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Research Papers

Numerical Investigation of Tandem Airfoils for Subsonic Axial-Flow Compressor Blades

[+] Author and Article Information
Jonathan McGlumphy

Department of Mechanical Engineering, Virginia Polytechnic Institute & State University, Blacksburg, VA 24061jmcglump@vt.edu

Wing-Fai Ng

Department of Mechanical Engineering, Virginia Polytechnic Institute & State University, Blacksburg, VA 24061wng@vt.edu

Steven R. Wellborn

Compressor and Fan Aerodynamic Design, Rolls-Royce Corp., Indianapolis, IN 46206steven.r.wellborn@rolls-royce.com

Severin Kempf

Compressor and Fan Aerodynamic Design, Rolls-Royce Corp., Indianapolis, IN 46206severin.g.kempf@rolls-royce.com

J. Turbomach 131(2), 021018 (Feb 03, 2009) (8 pages) doi:10.1115/1.2952366 History: Received August 08, 2007; Revised September 21, 2007; Published February 03, 2009

The tandem airfoil has potential to do more work as a compressor blade than a single airfoil without incurring significantly higher losses. Although tandem blades are sometimes employed as stators, they have not been used in any known commercial rotors. While the long-term goal for this program is development of a commercially viable tandem rotor, this paper discusses tandem airfoils in subsonic, shock-free rectilinear cascade flow. Existing literature data on tandem airfoils in rectilinear cascades have been compiled and presented in a Lieblein loss versus loading correlation. Large scatter in the data gave motivation to conduct an extensive 2D computational fluid dynamics (CFD) study evaluating the overall performance as a function of the relative positions of the forward and aft airfoils. CFD results were consistent with trends in the open literature, both of which indicate that a properly designed tandem airfoil can outperform a comparable single airfoil on and off design. The general agreement of the CFD and literature data serves as a validation for the computational approach.

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Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 10

Mach number contours at 0 AO, 5 PP

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Figure 11

CFD results of selected AO configurations at 90 PP

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Figure 12

Surface Isentropic Mach number at 10 AO, 90 PP

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Figure 13

Example loss bucket with incidence range

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Figure 14

Incidence range versus minimum loss D-factor

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Figure 1

Tandem airfoil geometrical parameters

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Figure 2

Lieblein chart of selected literature

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Figure 3

Single CFD versus tandem design rule

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Figure 4

Typical 2D tandem airfoil mesh

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Figure 5

CFD results of selected PP configurations at zero AO

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Figure 6

Surface isentropic Mach number at 0 AO, 90 PP

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Figure 7

Mach number contours at 0 AO, 90 PP

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Figure 8

Surface isentropic Mach number at 0 AO, 50 PP

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Figure 9

Mach number contours at 0 AO, 50 PP

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