Experimental Investigations on Highly Loaded Compressor Airfoils With Active Flow Control Under Non-Steady Flow Conditions in a 3D-Annular Low-Speed Cascade

Brück, Christian; Tiedemann, Christine; Peitsch, Dieter

doi:10.1115/gt2016-56891

Cited by 7 publications

(5 citation statements)

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“…Gbadebo [7] showed that a variation in incidence angle led to changes in size and characteristics of those vortices. As the pitch-to-chord ratio in the annular test rig is smaller on the hub side than at the tip, an asymmetrical occurrence of the corner vortices is observed as shown by Brück [8]. Utilizing different means of flow control has shown that the blade passage losses can be successfully reduced [9].…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Investigations on Optimized 3D Compressor Airfoils

Mihalyovics

Brück

Peitsch

et al. 2018

Volume 2A: Turbomachinery

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The objective of the presented work is to perform numerical and experimental studies on compressor stators. This paper presents the modification of a baseline stator design using numerical optimization resulting in a new 3D stator. The Rolls Royce in-house compressible flow solver HYDRA was employed to predict the 3D flow, solving the steady RANS equations with the Spalart-Allmaras turbulence model, and its corresponding discrete adjoint solver. The performance gradients with respect to the input design parameters were used to optimize the stator blade with respect to the total pressure loss over a prescribed incidence range, while additionally minimizing the flow deviation from the axial direction at the stator exit. Non-uniform profile boundary conditions, being derived from the experimental measurements, have been defined at the inlet of the CFD domain. The presented results show a remarkable decrease in the axial exit flow angle deviation and a minor decrease in the total pressure loss. Experiments were conducted on two compressor blade sets investigating the three-dimensional flow in an annular compressor stator cascade. Comparing the baseline flow of the 42° turning stator shows that the optimized stator design minimizes the secondary flow phenomena. The experimental investigation discusses the impact of steady flow conditions on each stator design while focusing on the comparison of the 3D optimized design to the baseline case. The flow conditions were investigated using five-hole probe pressure measurements in the wake of the blades. Furthermore, oil-flow visualization was applied to characterize flow phenomena. These experimental results are compared with the CFD calculations.

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Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Investigations on Optimized 3D Compressor Airfoils

Mihalyovics

Brück

Peitsch

et al. 2018

Volume 2A: Turbomachinery

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“…The respective positions where c p,T E,a f c has been measured is marked with a red circle in Figure 3. These positions have been chosen because the maximum static pressure at the TE is observed there, as shown in [25,26]. For the actuated case the maximum increase in pressure occurs at the same location.…”

Section: Comparison Of Active Flow Control Resultsmentioning

confidence: 99%

“…low speed, open circuit wind tunnel operated at the flight propulsion laboratory of TUB was used for the annular cascade experiments.Figure 1bshows a schematic depiction of the test section, introduced by Brück et al[21].The diameter of the casing of the test section measures 0.6 m. In order to create an inflow angle to the annular cascade of β 1 = 60 • at midspan 19 variable inlet guide vanes (VIGV s) produce the swirl needed for the stator inlet conditions.…”

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confidence: 99%

A Qualitative Comparison of Unsteady Operated Compressor Stator Cascades with Active Flow Control

Staats

Mihalyovics

Peitsch

2018

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Currently, the influence and scaling of active flow control by means of pulsed jet actuators applied to a two-dimensional compressor cascade flow are well understood. However, the presence of a transverse pressure gradient in a 3D annular cascade configuration causes additional effects which need a more profound consideration. The objective of this study is to compare results from the linear cascade setup to the annular one and transfer the AFC technology respectively.

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“…Since its radial scale exceeds half-span, more flow will pass through the opposite side at the given inlet Mach number and hence the upper endwall region will not suffer from sever flow separation and passage flow is not symmetric. It is necessary to note that this asymmetric flow phenomenon is a typical flow feature for a highly loaded low aspect ratio annular stator 26 and might also be observed in a planar cascade in some extreme cases. 27 To tell the truth, the outlet aerodynamic parameters distribution in this case is hard to satisfy the engineering applications.…”

Section: Grid Independency Studymentioning

confidence: 96%

A combination application of tandem blade and endwall boundary layer suction in a highly loaded aspirated compressor outlet vane

Zhang

Wang

2017

Proceedings of the Institution of Mechanical Engineers, Part A:

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Aspirated compressor is a promising design concept to enhance the power density of the compression system; however, with regard to the rear stages of multistage aspirated compressor, the blade is fairly thin. Limited by the mechanical constraints, it seems impractical to implement the boundary layer suction on the blade suction surface. So the question arising is can we replace the blade suction surface with other feasible flow control methods without implementing extra device on the blade? To address this issue, a compound flow control method, composed of the endwall boundary layer suction and tandem blade, is proposed. The design philosophy is to utilize the EBLS to suppress the three-dimensional corner stall while to use the tandem blade to control the two-dimensional airfoil flow separation. The endwall boundary layer suction is barely implemented in the forward blade, whereas the corner flow in the rear blade is restrained by the flow through the gap between the forward and rear blades. The preliminary implement strategy of the compound flow control was presented and then applied in the design of a highly loaded aspirated compressor outlet vane. Three-dimensional numerical simulations were carried out to validate its effectiveness with different inlet boundary layer distributions. Both flow fields in the outlet vane and its loss characteristics were analyzed. The results show that, by applying the compound flow control, the outlet vane could not only achieve an aggressive loading without incurring large-scale separation at the design point but also have a considerable available incidence range. Due to the implement of the endwall boundary layer suction, the tandem blade can bring out its full potential in the two-dimensional flow control. Moreover, owing to the flow through the gap of the forward and rear blades, the aspiration flow rate required for the suppression of the three-dimensional corner stall can be reduced.

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Experimental Investigations on Highly Loaded Compressor Airfoils With Active Flow Control Under Non-Steady Flow Conditions in a 3D-Annular Low-Speed Cascade

Cited by 7 publications

References 0 publications

Numerical and Experimental Investigations on Optimized 3D Compressor Airfoils

Numerical and Experimental Investigations on Optimized 3D Compressor Airfoils

A Qualitative Comparison of Unsteady Operated Compressor Stator Cascades with Active Flow Control

A combination application of tandem blade and endwall boundary layer suction in a highly loaded aspirated compressor outlet vane

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