The Effects of Some Design Parameters of an Isolated Rotor on Inlet Flow Distortions

Yocum, A. M.; Henderson, R. E.

doi:10.1115/1.3230219

Cited by 10 publications

(2 citation statements)

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“…The present investigations consider the combined effects of swirl and circumferential distortion. Most of the literature available till date on inlet flow distortion deals extensively on circumferential distortion alone (Colpin, 1979;Ehrich, 1957;Yocum and Henderson, 1980) and only recently few investigators have considered the combined effects of swirl and circumferential distortion. Flitcroft et al (1987) investigated the effect of inlet swirl on the propagation of total pressure distortion through a 3-stage fan without IGV.…”

Section: Clem Inlc7mentioning

confidence: 99%

Effect of Circumferential Inlet Flow Distortion and Swirl on the Flow Field of an Axial Flow Fan Stage

Viswanath

Govardhan

1996

Volume 1: Turbomachinery

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This paper reports a study of the combined effects of swirl and circumferential inlet flow distortion on the flow field of an axial flow fan stage. The study involves steady state measurements of the flow field at the rotor inlet, exit and the stator exit of the single stage axial flow fan subjected to circumferential inlet flow distortion and swirl. Flow field survey was done at two flow coefficients, namely, ϕ = 0.45 and ϕ = 0.285. The flow at the inlet to the rotor was measured using a three hole pressure probe and five hole pressure probes were used at the rotor and stator exits. The study indicated that at the design flow coefficient swirl had caused deterioration of the performance in addition to that caused by distortion. In addition, the attenuation of distortion was high in the presence of swirl.

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Section: Clem Inlc7mentioning

confidence: 99%

Effect of Circumferential Inlet Flow Distortion and Swirl on the Flow Field of an Axial Flow Fan Stage

Viswanath

Govardhan

1996

Volume 1: Turbomachinery

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“…It was concluded that an attenuation of 0.7 to 0.8 in velocity distortion is attainable and can be improved with lower reaction staging. In another study by Yocum and Henderson [8], it was shown that the attenuation of distortion as it passes through the rotor is a function of the blade stagger angle and the ratio of the rotor blade spacing to the distortion wave length. Plourde [9] concluded from his studies in a multistage compressor that the overall attenuation of both total pressure distortion and axial velocity distortion is dependent on the slope of the compressor characteristics.…”

Section: Introductionmentioning

confidence: 98%

Propagation of Different Types of Inflow Distortions through a Contra Rotating Fan Stage

Mistry

Pradeep

2015

International Journal of Turbo &Amp; Jet-Engines

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This paper aims to explain the propagation of different types of inflow distortions through a contra rotating fan stage. Inflow distortions like circumferential, radial and complex distortions were artificially generated using meshes of different porosities. The overall effects of these distortions are determined in the terms of the fan performance map. It is attempted to explain the propagation of inflow distortion using distortion descriptors like circumferential intensity, circumferential extent and radial intensity at the design mass flow rate. These are described for different speed combinations of both the rotors at the inlet, the exit of rotor-1 and at the exit of rotor-2. It is important to observe here that even for purely circumferential inflow distortion, the distortion does not remain purely circumferential, rather it propagates both circumferentially and radially along the stage. For the hub-strong complex inflow distortion, the higher magnitude of circumferential intensity and circumferential extent at the exit of rotor-1 clearly indicates the strong distortion effect that leads to poor performance of the stage amongst all distortion configurations studied. With radial inflow distortion, the radial redistribution of the flow at the exit of rotor-1 plays an important role in the performance of the rotor-2 and thereby for the stage.

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Investigations on an axial flow fan stage subjected to circumferential inlet flow distortion and swirl

Govardhan

Viswanath

1997

J. of Therm. Sci.

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I n v e s t i g a t i o n s on anA x i a l F l o w Fan S t a g e s u b j e c t e d to C i r c u m f e r e n t i a l Inlet F l o w D i s t o r t i o n and Swirl M. G o v a r d h a n K. V i s w a n~t h T h e r m a l T u r b o m a c h i n e s L a b o r a t o r y , D e p a r t m e n t of M e c h a n i c a l E n g i n e e r i n g , I n d i a n I n s t i t u t e of Technology, M a d r a s 600 036, I n d i aThe combined effects of swirl and circumferential inlet flow distortion on the flow field of an axial flow fan stage are reported in this paper. The study involves measurements at the inlet of the rotor and exit of the rotor and stator at design and off design flow conditions. The study indicated that at the design flow condition, swirl had caused deterioration of the performance in addition to that caused by distortion. Prcssure rise imparted in the distortion zone is higher than in the free zone. The attenuation of distortion is high in the presence of swirl.

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The Effects of Some Design Parameters of an Isolated Rotor on Inlet Flow Distortions

Cited by 10 publications

References 0 publications

Effect of Circumferential Inlet Flow Distortion and Swirl on the Flow Field of an Axial Flow Fan Stage

Effect of Circumferential Inlet Flow Distortion and Swirl on the Flow Field of an Axial Flow Fan Stage

Propagation of Different Types of Inflow Distortions through a Contra Rotating Fan Stage

Investigations on an axial flow fan stage subjected to circumferential inlet flow distortion and swirl

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