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Tai, Jimmy C. M.

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    Development of an Open Rotor Propulsion System Model and Power Management Strategy
    (Georgia Institute of Technology, 2023-01) Clark, Robert A. ; Perron, Christian ; Tai, Jimmy C. M. ; Airdo, Benjamin ; Mavris, Dimitri N.
    The development of an open rotor propulsion system architecture model and fuel burn-minimizing power management strategy is investigated. The open rotor architecture consists of a single-rotor open rotor (SROR) connected to the low speed shaft of a traditional turbojet engine in a puller configuration. The proposed architecture is modeled in the Numerical Propulsion System Simulation (NPSS) tool, and performance is evaluated across a complete flight envelope typical for a narrow body commercial airliner. Rotor performance maps are generated using a custom blade element momentum theory (BEMT) code, while compressor performance maps are created using CMPGEN. The performance of the overall propulsion system is detailed in the context of a notional 150 passenger aircraft mission, and a method for scheduling rotor power across the flight envelope is developed in order to minimize aircraft mission fuel burn. It is demonstrated that the power absorbed by the rotor can be optimized by scheduling rotor blade pitch angle versus fan speed. A power management technique using the optimal blade pitch angle at only six points in the flight envelope was shown to provide significant computational benefits without sacrificing any fuel burn when compared to a method using a schedule generated from data across the complete flight envelope.
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    Development of a Parametric Variable Cycle Engine Model Using the Multiple Design Point Approach
    (AIAA, 2023-01) Clark, Robert ; Tai, Jimmy C. M. ; Mavris, Dimitri N.
    The development of a parametric variable cycle engine (VCE) model is investigated. The model is developed using the multiple design point (MDP) approach, which allows for the sizing of an engine that meets design criteria across multiple flight conditions. The proposed architecture, a three-stream double-bypass architecture, is modeled in the Numerical Propulsion System Simulation (NPSS) tool. A double bypass architecture is selected due to the need to maintain continuous third-stream flow to be used as a heat sink for cooled-cooling and aircraft cooling heat exchangers. Results show that a VCE utilizing an aft variable area bypass injector (VABI), variable compressor inlet guide vanes (IGVs), and variable nozzle throats can be modulated to provide higher sea-level static (SLS) thrust and lower cruise specific fuel consumption (SFC) than a standard mixed-flow turbofan engine. Furthermore, engine pressure ratio (EPR) is shown to be a convenient thermodynamic parameter, such that variable geometry schedules can be developed as a function of EPR only, without respect to flight altitude or Mach number.
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    The Environmental Design Space: Modeling and Performance Updates
    (Georgia Institute of Technology, 2021-01) Salas Nunez, Luis ; Tai, Jimmy C. M. ; Mavris, Dimitri N.
    The Environmental Design Space (EDS) is a modeling and simulation environment devised for the design and evaluation of subsonic aircraft. One of the main features that sets it apart from other similar frameworks is its capability to perform aircraft performance and sizing, exhaust emissions, and noise prediction. These three elements are seamlessly executed due to the integration of multiple industry-standard tools. Since its conception in 2008, EDS has been used to support multiple research entities and projects for the evaluation of current and future aircraft concepts and technologies. Its results and assumptions have been calibrated and revised through the years in conjunction with panels of experts in the field. Therefore, it has undergone continuous development that has increased its capability, allowing it to model not only traditional tube-and-wing aircraft, but also unconventional configurations. At the writing of this paper, its capabilities extend beyond standard single and dual spool engines to include geared fans, ultra high bypass turbofans, open rotors, and partially turboelectric propulsion architectures. This paper presents an overview of how EDS has been used to support major research efforts. Then, an approach to develop and calibrate engine and aircraft models to match existing open-source data is presented. Finally, a summary of available advanced engine and aircraft architectures is shown. The results demonstrate EDS capability to create models that closely match existing systems performance, and its flexibility to keep supporting future aircraft design and technology development studies.