.
Vibration characteristics analysis of mistuned bladed disk system based on mobile interface prestressed CMS super-element method. J Vibroeng2018;
20: 2576–2692.
34.
PichotFLaxaldeDSinouJJ, et al.
Mistuning identification for industrial blisks based on the best achievable eigenvector. Comput Struct2006;
84: 2033–2049.
35.
LimSH.Dynamic analysis and design strategies for mistuned bladed disks.
Ann Arbor:
University of Michigan, 2005.
36.
LiJ.Experimental investigation of mistuned bladed disks system vibration.
Ann Arbor:
University of Michigan, 2007.
37.
MaddenACCastanierMPEpureanuBI.Reduced-order model construction procedure for robust mistuning identification of blisks. AIAA J2008;
46: 2890–2898.
38.
MaddenACCastanierMPEpureanuBI.Mistuning identification of blisks at higher frequencies. AIAA J2011;
49: 1299–1302.
39.
HollandDECastanierMPCeccioSL, et al.
Testing and calibration procedures for mistuning identification and traveling wave excitation of blisks. J Eng Gas Turb Power2010;
132: 042502.
40.
NyssenFGolinvalJC.Identification of mistuning and model updating of an academic blisk based on geometry and vibration measurements. Mech Syst Signal Process2016;
68–69: 252–264.
41.
NyssenFEpureanuBGolinvalJC.Experimental modal identification of mistuning in an academic two-stage drum. Mech Syst Signal Process2017;
88: 428–444.
42.
XuKSunWGaoJ.Mistuning identification and model updating of coating blisk based on modal test. Mech Syst Signal Process2019;
121: 299–321.
