Transonic Axial Compressor Using Laser Anemometry and Unsteady Pressure Measurements

Dunker, R. J.; Hungenberg, H. G.

doi:10.2514/3.50841

Cited by 16 publications

(3 citation statements)

References 3 publications

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“…A typical transonic cascade (DFLVR) 26 is utilized to validate the numerical method. The design parameters of DFLVR are similar to the transonic cascade in this study.…”

Section: Cfd Validationsmentioning

confidence: 99%

Effect of combined boundary layer suction on the separation control in a highly loaded transonic compressor cascade

Li,

Mu,

Luo

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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A numerical investigation is conducted to explore the potential of combined slot suction in controlling the shock wave and flow separation in a transonic compressor cascade. The three slots in the combined scheme are arranged in different directions on the suction surface and endwall. The locations are determined by the shock wave and separation point in the baseline cascade. Based on these locations, two combined schemes and three single schemes are provided to explore the control mechanism. For each suction scheme, five bleed mass ratios are examined at the same inlet Mach number. The results suggested that the cascade throughflow loss could be decreased by three single schemes. However, the cascade performance is improved slightly or even deteriorated when the losses generated by the suction are considered. The key reasons are the local effects of single scheme and the opposite trend between corner stall and the suction surface separation. Both corner stall and the suction surface separation are eliminated by the combined scheme with two slots, and the maximum reduction in throughflow losses is 75%. The new corner separation evolved from the horseshoe vortex limited the performance of combined scheme. When the bleed mass ratio excided 5%, the combined scheme with three slots is better than the two slots scheme in loss control. The reason is the improved endwall boundary layer and the eliminated new corner separation. By inducing the horseshoe vortex into the slot, the interaction of the two endwall slots eliminates the new corner separation.

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“…A typical transonic cascade (DFLVR) 26 is utilized to validate the numerical method. The design parameters of DFLVR are similar to the transonic cascade in this study.…”

Section: Cfd Validationsmentioning

confidence: 99%

Effect of combined boundary layer suction on the separation control in a highly loaded transonic compressor cascade

Li,

Mu,

Luo

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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show abstract

“…The next example shows results from a two-dimensional, finite volume code using Jameson's scheme with streamtube thickness variation [18,19]. The geometry is a streamtube cut of the DFVLR rotor [20] in 89% span. Figure 9 shows the Mach number contours of the computed solution with the present treatment.…”

Section: Computed Examplesmentioning

confidence: 99%

Time-Split Inflow Boundary Treatment

Tong

1985

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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This paper describes a new non-reflective inflow treatment for viscous and inviscid internal flow calculations. The method approximates the multi-dimensional governing equations at the inflow boundary in a series of one-dimensional split equations. This treatment allows the artificial inflow boundary to be brought in just in front of the leading edge, while allowing upstream running waves to penetrate without significant reflection. Calculation examples of two dimensional inviscid internal flows are presented. Extension of the method to three-dimensional problems is also discussed.

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“…The aerodynamic design considerations and the various experimental investigations of the original stage are discussed in detail in reference [1] to [3].Therefore only a brief description of the main parameters will be presented in the following:…”

Section: Stage Design Considerationsmentioning

confidence: 99%

Redesign and Performance Analysis of a Transonic Axial Compressor Stator and Equivalent Plane Cascades With Subsonic Controlled Diffusion Blades

Dunker¹,

Rechter²,

Starken³

et al. 1983

Volume 1: Turbomachinery

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In order to verify a new controlled diffusion blade design concept, the stator of an existing transonic axial compressor stage was redesigned. Stator and equivalent cascade tests revealed the potential of such blades for a considerably higher aerodynamic loading than it has been applied up to now. The design procedure is described and the results of plane cascade and stage testing are submitted including performance analysis of both, cascade and stator blade sections, at design and off-design operating conditions. The blade profile shapes and cascade geometries were calculated by means of an inverse 2-dimensional method taking also into account the axial velocity density ratio (AVDR). This design concept is essentially based on prescribed blade pressure distributions which are optimized with respect to the blade boundary layer development. The flow phenomena are illustrated by means of loss and flow turning investigations, blade pressure distributions and laser velocimetry data. The test results reveal that the 2-D approach applied is quite promising for the 3-D stator blade design. Finally overall and blade element performance comparisons between the original NACA 65 profiled stator and the redesigned one demonstrate the favourable flow behaviour of the new stator as well as the great potential of the controlled diffusion blade concept.

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Transonic Axial Compressor Using Laser Anemometry and Unsteady Pressure Measurements

Cited by 16 publications

References 3 publications

Effect of combined boundary layer suction on the separation control in a highly loaded transonic compressor cascade

Effect of combined boundary layer suction on the separation control in a highly loaded transonic compressor cascade

Time-Split Inflow Boundary Treatment

Redesign and Performance Analysis of a Transonic Axial Compressor Stator and Equivalent Plane Cascades With Subsonic Controlled Diffusion Blades

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