Optimal selection and analysis of design parameters for turbine-electric distributed propulsion

被引：0
|
作者：
Xie Q. [1 ]
Deng L. [1 ]
Wu H. [1 ]
机构：
[1] School of Power and Energy, Northwestern Polytechnical University, Xi’an
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2024年 / 45卷 / 01期
关键词：
Cycle parameters; Differential evolution algorithm; Distributed propulsion; Fuel consumption rate; Optimization; Turbine-electric;
D O I：
10.13675/j.cnki.tjjs.2210057
中图分类号：
学科分类号：
摘要：
In order to study the selection of design parameters of the Turbo-electric Distributed Propulsion system（TeDP），based on the component method，the design point performance calculation model of the entire TeDP system was established，and the optimal distribution relationship of the effective work between the turboshaft nozzle and the fan system was deduced. On the basis of the above，taking the ECO-150-300 aircraft as the application object，using the differential evolution algorithm，and taking the fuel consumption rate at the design cruise point as the optimization goal，the cycle parameters of TeDP were optimized. Then the optimized cycle parameters were analyzed，and the optimized result was compared with the high bypass ratio turbofan engine. The optimized cruising fuel consumption is 7.68% lower than the original system. There is an optimal fan design pressure ratio to make the fan duct with the highest efficiency，and the optimal design pressure ratio is related to the total pressure loss of the duct. The fuel consumption rate of the TeDP system is most sensitive to electrical component efficiency，free turbine efficiency，and fan adiabatic efficiency，and when these efficiencies respectively decrease by 1.0%，the fuel consumption rate increases by 1.0%，0.94% and 0.85%，respectively. Compared with the geared turbofan engine with a bypass ratio of 20，TeDP shows an economic advantage only when the electrical component efficiency is greater than 0.95. When the electrical component efficiency is close to 1，the fuel consumption rate of TeDP decreases by 5.40%. © 2024 Journal of Propulsion Technology. All rights reserved.
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共 30 条
  • [1] 34, 3, pp. 56-61, (2019)
  • [2] KOTLARZ W，WITANOWSKI M., Turbine engines trend development［J］, Journal of KONBiN, 51, 1, pp. 243-254, (2021)
  • [3] 9, 3, pp. 356-362, (2018)
  • [4] OKAI K, Et al., Investigation of FC/GT hybrid core in electrical propulsion for fan aircraft［C］, Orlando：51st AIAA/SAE/ASEE Joint Propulsion Conference, (2015)
  • [5] BOWMAN C L, FELDER J L, MARIEN T V., Turbo- and hybrid-electrified aircraft propulsion concepts for commercial transport［C］, Cincinnati：2018 AIAA/IEEE Electric Aircraft Technologies Symposium（EATS）, (2018)
  • [6] STONE J, Et al., Initial noise assessment of an embedded-wing-propulsion concept vehicle［C］, Sacramento：42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, (2008)
  • [7] KIM H, BERTON J, JONEs S., Low noise cruise efficient short take-off and landing transport vehicle study ［C］, Wichita：6th AIAA Aviation Technology，Integration and Operations Conference（ATIO）, (2006)
  • [8] GOHARDANI A S，, DOULGERIS G, SINGH R., Challenges of future aircraft propulsion：a review of distributed propulsion technology and its potential application for the all electric commercial aircraft［J］, Progress in Aerospace Sciences, 47, 5, pp. 369-391, (2011)
  • [9] FELDER J, KIM H, BROWN G., Turboelectric distributed propulsion engine cycle analysis for hybrid-wing-body aircraft［C］, Orlando：47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, (2009)
  • [10] FREEMAN J., Aeropropulsive interaction and thermal system integration within the ECO-150：a turboelectric distributed propulsion airliner with conventional electric machines［C］, Washington：16th AIAA Aviation Technology，Integration，and Operations Conference, (2016)
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