A parametric model for probabilistic analysis of turbine blades considering real geometric effects

Heinze, Kay; Meyer, Marcus; Scharfenstein, Jens; Voigt, Matthias; Vogeler, Konrad

doi:10.1007/s13272-013-0088-6

Cited by 17 publications

(9 citation statements)

References 24 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The ability to capture and recreate the geometry of manufactured blades in a numerical environment is essential for the Digital Twin. Suitable measurement methods include using a Coordinate Measuring Machine (CMM) (Garzon and Darmofal, 2003), structured-light scanning (Heinze et al, 2014), and computed tomography (Högner et al, 2017). Structured-light scanning is the method of choice as it produces tessellated point clouds, stereolithography (STL) meshes, with an accuracy of 8 − 27µm depending on the local curvature gradient (Kamenik et al, 2018).…”

Section: Methods II -Geometry Measurement and Recreation Methodsmentioning

confidence: 99%

The Required Aerodynamic Simulation Fidelity to Usefully Support a Gas Turbine Digital Twin for Manufacturing

Lee¹,

Dawes²,

Coull³

2020

Proceedings of Global Power &Amp; Propulsion Society

View full text Add to dashboard Cite

With the imminent digitalisation of the manufacturing processes of gas turbine components, a large volume of geometric data of as-manufactured parts is being generated. This geometric data can be used in aerodynamic simulations to predict component performance. Both the cost and accuracy of these simulations increase with their fidelity. To efficiently exploit Digital Twin technology, one must therefore understand how realistic the aerodynamic simulations need to be to give useful performance predictions. This paper considers this issue for a sample of scrapped high-pressure turbine rotor blades from a civil aero engine. The measured geometric data was used to build aerodynamic models of varying degrees of realism, ranging from quasithree-dimensional blade sections for an Euler solver to three-dimensional, multi-passage and multi-stage Reynolds-Averaged-Navier-Stokes models. The flow near the tip of these shrouded blades is sensitive to manufacturing variability and can switch between two quasi-stable horseshoe vortex modes. In general, capacity and exit flow angle can be adequately predicted by three-dimensional, single-passage calculations: averaging single-passage calculations gives a good prediction of the multi-passage behaviour. For efficiency and stage loading, the approach of averaging single-passage calculations is less accurate as the multi-passage behaviour requires an accurate prediction of the horseshoe vortex modes. Aerodynamic Simulation Hierarchy The aerodynamic environment of a turbine blade is complex and can only be captured using physics-based simulations. Computational Fluid Dynamics (CFD) tools that encompass a range of fidelities have been used by various published studies and they will be discussed here in the order of increasing fidelity. Considering the high volume of manufactured blades, rapid CFD tools like the Multiple blade Interacting Streamtube Euler Solver (MISES) (Drela, 1985) are attractive. MISES is a streamtube Euler solver coupled to an integral boundary layer code that is limited to quasi-three-dimensional (Q3D) blade sections. It has been used to assess compressor (Garzon

show abstract

Section: Methods II -Geometry Measurement and Recreation Methodsmentioning

confidence: 99%

The Required Aerodynamic Simulation Fidelity to Usefully Support a Gas Turbine Digital Twin for Manufacturing

Lee¹,

Dawes²,

Coull³

2020

Proceedings of Global Power &Amp; Propulsion Society

View full text Add to dashboard Cite

show abstract

“…Although the blades have been in service briefly with two different airlines and were taken from used, low-cycle engines, they essentially represent manufacturing variations. In a previous work, all blades were digitized using the scanning system GOM ATOS SO 4M, a high-resolution, structured-light 3D scanner [6]. Due to their significance for this study, some facts from this reference are repeated here: The measurement accuracy of the scan system according to the manufacturer is 5 µm, but previous internal investigations with a test specimen revealed that the real observed measurement accuracy is around 8 µm for planar surfaces and about 27 µm near strongly curved areas.…”

Section: B Optical Scans and Blade Variationsmentioning

confidence: 99%

“…[23] for PCA. Here, a reverse engineering process based on a set of 14 classical airfoil parameters, implemented in a tool called Blade2Parameter (B2P) developed at TU Dresden, is used [6]. Figure 5 depicts all 14 parameters applied to a turbine blade section.…”

Section: Parametric Construction Of Realistic Blade Modelsmentioning

confidence: 99%

“…The contribution of this paper relative to prior work is the incorporation of a previously developed parameterization method [2] and UQ workflow [6] into a coherent RDO workflow for turbine blades, which, to the best of our knowledge, is the first such heuristic to incorporate real variations of the entire blade shape. It is shown that artificially generated blades for UQ can recreate the stochastic performance of real scans and that the optimization effectively produces robust turbine blade designs.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Robust Turbine Blade Optimization in the Face of Real Geometric Variations

Kamenik

Voutchkov

Toal

et al. 2018

Journal of Propulsion and Power

Self Cite

View full text Add to dashboard Cite

show abstract

“…Recently, there has been an increasing interest in stochastic analysis, in which variations of the relevant parameters in real gas turbine blades are included. Besides the ideal configuration, simulations are performed which represent the behavior of the imperfect blade (Heinze et al , 2014). This leads to many calculations and even higher computational costs.…”

Section: Introductionmentioning

confidence: 99%

Efficient structural analysis of gas turbine blades

Rogge¹,

Berger²,

Pohle³

et al. 2018

AEAT

View full text Add to dashboard Cite

Purpose The purpose of this study a fast procedure for the structural analysis of gas turbine blades in aircraft engines. In this connection, investigations on the behavior of gas turbine blades concentrate on the analysis and evaluation of starting dynamics and fatigue strength. Besides, the influence of structural mistuning on the vibration characteristics of the single blade is analyzed and discussed. Design/methodology/approach A basic computation cycle is generated from a flight profile to describe the operating history of the gas turbine blade properly. Within an approximation approach for high-frequency vibrations, maximum vibration amplitudes are computed by superposition of stationary frequency responses by means of weighting functions. In addition, a two-way coupling approach determines the influence of structural mistuning on the vibration of a single blade. Fatigue strength of gas turbine blades is analyzed with a semi-analytical approach. The progressive damage analysis is based on MINER’s damage accumulation assuming a quasi-stable behavior of the structure. Findings The application to a gas turbine blade shows the computational capabilities of the approach presented. Structural characteristics are obtained by robust and stable computations using a detailed finite element model considering different load conditions. A high quality of results is realized while reducing the numerical costs significantly. Research limitations/implications The method used for analyzing the starting dynamics is based on the assumption of a quasi-static state. For structures with a sufficiently high stiffness, such as the gas turbine blades in the present work, this procedure is justified. The fatigue damage approach relies on the existence of a quasi-stable cyclic stress condition, which in general occurs for isotropic materials, as is the case for gas turbine blades. Practical implications Owing to the use of efficient analysis methods, a fast evaluation of the gas turbine blade within a stochastic analysis is feasible. Originality/value The fast numerical methods and the use of the full finite element model enable performing a structural analysis of any blade structure with a high quality of results.

show abstract

A parametric model for probabilistic analysis of turbine blades considering real geometric effects

Cited by 17 publications

References 24 publications

The Required Aerodynamic Simulation Fidelity to Usefully Support a Gas Turbine Digital Twin for Manufacturing

The Required Aerodynamic Simulation Fidelity to Usefully Support a Gas Turbine Digital Twin for Manufacturing

Robust Turbine Blade Optimization in the Face of Real Geometric Variations

Efficient structural analysis of gas turbine blades

Contact Info

Product

Resources

About