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Comparison of experimentally obtained performance of two single-stage turbines with design ratios of blade to jet speed of 0.191 and 0.262 operated in hydrogen and in nitrogen

机译：两个单级涡轮机的实验获得性能的比较，叶片与喷射速度的设计比率为0.191和0.262在氢气和氮气中操作

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作者
Wong, R. Y.; Darmstadt, D. L.;
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年度 1961
页码 1-24
总页数 24
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
PERFORMANCE TESTS; TURBINES; ENGINE DESIGN; HYDROGEN; NITROGEN;

机译：性能测试;汽轮机。发动机设计;氢;氮;

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1. Turbocharger turbine rotor tip leakage loss and mass flow model valid up to extreme off-design conditions with high blade to jet speed ratio [J] . Ramon Serrano Jose, Navarro Roberto, Miguel Garcia-Cuevas Luis, Energy . 2018,第MARa15期

机译：涡轮增压器的转子尖端泄漏损失和质量流模型在极端的非设计条件下有效，并且叶片与喷射的速度比高
2. Erosion of wind turbine blade coatings - Design and analysis of jet-based laboratory equipment for performance evaluation [J] . Zhang Shizhong, Dam-Johansen Kim, Norkjaer Sten, Progress in Organic Coatings: An International Review Journal . 2015,第Null期

机译：风力涡轮机叶片涂层的腐蚀-用于性能评估的基于喷射的实验室设备的设计和分析
3. Off-design performance comparison of single-stage axial turbines using CO_2 and zeotropic mixture for low-temperature heat source [J] . Peng Ningjian, Wang Enhua, Meng Fanxiao Energy Conversion & Management . 2020,第Juna期

机译：单级轴向涡轮机使用CO_2和鸟升混合物进行低温热源的缺失性能比较
4. Comparison of computational and experimental results for a transonic variable-speed power-turbine blade operating with low inlet turbulence levels [C] . David T. Booth, Ashlie B. Flegel AIAA propulsion and energy forum;AIAA/SAE/ASEE joint propulsion conference . 2015

机译：跨音速变速动力涡轮叶片在低入口湍流水平下运行的计算结果和实验结果的比较
5. An analytical and experimental investigation of potential mechanical work extraction from supersonic jet flow on high speed mini turbines. [D] . Lee, Ken Thye. 2010

机译：高速微型涡轮机上从超音速喷射流中提取潜在机械功的分析和实验研究。
6. Development of a centrifugal separator for grape marc: effect of the blade position and rotor speed on grape seed separation performance [O] . Roberto Romaniello, Antonia Tamborrino, Alessandro Leone 2019

机译：葡萄渣离心分离机的开发：叶片位置和转子转速对葡萄籽分离性能的影响
7. Cascade tests of the blading of a high-deflection, single-stage, axial-flow impulse turbine and comparison of results with actual performance data [O] . Bartocci John Eugene 1966

机译：高挠度单级轴流冲击式涡轮机叶片的级联测试，并将结果与实际性能数据进行比较
8. Cold-air performance evaluation of a three-stage turbine having a blade-jet speed ratio of 0.156 designed for a 100,000-pound-thrust hydrogen-oxygen rocket turbopump application [R] . Kofskey, M. G. 1961

机译：叶片喷射速度比为0.156的三级涡轮机的冷空气性能评估设计用于100,000磅推力的氢氧火箭涡轮泵应用

Comparison of experimentally obtained performance of two single-stage turbines with design ratios of blade to jet speed of 0.191 and 0.262 operated in hydrogen and in nitrogen

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