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Multi-fidelity Design and Analysis of Single Hub Multi-rotor High Pressure Centrifugal Compressor

Muppana, Sai
http://rave.ohiolink.edu/etdc/view?acc_num=ucin1553517075653458

Abstract Details

2018, MS, University of Cincinnati, Engineering and Applied Science: Aerospace Engineering.
Centrifugal compressors are favorable because they can generate high pressure ratio due to large change in radius from inlet to exit of compressor. This increase in trend to achieve high pressure ratios with increase blade loading narrows stable operating range of centrifugal compressor with stall and surge at relatively higher mass flow rate. Present research was aimed to improve the stall mass flow rate of centrifugal compressor. A novel configuration is designed and analyzed to overcome this issue by placing multiple rotors on the same hub with a vane in between similar to a multi-stage axial compressor blade arrangement. It is designed in such a way that the flow from the first row is adjusted by the stator for optimum performance of second blade row. A 0D tool has been developed for multi-rotor impellers to provide an estimate of work ratio. Work done by compressor is adjusted between the two blade rows to achieve optimum performance. A mean-line design code (CIMdes) is developed to study the effect of stator inlet flow angles on pressure ratio, work done, overall pressure ratio, isentropic efficiency and diffusion factor. Performance parameters were studied on a 1.5 stage impeller having a blade length of approximately one-third of the total blade length for each blade row using CIMdes. Numerical simulations are carried out through steady CFD analysis at design and off-design conditions for 100% speed-line to understand the flow physics in the compressor. Grid sensitivity study is conducted for three grids with 0.38, 1.9 million and 2.8 million elements respectively. The results obtained are validated with DLR centrifugal compressor. Stall mass flow rate is 18.6% lower than single-rotor compressor. Loss quantification revealed that diffuser losses are higher in single-stage and the novel design increased the backsweep angle resulting in lower diffuser losses. The flow capacity is extended near the stall with a penalty in efficiency. The preliminary analysis demonstrate the advantages of the multi-staging on the same hub and extends the design space for performance range improvement with some trade-offs.
Shaaban Abdallah, Ph.D. (Committee Chair)
Prashant Khare, Ph.D. (Committee Member)
Kiran Siddappaji, Ph.D. (Committee Member)
Mark Turner, Sc.D. (Committee Member)
162 p.
Aerospace Materials
Centrifugal compressor; multi-rotor; CFD; blade design; meanline analysis; stall

Recommended Citations

Citations

  • Muppana, S. (2018). Multi-fidelity Design and Analysis of Single Hub Multi-rotor High Pressure Centrifugal Compressor [Master's thesis, University of Cincinnati]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1553517075653458

    APA Style (7th edition)

  • Muppana, Sai. Multi-fidelity Design and Analysis of Single Hub Multi-rotor High Pressure Centrifugal Compressor. 2018. University of Cincinnati, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=ucin1553517075653458.

    MLA Style (8th edition)

  • Muppana, Sai. "Multi-fidelity Design and Analysis of Single Hub Multi-rotor High Pressure Centrifugal Compressor." Master's thesis, University of Cincinnati, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1553517075653458

    Chicago Manual of Style (17th edition)

ucin1553517075653458
832
© 2018, some rights reserved.Creative Commons License Multi-fidelity Design and Analysis of Single Hub Multi-rotor High Pressure Centrifugal Compressor by Sai Muppana is licensed under a Creative Commons Attribution-NonCommercial-ShareAlike 3.0 Unported License. Based on a work at etd.ohiolink.edu.
This open access ETD is published by University of Cincinnati and OhioLINK.