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Research Papers

Effect of End Wall Contouring on Performance of Ultra-Low Aspect Ratio Transonic Turbine Inlet Guide Vanes

[+] Author and Article Information
Toyotaka Sonoda

 Honda R&D Co., Aircraft Engine R&D Center, 1-4-1 Chuo, Wako-shi, Saitama 351-0193, Japan

Martina Hasenjäger

 Honda Research Institute Europe GmbH, Carl-Legien-Strasse 30, D-63073 Offenbach/Main, Germanymartina.hasenjaeger@honda-ri.de

Toshiyuki Arima

 Honda R&D Co., Fundamental Technology Research Center, 1-4-1 Chuo, Wako-shi, Saitama 351-0193, Japan

Bernhard Sendhoff

 Honda Research Institute Europe GmbH, Carl-Legien-Strasse 30, D-63073 Offenbach/Main, Germanybs@honda-ri.de

J. Turbomach 131(1), 011020 (Nov 10, 2008) (11 pages) doi:10.1115/1.2813015 History: Received July 23, 2007; Revised August 20, 2007; Published November 10, 2008

In our previous work on ultralow-aspect ratio transonic turbine inlet guide vanes (IGVs) for a small turbofan engine (Hasenjäger, 2005, “Three Dimensional Aerodynamic Optimization for an Ultra-Low Aspect Ratio Transonic Turbine Stator Blade  ,” ASME Paper No. GT2005-68680), we used numerical stochastic design optimization to propose the new design concept of an extremely aft-loaded airfoil to improve the difficult-to-control aerodynamic loss. At the same time, it is well known that end wall contouring is an effective method for reducing the secondary flow loss. In the literature, both “axisymmetric” and “nonaxisymmetric” end wall geometries have been suggested. Almost all of these geometric variations have been based on the expertise of the turbine designer. In our current work, we employed a stochastic optimization method—the evolution strategy—to optimize and analyze the effect of the axisymmetric end wall contouring on the IGV’s performance. In the optimization, the design of the end wall contour was divided into three different approaches: (1) only hub contour, (2) only tip contour, and (3) hub and tip contour, together with the possibility to observe the correlation between hub/tip changes with regard to their joint influence on the pressure loss. Furthermore, three-dimensional flow mechanisms, related to a secondary flow near the end wall region in the low-aspect ratio transonic turbine IGV, was investigated, based on the above optimization results. A design concept and secondary flow characteristics for the low-aspect ratio full annular transonic turbine IGV is discussed in this paper.

Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Secondary flow model for a low speed and high-AR turbine blade (obtained from Sonoda (5))

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Figure 2

Meridional passage of an ultralow-AR IGV

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Figure 3

Passage modeling

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Figure 4

Flowchart of optimization environment

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Figure 5

Experimental apparatus for IGV wake traverse measurement at Station 2, using a transonic turbine stage rig

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Figure 6

Comparison of vane surface oil flow visualization for (a) EXP and (b) CFD

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Figure 7

Comparison of loss (top) and exit flow angle (bottom) at Station 2 for EXP and CFD

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Figure 8

Comparison of total pressure loss at Station 2 for EXP (top) and CFD (bottom); 0.05 increment

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Figure 9

Base line and optimized three passages

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Figure 10

Comparison of blade surface Mach number distribution for base line and three optimized passages. (a) base line, (b) hub contouring, (c) tip contouring, and (d) hub and tip contouring.

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Figure 11

Spanwise distribution of loss (top) and exit flow angle (bottom) for base line and three optimized passages

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Figure 12

Total pressure loss contour for base line and three optimized passages at Station 2

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Figure 13

Comparison of loss and exit flow angle for (a) base line and (b) hub and tip contouring

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Figure 14

Relation of high loss region and streamline for base line

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Figure 15

Relation of high loss region and flow angle for base line

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