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Research Papers

An Analytical Model for Boundary Layer Control Via Steady Blowing and Its Application to NACA-65-410 Cascade

[+] Author and Article Information
Mehmet N. Sarimurat

Mechanical and Aerospace
Engineering Department,
Syracuse University,
Syracuse, NY 13244
e-mail: mnsarimu@syr.edu

Thong Q. Dang

Professor
Mechanical and Aerospace
Engineering Department,
Syracuse University,
Syracuse, NY 13244
e-mail: tqdang@syr.edu

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 7, 2013; final manuscript received August 4, 2013; published online November 21, 2013. Editor: Ronald Bunker.

J. Turbomach 136(6), 061011 (Nov 21, 2013) (10 pages) Paper No: TURBO-13-1139; doi: 10.1115/1.4025585 History: Received July 07, 2013; Revised August 04, 2013

In this paper, boundary-layer flow-control technique via steady blowing for low-speed compressor cascade applications is investigated using an analytical model based on the integral method and computational fluid dynamics (CFD). The integral method is developed and used to investigate the effect of the momentum, the velocity magnitude, and the angle of the blowing flow on the behavior of the boundary layer. It is found that the change in the boundary layer momentum thickness across the blowing location is a linear function of the blown-flow momentum coefficient and a decaying function of the blown-flow velocity ratio. For the case when the size of the blowing slot and the velocity magnitude of the blown-flow are kept constant and the blowing mass flow rate is increased by increasing the blowing angle, there is an “optimum” blowing angle that maximizes the benefit of the boundary layer blowing. This angle increases with increasing velocity ratio and reaches an asymptotic value of 45 deg. According to the model, the change in the momentum thickness across the blowing location is conveyed exponentially downstream; thus, a small change in the momentum thickness due to flow blowing can have significant effect downstream. The developed model is applied to the NACA-65-410 low speed cascade using CFD, and good agreement between theory and CFD is obtained.

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References

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Figures

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Fig. 1

Control volume for analysis of boundary layer with flow blowing (modified from Ref. [12])

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Fig. 2

Change in momentum thickness across blowing location with varying momentum coefficient

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Fig. 3

Change in momentum thickness across blowing location with varying velocity ratio

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Fig. 5

Optimum blowing angle as a function of velocity ratio

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Fig. 6

Change in momentum thickness across blowing location with varying blowing angle for the case where both velocity ratio and momentum coefficient are constant

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Fig. 7

Effect of flow blowing on boundary layer growth

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Fig. 8

NACA-65-410 cascade notation

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Fig. 9

Mesh and boundary conditions for NACA-65-410 CFD simulation

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Fig. 10

Performance prediction of NACA-65-410 without boundary layer blowing: (a) v2f, (b) Spalart–Allmaras, (c) standard k-ε with enhanced wall treatment, (d) standard k-ω

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Fig. 11

Pathlines around NACA-65-410 cascade without boundary layer blowing

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Fig. 12

Mesh and boundary conditions with flush boundary

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Fig. 13

Change in momentum thickness with varying momentum coefficient (uB/ui = 2, α = 35 deg)

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Fig. 14

Change in momentum thickness with varying velocity ratio (Cμ = 0.024, α = 35 deg)

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Fig. 15

Change in momentum thickness with varying blowing angle (uB/ui = 2, Δx/c = 0.0052)

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Fig. 16

Change in momentum thickness with varying blowing angle (uB/ui = 2, Cμ = 0.024)

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Fig. 17

Control volume for analysis of loss generation

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Fig. 18

Pathlines around NACA-65-410 cascade showing effect of blowing

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