Design and Testing of Two Supercritical Compressor Cascades

Rechter, H.; Schimming, Peter; Starken, H.

doi:10.1115/79-gt-11

Cited by 6 publications

(3 citation statements)

References 3 publications

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“…The agreement is satisfactory. This was also found for the two other cascades, in spite of some deviations in the leading edge regions due to inaccuracies of the inverse calculation method which have been discussed in detail in references [7] and [8].…”

Section: Test Resultssupporting

confidence: 69%

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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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Section: Test Resultssupporting

confidence: 69%

“…The blade pressure distributions were prescribed on the basis of the experience gained with the two former supercritical cascade designs SKG 1.3 and SKG 2.7 [7,8]. The SKG 2.7 cascade obtained the best agreement between measured and prescribed data.…”

Section: Design Proceduresmentioning

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

Self Cite

View full text Add to dashboard Cite

show abstract

“…Separating imaginary component and real component, following equations . In equation(2), R and I may be expressed by P -+6)1+s4-...51 4.5,-na4A1…”

mentioning

confidence: 99%

Similarity Law of Transonic Flow Fields Around Cascades

Zhou

Mengyu

Lin

1981

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

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In order to extend the usage range of a cascade having excellent aerodynamic performance, it is beneficial to investigate the similarity between different flow fields. Von Karman gave transonic similarity law of two-dimensional isolated airfoils many years ago. However, the law of cascades is still different from that of airfoils. This paper points out that, to guarantee similarity between two flow fields around cascades, it is necessary that five corresponding transonic similarity parameters must be kept equal. Also some examples have been presented in this paper for demonstration. They indicate that the similarity law will help us to obtain rapidly many similar transonic flow fields around cascades at different operating conditions from a known flow field around a given cascade.

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Inverse Design Calculations for Transonic Cascades

Wang

1985

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

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The computation methods of the inverse problem and several mixed aerodynamic problems for transonic cascades are presented. The calculations are completed directly on the physical plane by the stream function equation. The corresponding boundary conditions of these problems are transfered into the boundary conditions expressed by stream function with the help of the relations of the basic equations. The methods presented have a clear physical concept and use similar manners of iteration for different problems. The calculations of some examples for the transonic inverse problem indicate this method is very effective. An example is given of a shockless supercritical cascade designed successfuly by the transonic inverse code.

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Design and Testing of Two Supercritical Compressor Cascades

Cited by 6 publications

References 3 publications

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

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

Similarity Law of Transonic Flow Fields Around Cascades

Inverse Design Calculations for Transonic Cascades

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