Experimental and Numerical Analyses of Radial Turbine Blisks With Regard to Mistuning

Hönisch, Peter; Kühhorn, Arnold; Beirow, Bernd

doi:10.1115/gt2011-45359

Cited by 13 publications

(8 citation statements)

References 14 publications

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“…For that purpose, the SNM models have been chosen, which have to be individually updated for every frequency mistuning pattern being experimentally determined. In this regard, it is a well-established technique to adjust the Young’s modulus of each blade according to the measured distributions of relative blade-dominated frequency deviations depicted in the previous section ( 17 ) . Assuming that …”

Section: Structural Mistuningmentioning

confidence: 99%

Model update and validation of a mistuned high-pressure compressor blisk

et al. 2019

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In order to prepare an advanced 4-stage high-pressure compressor rig test campaign, details regarding both accomplishment and analysis of preliminary experiments are provided in this paper. The superior objective of the research project is to contribute to a reliable but simultaneously less conservative design of future high pressure blade integrated disks (blisk). It is planned to achieve trend-setting advances based on a close combination of both numerical and experimental analyses. The analyses are focused on the second rotor of this research compressor, which is the only one being manufactured as blisk. The comprehensive test program is addressing both surge and forced response analyses e.g. caused by low engine order excitation. Among others the interaction of aeroelastics and blade mistuning is demanding attention in this regard. That is why structural models are needed, allowing for an accurate forced response prediction close to reality. Furthermore, these models are required to support the assessment of blade tip timing (BTT) data gathered in the rig tests and strain gauge (s/g) data as well. To gain the maximum information regarding the correlation between BTT data, s/g-data and pressure gauge data, every blade of the second stage rotor (28 blades) is applied with s/g. However, it is well known that s/g on blades can contribute additional mistuning that had to be considered upon updating structural models.Due to the relevance of mistuning, efforts are made for its accurate experimental determination. Blade-by-blade impact tests according to a patented approach are used for this purpose. From the research point of view, it is most interesting to determine both the effect s/g-instrumentation and assembling the compressor stages on blade frequency mistuning. That is why experimental mistuning tests carried out immediately after manufacturing the blisk are repeated twice, namely, after s/g instrumentation and after assembling. To complete the pre-test program, the pure mechanical damping and modal damping ratios dependent on the ambient pressure are experimentally determined inside a pressure vessel. Subsequently the mistuning data gained before is used for updating subset of nominal system mode (SNM) models. Aerodynamic influence coefficients (AICs) are implemented to take aeroelastic interaction into account for forced response analyses. Within a comparison of different models, it is shown for the fundamental flap mode (1F) that the s/g instrumentation significantly affects the forced response, whereas the impact of assembling the compressor plays a minor role.

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Section: Structural Mistuningmentioning

confidence: 99%

Model update and validation of a mistuned high-pressure compressor blisk

et al. 2019

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“…They could find a response amplification of 5.02 compared to the tuned counterpart close to the Whitehead-limit of 5.30. In fact, mostly ' amplification factors ranging between 1 and hardly greater than 2 were found by Ewins [4], Griffin and Hoosac [5], Basu and Griffin [6], Jugde et al [7], Kenyon et al [8], Sever [9], Castanier and Pierre [10], Beirow et al [11], again Chan and Ewins [12], and Honisch et al [13] based on measured or preset blade frequency mistuning. However, normally the maxi mum mistuned forced response remains far below this limit since it is connected to a couple of assumptions such as that aero-elastic couplings of the blades are not considered.…”

Section: Introductionmentioning

confidence: 98%

Optimization-Aided Forced Response Analysis of a Mistuned Compressor Blisk

Beirow

Giersch

Kühhorn

et al. 2014

Journal of Engineering for Gas Turbines and Power

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The forced response of the first rotor of an engine 3E (technology program) (ESE)-type high pressure compressor (HPC) blisk is analyzed with regard to varying mistuning, varying engine order (EO) excitations and the consideration of aero-elastic effects. For that purpose, subset of nominal system modes (SNM)-based reduced order models are used in which the disk remains unchanged while the Young's modulus of each blade is used to define experimentally adjusted as well as intentional mistuning patterns. The aer odynamic influence coefficient (AIC) technique is employed to model aero-elastic interac tions. Furthermore, based on optimization analyses and depending on the exciting EO and aerodynamic influences it is searched for the worst as well as the best mistuning dis tributions with respect to the maximum blade displacement. Genetic algorithms using blade stiffness variations as vector o f design variables and the maximum blade displace ment as objective function are applied. An allowed limit of the blades' Young's modulus standard deviation is formulated as secondary condition. In particular, the question is addressed if and how far the aero-elastic impact, mainly causing aerodynamic damping, combined with mistuning can even yield a reduction of the forced response compared to the ideally tuned blisk. It is shown that the strong dependence of the aerodynamic damp ing on the interblade phase angle is the main driver for a possible response attenuation considering the fundamental blade mode. The results of the optimization analyses are compared to the forced response due to real, experimentally determined frequency mis tuning as well as intentional mistuning. Journal of Engineering for Gas Turbines and PowerJ o u rn a l o f E n g in e erin g fo r G as T u rb in es and Pow er JANUARY 2015, Vol. 137 / 0 12 50 4-9

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“…The blisk is a new-style key component of aero-engines, which rotor blade is integrated with the wheel disc. Compared to traditional blades and disk systems, the blisk has more advantages, including the lower weight, simple structure, higher reliability, long-service life and excellent reliability [1][2][3]. Therefore, the blisk has been widely utilized for modern high performance aero-engines.…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective Parameter Optimization for Disc Milling Process of Titanium Alloy Blisk Channels

Shi

2019

Symmetry

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The blisk has been widely used in modern high performance aero-engines of high thrust-weight ratio. Disc milling process provides a reliable way to improve the efficiency of the blisk milling. The process parameters of disc milling have crucial effects on the milling efficiency and physical property of blisk. In this paper, material removal rate, cutter life and thickness of residual stress layer are regarded as optimization targets the key process parameters such as spindle speed, cutting depth and feed speed are optimized. Based on the grey relational analysis, the multi-objective optimization problem is transformed into a single objective optimization problem. At the same time, the problem of non-symmetry influence of key process parameters on optimization targets can be solved. And the influence weight of material removal rate, cutter life and thickness of residual stress layer on the grey relational grade (GRG) are calculated according to principal component analysis. The second order prediction model of GRA is developed by response surface method. On the basis of verifying the accuracy of the model, the influence mechanism of the process parameters coupling on the gray correlation degree is analyzed the optimal process parameter combination is obtained as spindle speed with 81.92 rpm, cutting depth with 5.88 mm and feed rate with 66.0823 mm/min. The experimental research show that the optimal process parameter combination can effectively improve the material removal rate and cutter life and reduce the thickness of residual stress layer.

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Experimental and Numerical Analyses of Radial Turbine Blisks With Regard to Mistuning

Cited by 13 publications

References 14 publications

Model update and validation of a mistuned high-pressure compressor blisk

Model update and validation of a mistuned high-pressure compressor blisk

Optimization-Aided Forced Response Analysis of a Mistuned Compressor Blisk

Multi-Objective Parameter Optimization for Disc Milling Process of Titanium Alloy Blisk Channels

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