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Rocket Nozzle Thrust and Flow Field Measurements Using Particle Image Velocimetry

机译：使用粒子图像测速仪的火箭喷嘴推力和流场测量

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摘要

A force balance can provide limited information on the loads generated by the flow through a nozzle, such as the magnitude and direction of time average loads, but the flow features responsible for generating them remain elusive. In this study, a comparison of steady axial thrust measurements is carried out between a conventional load cell and a flow survey by using particle image velocimetry (PIV) and pressure probes to validate that the latter method can be used for thrust measurements as well as to investigate the flow field. A Mach 4 convergent-divergent nozzle with 12.7-mm throat diameter was tested by using compressed air at a range of substantially over-expanded conditions using jet stagnation pressures of 4 to 7.5 times the nozzle exit ambient pressure. The nozzle supply line was fitted with an electric heater generating stagnation temperatures in the range of 300 to 450 K. Using a load cell, the thrust produced by the nozzle was measured at each condition. The flow field downstream of the nozzle was surveyed by using a pressure rake and 2-dimensional PIV. Combining the data from both flow surveys, static pressure, and axial flow velocity, momentum flux as well as static pressure contribution to thrust were calculated. A comparison between the thrust obtained by the 2 methods verified that PIV and pressure surveys could be used to determine the time-averaged thrust of a nozzle to within 6% of the load cell reading.
机译：力平衡可以提供关于通过喷嘴的流动所产生的负荷的有限信息，例如时间平均负荷的大小和方向，但是负责产生它们的流动特征仍然难以捉摸。在这项研究中，通过使用粒子图像测速（PIV）和压力探头对常规称重传感器和流量测量之间的稳态轴向推力测量进行了比较，以验证后一种方法可用于推力测量以及调查流场。通过使用压缩空气，在基本上过分膨胀的条件下，使用喷嘴出口环境压力的4到7.5倍的喷射停滞压力，对喉部直径为12.7 mm的Mach 4收缩喷嘴进行测试。喷嘴供应管线上装有电加热器，该加热器产生停滞温度在300到450 K之间。使用测力传感器，在每种条件下测量喷嘴产生的推力。通过使用压力耙和二维PIV对喷嘴下游的流场进行了测量。结合两个流量调查的数据，计算出静压力和轴向流速，动量通量以及静压力对推力的贡献。通过两种方法获得的推力之间的比较证明，可以使用PIV和压力测量来确定喷嘴的时间平均推力到称重传感器读数的6％以内。

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