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Dataset of the experimentally measured heat transfer in the throat region of liquid rocket engine thrust chambers

机译:实验测量的热传递的数据集在液体火箭发动机推力室的喉部区域中的热传递

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摘要

About 500 experimental heat transfer data taken from the open literature and relevant to the most thermally solicited area (i.e., the throat region) of liquid rocket engine thrust chambers, are collected and manipulated. This collection is the outcome of a thorough and exhaustive survey of the available experimental data of hot-fire tests produced to date. Among the test cases reported in the literature, only those with a throat heat transfer that is not affected by laminar flow, evident soot deposition, or intended non-uniform propellant injection are collected. The heat transfer is typically measured in terms of wall heat flux and temperature. Sometimes the heat transfer coefficient, which is a combination of these two terms, is provided. Each collected heat transfer measurement is supplied with data relevant to the specific operative condition of the considered test case, as well as the configuration of the adopted thrust chamber and propellant injector. Among the different considered propellant combinations, most of the experiments are made burning oxygen-hydrogen or oxygen-kerosene. Experiments made using mildly heated and compressed air, although not a rocket propellant, are also considered because of their relevance to the problem of interest. The collected dataset, called the primary dataset, is numerically elaborated to create a secondary dataset that is more thorough and consistent than the primary one. In fact, also thanks to the adoption of a suitable hot-gas flow modeling, the secondary dataset contains elaborated data that are not always available in the selected open-literature as well as the non-dimensional numbers that are associated with the heat transfer and are typically used in regression rules, like the Nusselt and the Stanton numbers. The datasets presented in this manuscript are discussed and used to find heat transfer regressions in the research manuscript “Overview and analysis of the experimentally measured throat heat transfer in liquid rocket engine thrust chambers”, Acta Astronaut. 184 (2021), 46-58 [1].
机译:从开放文献中获取的大约500个实验传热数据,并与液体火箭发动机推力室的最热招募的区域(即喉部区域)相关的数据。该系列是对迄今为止产生的热火试验的可用实验数据进行彻底和详尽的调查结果。在文献中报道的测试案例中,仅收集具有喉部传热的喉部传热,并且收集了不受层流量的传热,显着的烟灰沉积或预均匀的非均匀推进剂注入的那些。通常在壁热通量和温度方面测量传热。有时,提供了热传递系数,即这是这两个术语的组合。每个收集的传热测量都提供与所考虑的测试用例的特定操作条件相关的数据,以及采用的推力室和推进剂注射器的配置。在不同考虑的推进剂组合中,大部分实验都是燃烧氧 - 氢或氧煤油的。由于它们与感兴趣的问题的相关性,也考虑了使用温和加热和压缩空气的实验虽然不是火箭推进剂。数值详细地详细说明了所收集的数据集,称为主数据集以创建比主要数据集更彻底和始终如一的辅助数据集。事实上,还要由于采用了合适的热气流建模,辅助数据集包含在所选择的开放文献中并不总是可用的详细数据以及与传热和传热相关联的不尺寸数字通常用于回归规则,如nusselt和斯坦顿数。讨论了本手稿中的数据集并用于在研究手稿中找到热传递回归“概述和分析液体火箭发动机推力室的实验测量喉部传热”,Acta Astronaut。 184(2021),46-58 [1]。

著录项

  • 期刊名称 Data in Brief
  • 作者

    Marco Pizzarelli;

  • 作者单位
  • 年(卷),期 2021(-1),-1
  • 年度 2021
  • 页码 -1
  • 总页数 7
  • 原文格式 PDF
  • 正文语种
  • 中图分类
  • 关键词

    机译:液体火箭发动机;热气侧传热;推力室喉咙;实验热转印;NUSELET和Stanton数字;
  • 入库时间 2022-08-21 12:24:30

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