High pressure compressor component performance report [PDF]
A compressor optimization study defined a 10 stage configuration with a 22.6:1 pressure ratio, an adiabatic efficiency goal of 86.1%, and a polytropic efficiency of 90.6%; the corrected airflow is 53.5 kg/s.
Cline, S. J. +4 more
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An aerodynamic investigation of a high-pressure turbine using rotor casing static pressure measurements at engine representative conditions with different tip designs, tip gaps, and inlet temperature profiles [PDF]
A rotating high-pressure (HP) turbine, in modern aircraft engines, is subjected to high cyclic thermal and mechanical loads. Shroudless turbines experience high heat loads on the rotor tip and casing, which makes them one of the life-limiting components ...
Bahulekar, Pratik +7 more
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Infrared Heat Transfer Coefficient Measurements in an Engine-Scaled Turbine Stage [PDF]
This paper presents full-field heat transfer coefficient measurements using infrared thermography in an engine-scaled, partially-cooled turbine stage in the NG-Turb facility at DLR Göttingen.
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Heat Transfer Due to Unsteady Effects as Investigated in a High-Speed, Full-Scale, Fully-Cooled Turbine Vane and Rotor Stage [PDF]
, 2008 Experiments were conducted to examine the effects of film cooling on a gas turbine engine’s high‐pressure turbine section. The focus for this effort was in the tip/shroud region of a rotor stage and a high pressure turbine vane.
Mason, Jonathan R.
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NiAl-based approach for rocket combustion chambers [PDF]
, 2005 A multi-layered component, such as a rocket engine combustion chamber, includes NiAl or NiAl-based alloy as a structural layer on the hot side of the component.
Gayda, John +2 more
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EXPERIMENTAL STUDY ON REDUCTION OF LEAKAGE LOSS IN ULTRA HIGHLY LOADED LINEAR TURBINE CASCADE : EFFECTS OF SQUEALER DEPTH AND CLEARANCE SIZE [PDF]
, 2018 An increase of turbine blade loading by the increase of blade turning angle enables to reduce the numbers of the blades and the stages, which result in the decreases of a gas turbine in size and weight.
脇田 悠介
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Summary and analysis of performance and stability characteristics of the refan JT8D-109 engine [PDF]
The refan JT8D-109 performance and stability characteristics are reported as determined from sea level testing, altitude testing, and DC-9 flight testing.
Davis, J. C. +3 more
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Unsteady Analysis of Blade and Tip Heat Transfer as Influenced by the Upstream Momentum and Thermal Wakes [PDF]
The effect of the upstream wake on the blade heat transfer has been numerically examined. The geometry and the flow conditions of the first stage turbine blade of GE s E3 engine with a tip clearance equal to 2 percent of the span was utilized.
Ameri, Ali A. +4 more
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Modeling approach to calculate redistributions of HPT-shroud cooling channels including some turbine blade tip effects [PDF]
Gestel, R. van +3 more
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Aerothermal optimization of turbine cascade squealer tip with non-uniform squealer height
Physics of Fluids, 2023The squealer tip has significant influence on both the aerodynamic and heat transfer characteristics of the high-pressure turbine blade. However, due to the complexity of parameterization and meshing of the squealer and the complicated flow structure within the over-tip region, the existing squealer designs in the open literature have constant squealer
Hongzhi Cheng +5 more
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