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对于沟槽壁结构的氢氧火箭发动机推力室的液氢冷却特性,包括非对称的热效应在内尚未进行充分的验证。为了获得在近临界和超临界条件下的液氫传热特性,将试验设备和推力室设计得使冷却剂的流量和压力的变化不取决于燃烧条件。周向平均传热系数h_1是根椐试验数据用稳态二维热传导模型确定的。局部的努塞尔数Nu.exp与一些典型的相关式做了比较。Nu.exp和预计的Nu.cal很不一致。与以前的相关式不一致的主要原因可能是非对称加热的影响。因此,作者提出了一个初始的相关式,该相关式在近临界和超临界的条件下与现有数据相关良好,误差在±20%范围内。可推荐该相关式作为沟槽壁结构再生冷却的高能氫氧火箭推力室的设计方程。
Liquid-hydrogen cooling characteristics of the thrust chamber of oxyhydrogen rocket engines with trench walls, including asymmetric thermal effects, have not been fully validated. In order to obtain liquid hydrogen heat transfer characteristics in near-critical and supercritical conditions, the test equipment and thrust chambers are designed so that the change in coolant flow and pressure does not depend on the combustion conditions. The average circumferential heat transfer coefficient, h_1, is determined from the steady-state two-dimensional heat transfer model for the test data. The local Nusselt Nu.exp is compared with some typical correlations. Nu.exp and expected Nu.cal are very inconsistent. The main reason for the inconsistency with the previous correlation may be the effect of asymmetric heating. Therefore, the authors propose an initial correlation that is well correlated with available data under near-critical and supercritical conditions with an error of ± 20%. This correlation equation can be recommended as the design equation for the high energy oxyhydrogen rocket thrust chamber that is regenerated and cooled by the trench wall structure.