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Michael van de Noort and Peter T. Ireland
Double-Wall Effusion Cooling schemes present an opportunity for aeroengine designers to achieve high overall cooling effectiveness and convective cooling efficiency in High-Pressure Turbine blades with reduced coolant usage compared to conventional cooli...
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Xiaojun Yang, Hongming Cai, Jinhui Kang, Wenbo Liu and Peiran Li
In modern civil aeroengines, the hot streak and swirl at the exit of the combustor have a significant impact on the aerothermal performance of the high-pressure turbine (HPT). Due to the different design purposes of the combustor and the turbine, hot str...
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Michael van de Noort and Peter Ireland
The high pressure turbine nozzle guide vane of a modern aeroengine experiences large heat loads and thus requires both highly effective internal and external cooling. This can be accomplished with double-wall effusion cooling, which combines impingement,...
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Shenghui Zhang, Shuiting Ding, Peng Liu and Tian Qiu
In advanced civil aero-engine, the gas exiting combustor typically features hot streak (HS) and swirl that affect the aerothermal performances of the high pressure (HP) nozzle guide vane (NGV). The purpose of this paper is to study the influences of HS o...
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Pawel Flaszynski, Michal Piotrowicz and Tommaso Bacci
Investigations of combustors and turbines separately have been carried out for years by research institutes and aircraft engine companies, but there are still many questions about the interaction effect. In this paper, a prediction of a turbine stator?s ...
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Peng Guan, Yanting Ai, Chengwei Fei and Yudong Yao
The aim of this paper was to develop a master?slave model with fluid-thermo-structure (FTS) interaction for the thermal fatigue life prediction of a thermal barrier coat (TBC) in a nozzle guide vane (NGV). The master?slave model integrates the phenomenol...
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Cengiz Camci, Michael Averbach and Jason Town
Flow within the space between the rotor and stator of a turbine disk, and an area referred to as the rim seal cavity, develops azimuthal velocity component from the rotor disk. The fluid within develops unsteady structures that move at a fraction of the ...
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Nicholas Bojdo and Antonio Filippone
There have been several recorded mishaps of rotorcraft experiencing flame-out due to engine surge as a result of rapid accumulation of sand and dust on nozzle guide vanes. Minerals such as sodium chloride and albite have lower melting points than quartz ...
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Holger Werschnik, Marius Schneider, Janina Herrmann, Dimitri Ivanov, Heinz-Peter Schiffer and Christoph Lyko
The aerothermal interaction of the combustor exit flow on the first vane row has been examined at the Large Scale Turbine Rig (LSTR) at Technische Universität Darmstadt (Darmstadt, Germany). A baseline configuration of axial inflow and a variation of swi...
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A. A. Thrift, K. A. Thole, and S. Hada
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