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    The Effect of Upstream Unsteadiness on the Unstarting of a Supersonic Inlet Turbine 

    Source: Journal of Turbomachinery:;2023:;volume( 146 ):;issue: 004:;page 41005-1
    Author(s): Mushtaq, Noraiz; Gaetani, Paolo
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: A 15% increase in thermal efficiency at medium pressure ratios is promised by rotating detonation engine technology over conventional Joule–Bryton cycles. A supersonic inlet turbine is a viable option to extract substantial ...
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    Advanced Design of a Transition Duct for Supersonic Inlet Turbines in Rotating Detonation Engines 

    Source: Journal of Turbomachinery:;2024:;volume( 147 ):;issue: 003:;page 31014-1
    Author(s): Mushtaq, Noraiz; Pini, Matteo; Gaetani, Paolo
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: A supersonic inlet turbine can extract substantial energy from the highly fluctuating and transonic flow delivered by a rotating detonation combustor (RDC). However, a transition duct is necessary to achieve the supersonic ...
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    The Role of Endwall Shape Optimization in the Design of Supersonic Turbines for Rotating Detonation Engines 

    Source: Journal of Turbomachinery:;2023:;volume( 145 ):;issue: 008:;page 81015-1
    Author(s): Mushtaq, Noraiz; Persico, Giacomo; Gaetani, Paolo
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Rotating detonation engines (RDEs) are characterized by a thermodynamic cycle with an efficiency gain up to 15% at medium pressure ratios with respect to systems based on the conventional Joule–Bryton cycle. Multiple turbine ...
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