In our previous work on ultralow-aspect ratio transonic turbine inlet guide vanes (IGVs) for a small turbofan engine (Hasenjäger et al., 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.
Skip Nav Destination
e-mail: martina.hasenjaeger@honda-ri.de
e-mail: bs@honda-ri.de
Article navigation
January 2009
Research Papers
Effect of End Wall Contouring on Performance of Ultra-Low Aspect Ratio Transonic Turbine Inlet Guide Vanes
Toyotaka Sonoda,
Toyotaka Sonoda
Honda R&D Co.
, Aircraft Engine R&D Center, 1-4-1 Chuo, Wako-shi, Saitama 351-0193, Japan
Search for other works by this author on:
Martina Hasenjäger,
e-mail: martina.hasenjaeger@honda-ri.de
Martina Hasenjäger
Honda Research Institute Europe GmbH
, Carl-Legien-Strasse 30, D-63073 Offenbach/Main, Germany
Search for other works by this author on:
Toshiyuki Arima,
Toshiyuki Arima
Honda R&D Co.
, Fundamental Technology Research Center, 1-4-1 Chuo, Wako-shi, Saitama 351-0193, Japan
Search for other works by this author on:
Bernhard Sendhoff
e-mail: bs@honda-ri.de
Bernhard Sendhoff
Honda Research Institute Europe GmbH
, Carl-Legien-Strasse 30, D-63073 Offenbach/Main, Germany
Search for other works by this author on:
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, Germanye-mail: martina.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, Germanye-mail: bs@honda-ri.de
J. Turbomach. Jan 2009, 131(1): 011020 (11 pages)
Published Online: November 10, 2008
Article history
Received:
July 23, 2007
Revised:
August 20, 2007
Published:
November 10, 2008
Citation
Sonoda, T., Hasenjäger, M., Arima, T., and Sendhoff, B. (November 10, 2008). "Effect of End Wall Contouring on Performance of Ultra-Low Aspect Ratio Transonic Turbine Inlet Guide Vanes." ASME. J. Turbomach. January 2009; 131(1): 011020. https://doi.org/10.1115/1.2813015
Download citation file:
Get Email Alerts
The Cooling Effect of Combustor Exit Louver Scheme on a Transonic Nozzle Guide Vane Endwall
J. Turbomach (July 2025)
Aerodynamic Performance Evaluation of Subsonic Compressor Cascade Blade With Leading-Edge Damage
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
Adjoint Aerodynamic Design Optimization for Blades in Multistage Turbomachines—Part II: Validation and Application
J. Turbomach (April,2010)
2D Viscous Aerodynamic Shape Design Optimization for Turbine Blades Based on Adjoint Method
J. Turbomach (July,2011)
Profiled End Wall Design Using an Adjoint Navier–Stokes Solver
J. Turbomach (April,2008)
Advanced Aerodynamic Optimization System for Turbomachinery
J. Turbomach (April,2008)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Other Components and Variations
Axial-Flow Compressors
Introduction
Design and Analysis of Centrifugal Compressors