Design of Experiments and Numerical Simulation of Deteriorated High Pressure Compressor Airfoils

Reitz, Gerald; Schlange, Stephan; Friedrichs, Jens

doi:10.1115/gt2016-56024

Cited by 9 publications

(15 citation statements)

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“…In order to rank the effect of coupled geometric properties, a sensitivity analysis was done by means of a DoE. The work of Reitz et al [5] was extended by focusing on circumferentially-coupled deteriorated blades, their interaction, and effects considering three different operating points. Figure 2 shows the non-dimensional pressure distribution for three operating points at 85% blade height compared to their complementary full 3D simulations.…”

Section: Design Of Experimentsmentioning

confidence: 99%

“…In terms of the aerodynamic effects of geometric variances, the 85% profile section is representative. Reitz et al [5] investigated a full 3D blade. With respect to this study, the results of the 85% profile section presented here are comparable.…”

Section: Design Of Experimentsmentioning

confidence: 99%

“…Here the error reached 0.1%. The quadratic interpolation method is best suited for the problem definition because it can be assumed that relations between geometric parameters and aerodynamic flow field cannot be mapped with a linear approach (Reitz et al [5]).…”

Section: Validation Of Meta-modelmentioning

confidence: 99%

“…A sensitivity investigation on the influence of deterioration on high-pressure compressor performance was done by Reitz et al [5]. They analyzed a deteriorated HPC front stage by means of a design of experiments (DoE) at cruise condition.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, a DoE was done to identify the geometric properties leading to a change in performance. The DoE was performed by an in-house tool, introduced by Reitz et al [5]. The data base of this investigation was based on ten first-stage HPC BLISKs with 26 blades each.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Sensitivity Analysis of BLISK Airfoil Wear

Kellersmann

Reitz

Friedrichs

2018

IJTPP

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The decreasing performance of jet engines during operation is a major concern for airlines and maintenance companies. Among other effects, the erosion of high-pressure compressor (HPC) blades is a critical one and leads to a changed aerodynamic behavior, and therefore to a change in performance. The maintenance of BLISKs (blade-integrated-disks) is especially challenging because the blade arrangement cannot be changed and individual blades cannot be replaced. Thus, coupled deteriorated blades have a complex aerodynamic behavior which can have a stronger influence on compressor performance than a conventional HPC. To ensure effective maintenance for BLISKs, the impact of coupled misshaped blades are the key factor. The present study addresses these effects on the aerodynamic performance of a first-stage BLISK of a high-pressure compressor. Therefore, a design of experiments (DoE) is done to identify the geometric properties which lead to a reduction in performance. It is shown that the effect of coupled variances is dependent on the operating point. Based on the DoE analysis, the thickness-related parameters, the stagger angle, and the max. profile camber as coupled parameters are identified as the most important parameters for all operating points.

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Section: Design Of Experimentsmentioning

confidence: 99%

Section: Design Of Experimentsmentioning

confidence: 99%

Section: Validation Of Meta-modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Sensitivity Analysis of BLISK Airfoil Wear

Kellersmann

Reitz

Friedrichs

2018

IJTPP

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Comparison of sensitivities to geometrical properties of front and aft high pressure compressor stages

et al. 2018

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The Effect of Manufacturing Variations on Unsteady Interaction in a Transonic Turbine

Clark

Beck²,

Kaszynski

et al. 2018

Journal of Turbomachinery

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This effort focuses on the comparison of unsteadiness due to as-measured turbine blades in a transonic turbine to that obtained with blueprint geometries via computational fluid dynamics (CFD). A Reynolds-averaged Navier–Stokes flow solver with the two-equation Wilcox turbulence model is used as the numerical analysis tool for comparison between the blueprint geometries and as-manufactured geometries obtained from a structured light optical measurement system. The nominal turbine CFD grid data defined for analysis of the blueprint blade were geometrically modified to reflect as-manufactured turbine blades using an established mesh metamorphosis algorithm. The approach uses a modified neural network to iteratively update the source mesh to the target mesh. In this case, the source is the interior CFD surface grid while the target is the surface blade geometry obtained from the optical scanner. Nodes interior to the CFD surface were updated using a modified iterative spring analogy to avoid grid corruption when matching as-manufactured part geometry. This approach avoids the tedious manual approach of regenerating the CFD grid and does not rely on geometry obtained from coordinate measurement machine (CMM) sections, but rather a point cloud representing the entirety of the turbine blade. Surface pressure traces and the discrete Fourier transforms (DFT) thereof from numerical predictions of as-measured geometries are then compared both to blueprint predictions and to experimental measurements. The importance of incorporating as-measured geometries in analyses to explain deviations between numerical predictions of blueprint geometries and experimental results is readily apparent. Further analysis of every casting produced in the creation of the test turbine yields variations that one can expect in both aero-performance and unsteady loading as a consequence of manufacturing tolerances. Finally, the use of measured airfoil geometries to reduce the unsteady load on a target blade in a region of interest is successfully demonstrated.

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Design of Experiments and Numerical Simulation of Deteriorated High Pressure Compressor Airfoils

Cited by 9 publications

References 0 publications

Sensitivity Analysis of BLISK Airfoil Wear

Sensitivity Analysis of BLISK Airfoil Wear

Comparison of sensitivities to geometrical properties of front and aft high pressure compressor stages

The Effect of Manufacturing Variations on Unsteady Interaction in a Transonic Turbine

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