Conceptual Design of Turbo-Accelerator for HST Combined Cycle Engine
Conceptual Design of Turbo-Accelerator for HST Combined Cycle Engine
复制标题
HST联合循环发动机涡轮加速器概念设计
DOI：
10.1115/92-gt-253
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发表时间：
1992
期刊：
影响因子：
--
通讯作者：
T. Aoki
中科院分区：
文献类型：
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作者：
R. Yanagi;M. Morita;Y. Watanabe;H. Itahara;Y. Sasaki;T. Aoki
高超声速运输机推进系统研究项目（I1 YPH）于1990年启动，旨在开发环境可接受且经济可行的5马赫高超声速民用运输机推进系统技术。所研究的发动机是由低速涡轮加速器和高速冲压发动机组成的甲烷燃料联合循环发动机。这就是所谓的涡轮/冲压喷气发动机。涡轮加速器需要满足起飞时的低噪音规定，并在高速飞行时获得高比推力，如第二代SST（超音速运输机）发动机。为了满足上述要求，选择了采用变循环方案的单涵道涡扇发动机（S BE）作为涡轮加速发动机。该发动机设计为在压气机定子、低压涡轮机定子、风扇旁通流喷嘴区域和排气喷嘴区域中具有可变几何形状，以便在起飞时具有低喷射速度，在高空高速时具有高喷射速度，并且在排气喷嘴中配备混合喷射器以进一步降低噪声。本文介绍了计划于1993年进行试验的涡轮加速发动机的循环研究和验证机的概念设计。
Hypersonic Transport Propulsion System Research (I1YPH) Project was started In 1990 to develop technologies for the propulsion system of a Mach 5 Hypersonic Civil Transport, which could be environmentally acceptable and economically viable. The engine being studied is the methane fueled combined cycle engine composed of a turbo-accelerator for low speed range and a ramjet engine for high speed range. what Is called a turbo/ramjet engine. The turbo- accelerator Is required to meet the low noise regulations at take-off and achieve high specific thrust at high speed flight like the second generation SST (Supersonic Transport) engine. The single bypass turbofan engine (S BE) with variable cycle concept was selected as the turbo-accelerator engine to meet the above requirements in one engine. The engine was conceived to have variable geometry In compressor stator, low pressure turbine stator, fan bypass flow nozzle area and exhaust nozzle area for low jet velocity at take-off and high jet velocity at altitude high speed and be equipped with a mixer ejector In the exhaust nozzle for further noise reduction. This paper describes the cycle study and conceptual design or the demonstrator of a turbo-accelerator engine being planned to be tested In 1993.