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RESEARCH PAPERS

Aerodynamic Characteristics of Supercritical Outlet Guide Vanes at Low Reynolds Number Conditions

[+] Author and Article Information
Toyotaka Sonoda

Honda R&D Co. Ltd., Aircraft Engine R&D Center, 351-0193, Saitama, Japantoyotaka_sonoda@n.n.rd.honda.co.jp

Heinz-Adolf Schreiber

German Aerospace Center (DLR), Institute of Propulsion Technology, 51170 Köln, Germany

J. Turbomach 129(4), 694-704 (Aug 19, 2006) (11 pages) doi:10.1115/1.2720868 History: Received July 26, 2006; Revised August 19, 2006

As a part of an innovative aerodynamic design concept for a single stage low pressure turbine, a high turning outlet guide vane is required to remove the swirl from the hot gas. The airfoil of the vane is a highly loaded compressor airfoil that has to operate at very low Reynolds numbers (Re120,000). Recently published numerical design studies and experimental analysis on alternatively designed airfoils showed that blade profiles with an extreme front loaded pressure distribution are advantageous for low Reynolds number conditions. The advantage even holds true for an increased inlet Mach number at which the peak Mach number on the airfoils reaches and exceeds the critical conditions (Mss>1.0). This paper discusses the effect of the inlet Mach number and Reynolds number on the cascade performance for both a controlled diffusion airfoil (CDA) (called baseline) and a numerically optimized front loaded airfoil. The results show that it is advantageous to design the profile with a fairly steep pressure gradient immediately at the front part in order to promote early transition or to prevent too large laminar—even shock induced—separations with the risk of a bubble burst. Profile Mach number distributions and wake traverse data are presented for design and off-design conditions. The discussion of Mach number distributions and boundary layer behavior is supported by numerical results obtained from the blade-to-blade flow solver MISES.

Copyright © 2007 by American Society of Mechanical Engineers
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Figures

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Figure 1

Reynolds number effect on profile losses for subsonic compressor cascades

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Figure 2

Reduction of number of LP-turbine components in a small turbofan engine by using a highly loaded compressor airfoil as an outlet guide vane

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Figure 3

Baseline and optimized cascade at design condition

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Figure 4

DLR transonic cascade facility

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Figure 5

Effect of free-stream turbulence on total pressure losses at a low Reynolds number. Experimental results for (a) OGV-BASE and (b) OGV-ES.

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Figure 6

Total pressure losses as function of blade chord Reynolds number for M1=0.5, 0.6, and 0.7. Experimental results for OGV-BASE (top) and OGV-ES (bottom).

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Figure 7

Reynolds number effect on the incidence characteristic at M1=0.7. Experimental results for OGV-BASE (top) and OGV-ES (bottom).

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Figure 8

Mach number influence on losses for i=−6deg, i=0deg, and i=+1.5deg. Experiment (symbol) and MISES simulation (line).

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Figure 9

Comparison of MISES and experiment for low Reynolds number condition (Re=120,000)

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Figure 10

Simulated loss-incidence characteristics for M1=0.7 at high (top) and low (bottom) Reynolds number

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Figure 11

Simulated Mach number distributions for M1=0.7 and Re=120,000 at i=−6deg (top), i=0deg (center), and i=+1.5deg (bottom)

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Figure 12

Schlieren photograph and surface Mach number distributions for M1=0.7 at i=−6deg and Re≈1×106. Experiment (symbol) and MISES (line).

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Figure 13

Surface Mach number distributions and Schlieren photograph for M1=0.7 at i=+1.5deg and Re≈1×106. Experiment (symbol) and MISES (line).

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Figure 14

Surface Mach number distributions for M1=0.7 at i=−6deg and low Reynolds number (Re≈1.2×105)

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Figure 15

Surface Mach number distributions for M1=0.7 at i=+1.5deg and a low Reynolds number

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Figure 16

Boundary layer properties at i=0deg for M1=0.7

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Figure 17

Boundary layer properties at i=−6deg for M1=0.7 and additional results for a very low Re=80,000

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Figure 18

Boundary layer properties at i=+1.5deg for M1=0.7

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