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  • 1
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    Numerical Studies of an Array of Fluidic Diverter Actuators for Flow Control (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In this paper, we study the effect of boundary conditions on the behavior of an array of uniformly-spaced fluidic diverters with an ultimate goal to passively control their output phase. This understanding will aid in the development of advanced designs of actuators for flow control applications in turbomachinery. Computations show that a potential design is capable of generating synchronous outputs for various inlet boundary conditions if the flow inside the array is initiated from quiescence. However, when the array operation is originally asynchronous, several approaches investigated numerically demonstrate that re-synchronization of the actuators in the array is not practical since it is very sensitive to asymmetric perturbations and imperfections. Experimental verification of the insights obtained from the present study is currently being pursued.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2011-217259 , AIAA Paper 2011-3100 , E-18014 , 41st Fluid Dynamics Conference and Exhibit; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
    Format: application/pdf
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  • 2
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    The Application of Hardware in the Loop Testing for Distributed Engine Control (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The essence of a distributed control system is the modular partitioning of control function across a hardware implementation. This type of control architecture requires embedding electronics in a multitude of control element nodes for the execution of those functions, and their integration as a unified system. As the field of distributed aeropropulsion control moves toward reality, questions about building and validating these systems remain. This paper focuses on the development of hardware-in-the-loop (HIL) test techniques for distributed aero engine control, and the application of HIL testing as it pertains to potential advanced engine control applications that may now be possible due to the intelligent capability embedded in the nodes.
    Keywords: Computer Programming and Software; Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN34093 , AIAA/SAE/ASEE Joint Propulsion Conference; Jul 25, 2016 - Jul 27, 2016; Salt Lake City, UT; United States
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  • 3
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    Numerical Studies of a Fluidic Diverter for Flow Control (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The internal flow structure in a specific fluidic diverter is studied over a range from low subsonic to sonic inlet conditions by a time-dependent numerical analysis. The understanding will aid in the development of fluidic diverters with minimum pressure losses and advanced designs of flow control actuators. The velocity, temperature and pressure fields are calculated for subsonic conditions and the self-induced oscillatory behavior of the flow is successfully predicted. The results of our numerical studies have excellent agreement with our experimental measurements of oscillation frequencies. The acoustic speed in the gaseous medium is determined to be a key factor for up to sonic conditions in governing the mechanism of initiating the oscillations as well as determining its frequency. The feasibility of employing plasma actuation with a minimal perturbation level is demonstrated in steady-state calculations to also produce oscillation frequencies of our own choosing instead of being dependent on the fixed-geometry fluidic device.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-216088 , AIAA Paper 2009-4012 , E-17132 , 39th Fluid Dynamics Conference and Exhibit; Jun 22, 2009 - Jun 25, 2009; San Antonio, TX; United States
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  • 4
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    Numerical Studies of a Supersonic Fluidic Diverter Actuator for Flow Control (2010)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The analysis of the internal flow structure and performance of a specific fluidic diverter actuator, previously studied by time-dependent numerical computations for subsonic flow, is extended to include operation with supersonic actuator exit velocities. The understanding will aid in the development of fluidic diverters with minimum pressure losses and advanced designs of flow control actuators. The self-induced oscillatory behavior of the flow is successfully predicted and the calculated oscillation frequencies with respect to flow rate have excellent agreement with our experimental measurements. The oscillation frequency increases with Mach number, but its dependence on flow rate changes from subsonic to transonic to supersonic regimes. The delay time for the initiation of oscillations depends on the flow rate and the acoustic speed in the gaseous medium for subsonic flow, but is unaffected by the flow rate for supersonic conditions
    Keywords: Aeronautics (General)
    Type: NASA/TM-2010-216805 , AIAA Paper 2010-4415 , E-17437 , 5th Flow Control Conference; Jun 28, 2010 - Jul 01, 2010; Chicago, IL; United States
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