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DESIGN STUDY AND COMPONENT TESTS ON A SUBSCALE PRECOOLED TURBOJET ENGINE FOR FLIGHT EXPERIMENTS

机译:用于飞行实验的超小型预冷却涡轮喷气发动机的设计研究和组件测试

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摘要

Components of the small scale precooled turbojet engine such as variable intake, air pre-cooler, core engine, ram combustor, and variable nozzle are designed and tested for flight experiments and high enthalpy wind tunnel tests. The engine is expected to be operative from lift-off to Mach 6 by applying the precooling system and using LH2 as a fuel. Length of the engine is 2 m. Hypersonic and supersonic wind tunnel experiments are conducted to acquire and improve the intake aerodynamic performances. Total pressure recovery of the intake is 0.22 at Mach 5. Variable intake with advanced composite material is designed to realize the intake without cooling under Mach 6 flight condition. The shape of the intake and the precooler is determined using FEM analysis. Mixed compression type compressor is designed by CFD analyses. Component test of the main combustor is performed using gas hydrogen. A variable mechanism and cooling mechanism of the rectangular nozzle is designed. After the wind tunnel and combustion tests of the engine components, total engine system is designed by 3 dimensional CAD. The weight of the engine satisfies the requirement of the flight test.
机译:小型预冷涡轮喷气发动机的组件,例如可变进气,空气预冷器,核心发动机,冲压燃烧器和可变喷嘴,均经过设计和测试,用于飞行实验和高焓风洞测试。通过使用预冷却系统并使用LH2作为燃料,发动机有望从提速到6马赫运转。引擎长度为2 m。进行高超音速和超音速风洞实验,以获取和改善进气空气动力学性能。进气口的总压力恢复为5马赫时为0.22。采用先进的复合材料制成的可变进气口旨在在6马赫飞行条件下实现无需冷却的进气。进气口和预冷器的形状使用FEM分析确定。混合压缩式压缩机是通过CFD分析设计的。主燃烧室的成分测试是使用氢气进行的。设计了矩形喷嘴的可变机构和冷却机构。经过风洞和发动机部件的燃烧测试后,整个发动机系统由3D CAD设计。发动机的重量满足飞行测试的要求。

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