Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor

Suder, Kenneth L.; Celestina, Mark L.

doi:10.1115/1.2836629

Cited by 168 publications

(67 citation statements)

References 13 publications

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“…As already shown from particle traces passing through the tip clearance, leakage (Gerolymos andVallet, 1999, Suder andCelestina, 1996). As already shown from particle traces passing through the tip clearance, leakage (Gerolymos andVallet, 1999, Suder andCelestina, 1996).…”

Section: Tip Leakage Flow At Peak Efficiency Operating Pointsupporting

confidence: 58%

Effects of Shock-Wave on Flow Structure in Tip Region of Transonic Compressor Rotor

Park¹,

Chung²,

Baek³

2003

International Journal of Turbo and Jet Engines

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It is known that tip clearance flows reduce the pressure rise, flow range and efficiency of turbomachinery. So, a clear understanding about flow fields in the tip region is needed to efficiently design the turbomachinery. In the present paper, the Navier-Stokes code with the proper treatment of the boundary conditions has been developed to analyze the threedimensional steady viscous flow fields in the transonic rotating blades and a numerical study has been conducted to investigate the detailed flow physics in the tip region of transonic rotor, NASA Rotor 67. The computational results in the tip region of transonic rotor show the leakage vortices, leakage flow from pressure side to suction side and their interaction with a shock. Depending on the operating conditions, load distributions and the position of shock-wave on the blade surface are very different close to the blade tip of transonic compressor rotor. It is shown that the load distribution and the shock-wave position close to blade tip have great effects on the starting position of leakage vortex and direction of leakage flow. peak efficiency Experiment Calculation choke J I L j L j Ι-Ο.92 0.94 0.96 0.98 Mass flow rate/Mass flow rate at choke 1 ιnear stall Experiment Calculation J I L. J ' ' J_ J I L 0.92 0.94 0.96 0.98

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Section: Tip Leakage Flow At Peak Efficiency Operating Pointsupporting

confidence: 58%

Effects of Shock-Wave on Flow Structure in Tip Region of Transonic Compressor Rotor

Park¹,

Chung²,

Baek³

2003

International Journal of Turbo and Jet Engines

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“…Further details of the flow in the compressor are provided by who showed a remarkable dependence of the performance on the fine detail of the leading edge geometry and roughness, and by Suder & Celestina (1994) who studied the tip leakage flow both experimentally and computationally. Further details of the flow in the compressor are provided by who showed a remarkable dependence of the performance on the fine detail of the leading edge geometry and roughness, and by Suder & Celestina (1994) who studied the tip leakage flow both experimentally and computationally.…”

Section: T E S T C a S E D E T A I L Smentioning

confidence: 99%

Lessons from rotor 37

Denton

1997

J. of Therm. Sci.

135

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NASA rotor 37 was used as a 'blind' test case for turbomachinery CFD by the Turbomachinery Committee of the IGTI. The rotor is a transonic compressor with a tip speed of 454 m/s (1500 ft/s) and a relatively high pressure ratio "of 2.1. It was tested in isolation with a circumferentially uniform inlet flow so that the flow through it should be steady apart from any effects of passage to passage geometry variation and mechanical vibration. As such it represents the simplest possible type of test for thrcc dimensional turbomachinery flow solvers. However, the rotor still presents a real challenge to 3D viscous flow solvers because the shock wave-boundary layer interaction is strong and the effects of viscosity are dominant in determining the flow deviation and hence the pressure ratio. Eleven 'blind' solutions were submitted and in addition a 'non-blind' solution was used to prepare for the exercise. This paper reviews the flow in the test case and the comparisons of the CFD solutions with the test data. Lessons for both the Flow Physics in transonic fans and for the application of CFD to such machines are pointed out. K e y w o r d s : t r a n s o n i c c o m p r e s s o r r o t o r , s h o c k w a v e -b o u n d a r y l a y e r i n t e r a t i o n ,

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“…The rotor aspect ratio is 1.19 and the hub / tip radius ratio is 0.70. The rotor tip clearance at design speed is approximately 0.40 mm, corresponding to 0.5% of inlet span and 0.7% of exit span, see Suder and Celestina, 1994. The measurements were performed in the single stage transonic test facility at the NASA Lewis…”

Section: Introductionmentioning

confidence: 99%

Numerical Transonic Flow Field Predictions for NASA Compressor Rotor 37

Dalbert

Wiss

1995

Volume 1: Turbomachinery

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Flow field calculations of the NASA transonic axial compressor Rotor 37 are presented. These were obtained by the two commercially available 3D Navier Stokes-codes BTOB3D and TASCflow using different turbulence models, i.e. Baldwin-Lomax and k -E. Some of the results were submitted to the CFD code assessment exercise organized in 1994 by the Turbomachinery Committee of the ASME, where a number of "blind" CFD predictions were compared against previously unknown experimental data taken at the NASA Lewis Research Center. The objective of these calculations was to use the codes in the same way as they are generally used by experienced engineers for standard industrial design tasks. Thus, the effort involved in grid generation, flow simulation runs and postprocessing was subject to the usual limitations in computer resources as well as a stringent observation of cost-effectiveness (manpower and time available). With both codes, two sets of calculations were carried out: BTOB3D with two different tip clearances and TASCflow with a uniform and a spanwise varying outlet static pressure. Generally, the results of both codes show good agreement with respect to the measured overall performance characteristics and averaged spanwise distributions. In particular, the TASCflow solutions display high prediction accuracy in some local details of the flow field while in the BTOB3D code, boundary effects seem to mix out the flow significantly.The solution strategies employed as well as the reasons for certain discrepancies between computations and measurements are discussed. NOMENCLATUREfi massflow rhmax maximum measured massflow p pressure z axial coordinate Indices choke calculated choking conditions in inlet out outlet total conditions

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Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor

Cited by 168 publications

References 13 publications

Effects of Shock-Wave on Flow Structure in Tip Region of Transonic Compressor Rotor

Effects of Shock-Wave on Flow Structure in Tip Region of Transonic Compressor Rotor

Lessons from rotor 37

Numerical Transonic Flow Field Predictions for NASA Compressor Rotor 37

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