分布式边界层吸入推进系统的建模与分析

doi:10.7527/S1000-6893.2018.22048

Abstract

Abstract: The aft body boundary layer ingesting technology can significantly improve the fuel economy of aircraft. However, the design and analysis methods for such a propulsion system have not been developed yet. To provide supportive theories and data on the distributed boundary layer ingesting propulsion system of N3-X aircraft, the numerical analysis method based on integral boundary layer equations is used and the power-thrust ratio is introduced to analyze the effect of boundary layer conditions and propulsion system parameters on the system performance. The computational model and procedure are validated through a comparison between the benchmark condition and N3-X. Analyses show that 50% boundary layer ingestion can improve the fuel consumption efficiency by 4%. The smaller the shape factor is or the larger the momentum thickness is, the less the fuel consumption is. The power-thrust ratio is weakly relevant to the inlet area ratio, but the ratio decreases with the increase of the inlet Mach number or fan efficiency, or with the decrease of the fan pressure ratio, fan loss or jet velocity.

Key words: distributed propulsion, boundary layer ingestion, inlet, propulsive fan, nozzle, power-thrust ratio

CLC Number:

V211.3

DA Xingya, FAN Zhaolin, XIONG Neng, WU Junqiang, ZHAO Zhongliang. Modeling and analysis of distributed boundary layer ingesting propulsion system[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(7): 122048-122048.

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Modeling and analysis of distributed boundary layer ingesting propulsion system

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