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TECHNICAL PAPERS

A Numerical Investigation of Boundary Layer Suction in Compound Lean Compressor Cascades

[+] Author and Article Information
Yanping Song

School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, Chinasongyanping@hit.edu.cn

Fu Chen, Jun Yang, Zhongqi Wang

School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

J. Turbomach 128(2), 357-366 (Feb 01, 2005) (10 pages) doi:10.1115/1.2162181 History: Received October 01, 2004; Revised February 01, 2005

This paper is focused on the numerical investigation of boundary layer suction (BLS) via a slot on the suction surfaces of two compound lean compressor cascades with large camber angles as well as a conventional straight compressor cascade for comparison. The objective of the investigation is to study the influence of boundary layer suction on the performance of compound lean compressor cascades, thus to discuss the possibility of the application of boundary layer suction to improve their performance. An extensive numerical study has been carried out under different spanwise lengths, different axial positions of the slots, and different suction flow rates. The results show that the total loss of all three cascades is reduced significantly by boundary layer suction, and the largest reduction occurs at the highest suction flow rate. The axial locations of the slot have little effect on the total loss of the three cascades, which means the slots are opened within the optimal axial range in this case. The slot opened along the full span is the best one to obtain the largest reduction in total loss for all three cascades due to the alleviation of flow separation in the corner between the endwall and the suction surface. Moreover, the flow turning is increased, and pressure rise at the rear of the passage is recovered along the whole blade height via boundary layer suction along the full span, enhancing the working range of the highly loaded compressor cascades.

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Stacking lines of compound lean cascades

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Figure 2

Comparison of total loss of the cascades

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Figure 3

Grid for cascade and slot

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Figure 4

Static pressure distribution on the blade surfaces

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Figure 5

Radial distribution of pitch-averaged loss coefficient

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Figure 6

Reduction in total loss with boundary layer suction

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Figure 7

Radial distribution of pitch-averaged loss coefficient

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Figure 8

Static pressure distribution on the blade surfaces

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Figure 9

Radial distribution of exit flow angle

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Figure 10

Static pressure contours on suction surface of the conventional straight blade (left side: L.E., right side: T.E.)

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Figure 11

Static pressure contours on suction surface of positive compound lean blade (left side: L.E., right side: T.E.)

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Figure 12

Static pressure contours on suction surface of negative compound lean blade (left side: L.E., right side: T.E.)

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Figure 13

Reduction in total loss with boundary layer suction

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Figure 14

Radial distribution of loss with boundary layer suction

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Figure 15

Loss contours at the exit of the straight cascade (left side: SS, right side: PS)

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Figure 16

Loss contours at the exit of the positive compound lean cascade (left side: SS, right side: PS)

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Figure 17

Loss contours at the exit of the negative compound lean cascade (left side: SS, right side: PS)

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Figure 18

Limiting streamline on suction surface of the straight cascade (left side: L.E., right side: T.E.)

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Figure 19

Limiting streamline on suction surface of the positive compound lean cascade (left side: L.E., right side: T.E.)

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Figure 20

Limiting streamline on suction surface of the negative compound lean cascade (left side: L.E., right side: T.E.)

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