变循环发动机与飞机热管理系统的集成设计

IF 1.4 4区 工程技术 Q3 ENGINEERING, MECHANICAL
Robert Clark, Jimmy C.M. Tai, Dimitri N. Mavris
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引用次数: 0

摘要

摘要研究了变循环发动机(VCE)与飞机热管理系统(TMS)的集成设计。集成系统采用多设计点方法进行设计,以便在周期设计条件以外的其他点实现所需的性能指标。VCE结构为三流设计,其中第三流在风扇之后分离,通过单独的第三流喷嘴排出。一次气流经过低压压缩机,然后分成内部旁路气流和核心气流。内部气流在低压涡轮尾部混合,并通过核心喷嘴排出。可变循环发动机采用可变压气机进口导叶,在核心流混合平面上使用可变面积旁通喷油器,在两个排气喷嘴中使用可变喉道。TMS架构是一个空气循环系统,使用高压压缩机排出的空气。研究了将TMS集成到发动机设计回路中的效果。与之前的研究进行了比较,其中相同的TMS架构连接到一个低涵道比涡扇发动机。对比表明,与冲压空气冷却系统相比,可变循环发动机能够提高散热能力,同时消除了单独冲压空气流带来的机身集成影响。最后,研究了调节可变几何特征对整体冷却能力的影响。给出了单个操作点以及飞机任务级别的结果。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Integrated Design Of A Variable Cycle Engine And Aircraft Thermal Management System
Abstract The integrated design of a variable cycle engine (VCE) and an aircraft thermal management system (TMS) is investigated. The integrated system is designed using the multiple design point approach in order to achieve required performance metrics at points other than the cycle design condition. The VCE architecture is a three stream design where the third stream is split off after the fan, exhausting through a separate third-stream nozzle. The primary air stream passes through a low-pressure compressor before splitting into an inner bypass stream and a core stream. The inner streams mix aft of the low-pressure turbine and exhaust through a core nozzle. The variable cycle engine utilizes variable compressor inlet guide vanes, a variable area bypass injector at the core stream mixing plane, and variable throats in the two exhaust nozzles. The TMS architecture is an air cycle system using air bled from the high-pressure compressor. The effect of integrating the TMS into the engine design loop is investigated. A comparison is made to prior studies where the same TMS architecture was connected to a low bypass ratio turbofan engine. The comparison shows that the variable cycle engine is able to improve heat dissipation capability versus a ram air cooled system, while eliminating the airframe integration impact that comes with a separate ram-air stream. Lastly, the impact of modulating the variable geometry features on overall cooling capability is investigated. Results are presented for individual operating points as well as at the aircraft mission level.
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来源期刊
CiteScore
3.80
自引率
20.00%
发文量
292
审稿时长
2.0 months
期刊介绍: The ASME Journal of Engineering for Gas Turbines and Power publishes archival-quality papers in the areas of gas and steam turbine technology, nuclear engineering, internal combustion engines, and fossil power generation. It covers a broad spectrum of practical topics of interest to industry. Subject areas covered include: thermodynamics; fluid mechanics; heat transfer; and modeling; propulsion and power generation components and systems; combustion, fuels, and emissions; nuclear reactor systems and components; thermal hydraulics; heat exchangers; nuclear fuel technology and waste management; I. C. engines for marine, rail, and power generation; steam and hydro power generation; advanced cycles for fossil energy generation; pollution control and environmental effects.
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