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Airfoil Parameters Reverse Engineering Framework for Plot Digitized Blade Sections

Dogga, Bharadwaj
http://orcid.org/0009-0002-5915-1367
http://rave.ohiolink.edu/etdc/view?acc_num=ucin1733831422629719

Abstract Details

2024, MS, University of Cincinnati, Engineering and Applied Science: Aerospace Engineering.
A framework to reverse engineer airfoil section parameters using a Turbomachinery Blade Geometry code has been developed and presented. A multivariable single objective optimization is used to reduce the sum of the square difference between the parametric blade shape and the target airfoil blade section to obtain those parameters. The method divides input airfoil into six parts to simplify blade difference calculation. A turbomachine blade section is obtained using the new input files with airfoil parameters: inlet and outlet metal angles, six curvature control points, Leading edge radius, location of maximum thickness, value of maximum thickness, and trailing edge thickness. Key issues of the process are discussed. A demonstration of the developed method was carried out by first reverse engineering three different airfoils and then reverse engineering E3 transonic compressor blade from its sections. This blade was chosen due to its uniqueness of having a sloped hub. The Airfoil sections were plot digitized from the E3 report which were then run through the method to get Tblade3 parameters. A subsequent 3D simulation of the blade has been carried out to compare the performance of the reverse engineered blade with it’s the experimental results of the actual design. Furthermore, a grid dependence and off design study (full speedline) has been carried out to determine the most appropriate running condition for the comparison. Insights on further directions are suggested that will improve the comparison.
Mark Turner, Sc.D. (Committee Chair)
Paul Orkwis, Ph.D. (Committee Member)
Benjamin Vaughan, Ph.D. (Committee Member)
Daniel Cuppoletti, Ph.D. (Committee Member)
Prashant Khare, Ph.D. (Committee Member)
202 p.
Aerospace Materials
Airfoil; Optimization; OpenMDAO; Reverse engineering; Blade Digitization; Automation

Recommended Citations

Citations

  • Dogga, B. (2024). Airfoil Parameters Reverse Engineering Framework for Plot Digitized Blade Sections [Master's thesis, University of Cincinnati]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1733831422629719

    APA Style (7th edition)

  • Dogga, Bharadwaj. Airfoil Parameters Reverse Engineering Framework for Plot Digitized Blade Sections. 2024. University of Cincinnati, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=ucin1733831422629719.

    MLA Style (8th edition)

  • Dogga, Bharadwaj. "Airfoil Parameters Reverse Engineering Framework for Plot Digitized Blade Sections." Master's thesis, University of Cincinnati, 2024. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1733831422629719

    Chicago Manual of Style (17th edition)

ucin1733831422629719
20
© 2024, some rights reserved.Creative Commons License Airfoil Parameters Reverse Engineering Framework for Plot Digitized Blade Sections by Bharadwaj Dogga is licensed under a Creative Commons Attribution-NonCommercial-NoDerivs 3.0 Unported License. Based on a work at etd.ohiolink.edu.
This open access ETD is published by University of Cincinnati and OhioLINK.