Physical Explanations of Tip Leakage Flow Field in an Axial Compressor Rotor

Inoue, M.; Furukawa, Masato; Saiki, Keitarou; Yamada, Kazutoyo

doi:10.1115/98-gt-091

Cited by 15 publications

(8 citation statements)

References 25 publications

(37 reference statements)

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“…Kang and Hirsch [6j experimentally observed that the flow in the linear cascade tip had a multiple vortex structure, consisting of the tip leakage vortex, the tip separation vortex and the secondary vortex. Inoue et al [7][8][9] studied the influence of the tip clearance size on the tip leakage vortex in an isolated rotor. Foley and Ivey [~°] observed that the leakage jet from both stators and rotors rolled up into a vortex downstream of Received June 2, 2005 Hongwu ZHANG: Associate Professor their respective blade rows in the third stage of a low-speed four-stage axial compressor.…”

Section: Introduction Backgroundmentioning

confidence: 99%

Unsteady tip clearance flow in an isolated axial compressor rotor

et al. 2005

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The paper investigates effects of operating conditions, tip clearance sizes and external unsteady excitations on the unsteady tip clearance flow in an isolated axial compressor rotor by unsteady 3D Navier-Stokes simulations. The results show that the unsteady tip clearance vortex takes a periodic flow behavior in the rotor tip region. With the decrease of the flow coefficient, the unsteady tip clearance vortex is enhanced and its frequency becomes lower. A larger tip clearance size can cause bigger unsteady fluctuation amplitude and a lower fluctuation frequency of the tip clearance vortex at the near stall operating condition. The unsteady excitation with the natural frequency of the tip clearance vortex can enhance the unsteadiness of the tip clearance vortex and improve the overall rotor performance. The frequency of the unsteady tip clearance vortex is independent of external unsteady excitations with different frequencies.

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Section: Introduction Backgroundmentioning

confidence: 99%

Unsteady tip clearance flow in an isolated axial compressor rotor

et al. 2005

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“…However, considering the structural strength and the cost of air entrainment, short slot suction scheme and smaller suction flow are the goals we want to pursue. According to the research viewpoints of Storer and Inoue et al (Storer et al 1990;Inoue et al 1989Inoue et al , 1998, the trajectory of leakage vortex near the stator blade tip coincided with the line of the inclined channel connecting the local minimum static pressure on hub endwall. In addition, the minimum static pressure point on the hub endwall was considered as the onset position of leakage vortex.…”

Section: Effect Of the Endwall Suction On The Compressor Performance mentioning

confidence: 95%

Numerical Research on the Impact of Axial Position of Endwall Suction Slot on Tip Leakage Flow

Zhang

Liu

Rehman

et al. 2020

JAFM

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In order to reduce the adverse effect of the tip leakage flow of cantilever stator on compressor performance, the impact of the axial position of endwall streamwise suction slot on tip leakage flow was numerically studied. The study on the overall performance of the compressor and the details of the flow field near the stator end region with and without suction showed that all suction schemes could weaken the tip leakage flow intensity to a certain extent, and the flow control effect was gradually enhanced with the increase of the suction flow rate. In the case of small suction flow rate, for example, 0.5%, the short slot schemes can improve the overall efficiency of the compressor by about 0.5%, which is more advantageous than the long slot scheme, and the overall efficiency improvement of the latter is about 0.3%. The advantage of the long slot scheme in flow control is reflected in the case of large suction flow rate, that is, 1.0%, which may improve the overall efficiency of the compressor by about 0.96%. The axial position of suction slot has a significant influence on flow control effect of the tip leakage flow. Compared with the downstream suction, which only modified the flow field by reducing the blocking effect generated by tip flow vortex, the upstream suction could better control the tip leakage flow by restraining the development of the initial stage of the leakage vortex. Besides, the endwall suction scheme with a full chord length slot has the greatest impact on the passage vortex, its effect on modifying the flow field near the end zone was determined by the combinatorial action of the enhancement of the passage vortex and the attenuation of the leakage vortex.

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“…This method has been successfully used recently to Figure 10. Trajectories of the leakage vortex cores identified using a semi-analytical method 10 study the tip leakage vortices (Inoue et al, 1998;Furukawa et aL, 1998). bout et aL (1998) have been able to identify the trajectory of a vortex core visually using this method to explain the onset of the tip-leakage vortex.…”

Section: Vortex Core Trajectoriesmentioning

confidence: 99%

“…bout et aL (1998) have been able to identify the trajectory of a vortex core visually using this method to explain the onset of the tip-leakage vortex. Furukawa et al (1998) have explained the role of the vortex breakdown in rotor performance near the stall condition. This method is similar to a critical-point analysis (e.g., Perry and Chong, 1987) except that it uses a semi-analytical streamline construction, which assumes that the local velocity field can be linearly parametrized in a tetrahedral computational cell.…”

Section: Vortex Core Trajectoriesmentioning

confidence: 99%

The Flow Field in the Tip Clearance Region of an Axial Compressor Rotor

Arima

Shirotori

Yamaguchi

1999

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

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A three-dimensional, Reynolds-averaged, compressible Navier-Stokes analysis (using a multi-block grid with the grid embedded in the tip-clearance space) has been developed to study the tip-clearance flow of an axial compressor rotor. A low-Reynolds number k-ε model have been used to reproduce the effects of turbulence. In order to assess the effect of the tip-clearance-grid treatment on prediction for the tip-clearance flow, calculations using a single-block grid (pinched grid topology) and multi-block grid (embedded grid topology) have been performed to calculate the flow field of NASA Rotor 37. The results are compared with experimental data. It has been found that both the single-block and multi-block approaches give a good agreement with the experimental data regarding the overall performance map of the rotor. For the prediction of the spanwise distributions of averaged aerodynamic properties downstream of the rotor, however, the orderly grid over the blade tip associated with the embedded grid has produced accurate predictions particularly from 40% to 80% span. In order to investigate the tip-clearance flow for different operating conditions, calculations have been performed for conditions at 100% (transonic inflow condition) and 60% (subsonic inflow condition) of the design point speed. Computed limiting streamlines at the blade tip surface and particle traces released from the tip-clearance have been used to study the tip-clearance flow. At the 100% speed, both separation and reattachment lines have been observed and a separation bubble occurs. At the 60% speed, the separation line shifts to the blade pressure side and the reattachment line can be partly observed near the leading edge of the blade tip surface. In order to investigate the interaction of the leakage vortex from the tip clearance with the main flow, the computed secondary flows on the cross-flow sections have been analyzed at the 100% and the 60% speeds. At the 100% speed, the vortex core apparently increases in size, as it moves downstream. At 60% speed, the second vortex, first reported by Suder and Celestina in 1994, is barely observable. Furthermore, the trajectory of vortex core identified using a semi-analytical method has also been used to study the vortex motion in the flow field near the blade tip.

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Physical Explanations of Tip Leakage Flow Field in an Axial Compressor Rotor

Cited by 15 publications

References 25 publications

Unsteady tip clearance flow in an isolated axial compressor rotor

Unsteady tip clearance flow in an isolated axial compressor rotor

Numerical Research on the Impact of Axial Position of Endwall Suction Slot on Tip Leakage Flow

The Flow Field in the Tip Clearance Region of an Axial Compressor Rotor

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