High-Frequency Effects in the Aspirating Probe

2006 ◽  
Vol 129 (4) ◽  
pp. 842-851
Author(s):  
S. J. Payne ◽  
A. J. W. Moxon

The aspirating probe has recently been successfully used to measure entropy within a turbomachine; however, it was found that its sensitivity to total pressure and total temperature fluctuations was significantly altered at high frequencies. If the aspirating probe is to be used to measure unsteady flow fields accurately, these high-frequency effects must be better understood. The analysis of this behavior presented here shows that there are three effects that must be considered: the frequency response of the hot wires, the presence of Mach number fluctuations inside the probe, and the change in heat transfer from the hot wires at high frequencies. A theoretical analysis of the first effect has provided a correction factor that can be used for any hot wire, dependent solely on the baseline heat transfer ratio, the overheat ratio, and the time constant of the hot wires. The second and third effects have been examined numerically, since no theoretical solution is known to exist. The Mach number fluctuations are found to be well predicted by a simple one-dimensional solver and to show a variation of ±2.4% in Mach number at the hot-wire plane for the geometry and flow field considered here. The variation in heat transfer with frequency is found to be negligible at high overheat ratios, but significant at overheat ratios below ∼0.4. Coefficients that determine how the measured total pressure and total temperature depend on the actual total pressure, total temperature, and Mach number have been derived, and these show significant variation with the values of the two overheat ratios. Using synthetic data, based on previous experimental data, the effects on the probe measurement accuracy are analyzed. This shows that the amplitudes of total pressure and total temperature are reduced. At widely spaced overheat ratios, the amplitudes are reduced by similar amounts, but at smaller spacing the reductions become dissimilar, resulting in highly erroneous entropy∕R measurements. High-frequency effects thus have a significant effect on the performance of the aspirating probe and should be carefully considered when using it in a highly unsteady flow field.

1995 ◽  
Vol 117 (4) ◽  
pp. 642-649 ◽  
Author(s):  
D. E. Van Zante ◽  
K. L. Suder ◽  
A. J. Strazisar ◽  
T. H. Okiishi

The aspirating probe originally designed by Epstein and Ng at MIT was modified by replacing the two platinum-coated tungsten hot wires normally used with platinum–iridium alloy wires. The resulting improved unsteady total pressure and total temperature resolution of the modified probe is demonstrated. Flowfield measurements were made downstream of NASA Rotor 37 for a part-speed operating condition to test the performance of the probe. Time-resolved blade-to-blade total temperature and total pressure as calculated from the two platinum–iridium hot-wire voltages are shown. The flowfield measurements are compared with independent measurements of total pressure with high response transducers and total temperature calculated from laser anemometer measurements. Limitations of a more often used unsteady temperature data reduction method, which involves only one aspirating probe hot-wire voltage and a high-response pressure measurement, are discussed.


Author(s):  
Dale E. Van Zante ◽  
Kenneth L. Suder ◽  
Anthony J. Strazisar ◽  
Theodore H. Okiishi

The aspirating probe originally designed by Epstein and Ng at MIT was modified by replacing the two platinum coated tungsten hot wires normally used with platinum iridium alloy wires. The resulting improved unsteady total pressure and total temperature resolution of the modified probe is demonstrated. Flowfield measurements were made downstream of NASA Rotor 37 for a part speed operating condition to test the performance of the probe. Time resolved blade-to-blade total temperature and total pressure as calculated from the two platinum iridium hot wire voltages are shown. The flowfield measurements are compared with independent measurements of total pressure with high response transducers and total temperature calculated from laser anemometer measurements. Limitations of a more often used unsteady temperature data reduction method which involves only one aspirating probe hot wire voltage and a high-response pressure measurement are discussed.


2012 ◽  
Vol 571 ◽  
pp. 701-705
Author(s):  
Hui Yang ◽  
Feng Li ◽  
Bai Gang Sun ◽  
Dan Dan Tian ◽  
Yao Ying Song ◽  
...  

Structures of liquid-fuel injection in supersonic crossflow is studied experimentally. Schemes of flush-wall injector and aviation kerosene are selected. The conditions of the supersonic freestream are kept constant (total pressure is 0.5MPa, total temperature is 500K and Mach number is 2) and the diameter of the injector is fixed as 0.5mm, while seven scenarios of injection angle and three scenarios of injection driven pressure are discussed. Both methods of schlieren and planar laser induced fluorescence (PLIF) techniques are implemented to obtain the visual images of the liquid-fuel injection. The penetration height of fuel is analyzed quantitatively with the aid of Photoshop and Origin. The results serve not only the future computational simulation but also combined scheme of flush-wall injector and other combustor configurations.


1962 ◽  
Vol 29 (4) ◽  
pp. 609-614 ◽  
Author(s):  
C. J. Cremers ◽  
E. R. G. Eckert

Previous studies by flow visualization have indicated that the flow through a duct of triangular cross section is in its characteristics quite different from flow through a duct with circular cross section. They revealed among others that purely laminar flow exists in the corners of the duct even though the bulk of the fluid moves in turbulent motion. Heat-transfer measurements in such a duct appear to indicate that the turbulent transport in the direction of the height of the duct is considerably smaller than expected from circular tube measurements. The present paper reports the measurements of turbulent correlations for turbulent flow through such a duct. These measurements have been made with hot wires of very small dimensions. They again reveal the existence of a laminar corner region. In the bulk of the fluid, the differences of the correlations to those in a round tube turned out to be smaller than originally suspected.


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