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Tian S.-Q.,Aviation Industry Corporation of China Commercial Aircraft Engine Company Ltd | Tian S.-Q.,Rheinisch Westfaelische Technische Aachen University | Xue H.,Aviation Industry Corporation of China International Holding Corporation | Gao C.,Beihang University | Li Y.,Sinopec
Hangkong Dongli Xuebao/Journal of Aerospace Power | Year: 2012

In order to get a better knowledge of the heat transfer in compressor cavities of aero-engines, the simplified rotating cavity with two-plane discs, a shaft and a cylindrical rim has been investigated numerically and compared with the available measurements. The numerical results in agreement with the available experiments show large-scale instabilities. The disk local Nusselt numbers show mainly radial rising distributions for the heated disks with radial rising temperature profiles. In the present work, at the Reynolds number of 20000, the disk local Nusselt numbers are the correlations of the local Grashof number to the power of 1.89~2.6, and the value of the power is increased as the rotational Reynolds number goes up. At the rotational Reynolds number of 800000, the local Nusselt numbers are the correlations of the local Grashof number to the power of 0.68~2.6, and the value of the power is decreased as Reynolds number goes up. The area-averaged disk Nusselt number is the correlation of the Reynolds number to the power of 0.479 and the rotational Grashof number to the power of 0.12. Source


Chen J.,Nanjing University of Aeronautics and Astronautics | Chen J.,Aviation Industry Corporation of China Commercial Aircraft Engine Company Ltd | Ji H.-H.,Nanjing University of Aeronautics and Astronautics
Hangkong Dongli Xuebao/Journal of Aerospace Power | Year: 2012

A numerical study was conducted on infrared radiation characteristics in the waveband of 3~5 μm for two-dimensional plug nozzle of a turbofan engine, which was compared with an axisymmetric converge-diverge nozzle. The results reveal that: compared to axisymmetric converge-diverge nozzle, there is only a limited range of detecting angle, where the two-dimensional plug nozzle has infrared restraining effect. The infrared radiation of two-dimensional plug nozzle decreases 54% as the detecting angle equals to 90° on the narrow detecting side. On the condition that the back wall temperature of plug decreases 300 K, the two-dimensional plug nozzle has visible infrared restraining effect on most detecting angle; moreover, its infrared radiation intensity decreases 57% towards the aft-nozzle. Source


Chen M.-N.,Aviation Industry Corporation of China Commercial Aircraft Engine Company Ltd | Xie W.-L.,Aviation Industry Corporation of China Commercial Aircraft Engine Company Ltd | Wang H.-T.,Aviation Industry Corporation of China Commercial Aircraft Engine Company Ltd
Hangkong Dongli Xuebao/Journal of Aerospace Power | Year: 2014

Three-dimensional numerical simulations were carried out for a compressor to investigate the stator cavities' influence to the performance and flow field. Detailed analyses of the performance and flow field came to some conclusions: the cavity leakage flow led to decreases in the efficiency, pressure ratio and stall margin of the compressor. The compressor stall margin declines by 5.19% due to the cavity leakage flow. The cavity leakage flow mainly influences the root flow of the stator and rear blades, and changes the compressor stall mechanism. The cavity leakage flow causes flow separation near the hub of the first stator, as a result the second rotor incidence angle increase sharply; consequently the flow separates at the suction side of the second rotor, causing the compressor stall earlier than that without the cavity. ©, 2014, BUAA Press. All right reserved. Source

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