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LOX-HYDROCARBON ROCKET ENGINES AND THRUST CHAMBER TECHNOLOGIES FOR FUTURE LAUNCH VEHICLE APPLICATIONS

机译：未来发射汽车应用中的低氧加氢火箭发动机和推力室技术

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Non-toxic hydrocarbon propellants have gained interest recently promising better environmental conditions for easier handling and thus reduced space transportation costs. Liquid methane provides the best performance and chamber cooling capability but requires cryo-cooling and no operational engine has been developed so far. Kerosene is more dense and easily storable but the chamber requires thermal protection coating or film-cooling due to the low coking temperature limit. A huge experience is available for LOX-kerosene in particular from Russian engines. The danger of corrosion due to small impurities in methane was observed independently by various authors and needs to be checked for the envisioned methane composition and liner material. Irrespective of the fuel choice, it is recommended to keep the size and thrust level of future thrust chambers near the range experienced today for Europe. The engine system trade-off showed that a fuel-rich turbine gas results in higher engine performance of gas generator cycle engines. The sooting associated with fuel-rich hot gases needs to be studied in further detail. Oxidizer-rich turbine gas seems to be more attractive for staged combustion cycle engines in view of pump pressures, thus turbopump complexity. Sooting is avoided in oxygen-rich gases. However, the oxygen-rich environment may require specific material selection or coatings to reliably prevent hazards. Pump pressures are also acceptable in the fuel-rich staged combustion cycle with LOX-methane, thus problems associated with the hot oxygen-rich environment would be avoided. All engine cycles are suited for a single-shaft turbopump configuration. To gain experimental experience for injection, ignition, and combustion of LOX-hydrocarbon, subscale chamber tests with different types of injection elements for LOX-methane and LOX-kerosene were performed in cooperation with CADB. The tests with LOX-methane demonstrated successful ignition and operation of three injector types. The combustion efficiency could be increased by variation of injector parameters to values as high as the past experience with LOX-H2. A GOX-methane torch igniter was used successfully. The injector trade-off testing was complemented in summer 2002 with subscale tests for LOX-kerosene using the same subscale chamber with new injection elements designed for liquid-liquid injection. Most of the tests were conducted successfully and indicate good injector element behavior including reliable ignition using a GOX-kerosene spark igniter. In two cases, the tests had to be stopped due to excessive combustion instabilities. A slight soot layer that had formed could be cleaned away easily. A new phase in the cooperation is currently under discussion aiming at continuing the testing of injection elements and also including some cooling testing with methane and kerosene. Further work is aimed at an in-depth trade-off between methane and kerosene as a hydrocarbon fuel for future reusable space transportation.
机译：最近，无毒烃推进剂引起了人们的兴趣，他们承诺提供更好的环境条件，以便于处理，从而降低空间运输成本。液态甲烷具有最佳的性能和腔室冷却能力，但需要进行低温冷却，并且迄今为止尚未开发出可运行的发动机。煤油更致密且易于存储，但由于焦化温度低，该腔室需要热保护涂层或薄膜冷却。 LOX煤油具有丰富的经验，尤其是俄罗斯发动机。各种作者独立地观察到由于甲烷中的少量杂质而导致腐蚀的危险，需要对预想的甲烷成分和衬里材料进行检查。无论选择哪种燃料，建议将未来的推力室的尺寸和推力水平保持在当今欧洲所能承受的范围内。发动机系统的权衡表明，富含燃料的涡轮气体会导致气体发生器循环发动机的发动机性能更高。与富含燃料的热气体相关的烟ot需要进一步研究。鉴于泵压力，因此涡轮增压器的复杂性看来，富含氧化剂的涡轮气体对于分级燃烧循环发动机似乎更具吸引力。避免在富氧气体中积灰。但是，富氧环境可能需要特定的材料选择或涂层以可靠地防止危害。在具有LOX-甲烷的富燃料分阶段燃烧循环中，泵压也是可接受的，因此可以避免与热富氧环境相关的问题。所有发动机循环均适用于单轴涡轮泵配置。为了获得有关LOX烃的注入，点火和燃烧的实验经验，与CADB一起对LOX甲烷和LOX煤油使用了不同类型的注入元素进行了小规模室内试验。用LOX甲烷进行的测试证明了三种喷射器的成功点火和运行。通过将喷油器参数更改为与LOX-H2过去的经验一样高的值，可以提高燃烧效率。成功使用了GOX甲烷火炬点火器。注射器的权衡测试在2002年夏季得到了补充，在LOX煤油的子级测试中使用了相同的子级腔，并为液-液注入设计了新的注入元件。大多数测试均已成功进行，并显示出良好的喷油嘴性能，包括使用GOX-煤油火花点火器的可靠点火。在两种情况下，由于过度的燃烧不稳定性而不得不停止测试。容易清除形成的少量烟灰层。目前正在讨论合作的新阶段，目的是继续测试注入元件，还包括使用甲烷和煤油进行一些冷却测试。进一步的工作旨在在甲烷和煤油（作为碳氢燃料）之间进行深入权衡，以供将来可重复使用的太空运输之用。

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