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    Mach Number Effects on Secondary Flow Development Downstream of a Turbine Cascade 

    Source: Journal of Turbomachinery:;1990:;volume( 112 ):;issue: 004:;page 643
    Author(s): A. Perdichizzi
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The results of an investigation of the three-dimensional flow downstream of a transonic turbine cascade are presented. The investigation was carried out for a wide range of Mach numbers, extending ...
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    Incidence Angle and Pitch–Chord Effects on Secondary Flows Downstream of a Turbine Cascade 

    Source: Journal of Turbomachinery:;1993:;volume( 115 ):;issue: 003:;page 383
    Author(s): A. Perdichizzi; V. Dossena
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: This paper describes the results of an experimental investigation of the three-dimensional flow downstream of a linear turbine cascade at off-design conditions. The tests have been carried out ...
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    Efficiency Prediction for Axial-Flow Turbines Operating with Nonconventional Fluids 

    Source: Journal of Engineering for Gas Turbines and Power:;1981:;volume( 103 ):;issue: 004:;page 718
    Author(s): E. Macchi; A. Perdichizzi
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The need for a simple and reliable method for predicting the efficiency of a turbine stage without carrying out a detailed aerodynamic design is enhanced. The results of an optimization study ...
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    Flow Field Investigation in a Low-Solidity Inducer by Laser-Doppler Velocimetry 

    Source: Journal of Turbomachinery:;1990:;volume( 112 ):;issue: 001:;page 91
    Author(s): A. Boccazzi; A. Perdichizzi; U. Tabacco
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The results of an experimental investigation of the flow field within a low-solidity inducer at design and off-design flow rates are presented and discussed; particular attention is devoted to ...
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    The Influence of Endwall Contouring on the Performance of a Turbine Nozzle Guide Vane 

    Source: Journal of Turbomachinery:;1999:;volume( 121 ):;issue: 002:;page 200
    Author(s): V. Dossena; A. Perdichizzi; M. Savini
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The paper presents the results of a detailed investigation of the flow field in a gas turbine linear cascade. A comparison between a contoured and a planar configuration of the same cascade ...
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    Secondary Flows in a Transonic Cascade: Comparison Between Experimental and Numerical Results 

    Source: Journal of Fluids Engineering:;1989:;volume( 111 ):;issue: 004:;page 369
    Author(s): F. Bassi; C. Osnaghi; A. Perdichizzi; M. Savini
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The paper presents a comparison between numerical results and experimental data about the secondary flow development in a linear transonic turbine cascade. Computations are carried out by using ...
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    Solar Hybrid Combined Cycle Performance Prediction Influence of Gas Turbine Model and Spool Arrangements 

    Source: Journal of Engineering for Gas Turbines and Power:;2012:;volume( 134 ):;issue: 012:;page 121701
    Author(s): G. Barigozzi; G. Bonetti; G. Franchini; A. Perdichizzi; S. Ravelli
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: A modeling procedure was developed to simulate design and off-design operation of hybrid solar gas turbines in a combined cycle (CC) configuration. The system includes a heliostat field, a ...
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    Influence of Coolant Flow Rate on Aero-Thermal Performance of a Rotor Blade Cascade With Endwall Film Cooling 

    Source: Journal of Turbomachinery:;2012:;volume( 134 ):;issue: 005:;page 51038
    Author(s): G. Barigozzi; M. Maritano; R. Abram; F. Fontaneto; G. Franchini; A. Perdichizzi
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: This paper investigates the influence of coolant injection on the aerodynamic and thermal performance of a rotor blade cascade with endwall film cooling. A seven blade cascade of a high-pressure-rotor ...
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