Results of Experiments on Quasi-Isentropic Compression of Deuterium and Helium to Extreme Pressures of ~3000 GPa

2018 ◽  
Keyword(s):  
Isentropic Compression

Magnetically driven isentropic compression to multimegabar pressures using shaped current pulses on the Z accelerator

2005 ◽  
Vol 12 (5) ◽  
pp. 056310 ◽  
Author(s):  
Jean-Paul Davis ◽  
Christopher Deeney ◽  
Marcus D. Knudson ◽  
Raymond W. Lemke ◽  
Timothy D. Pointon ◽  
...  
Keyword(s):  
Isentropic Compression ◽  
Current Pulses

Numerical Study of Magnetically Driven Isentropic Compression Experiments on PTS

2018 ◽  
Vol 46 (10) ◽  
pp. 3478-3486
Author(s):  
Yang Zhang ◽  
Zhaohui Zhang ◽  
Guilin Wang ◽  
Ning Ding ◽  
Chuang Xue
Keyword(s):  
Numerical Study ◽  
Isentropic Compression

scholarly journals Quasi-isentropic compression of vapor-deposited hexanitroazobenzene (HNAB): Experiments and analysis

2018 ◽  
Author(s):  
C. D. Yarrington ◽  
A. S. Tappan ◽  
P. E. Specht ◽  
R. Knepper
Keyword(s):  
Isentropic Compression

Influence of Gas-to-Wall Temperature Ratio on By-Pass Transition

2017 ◽  
Author(s):  
Tânia S. Cação Ferreira ◽  
Tony Arts
Keyword(s):  
Heat Flux ◽  
Wall Temperature ◽  
Analog Circuits ◽  
Guide Vane ◽  
Operating Conditions ◽  
Wall Heat Flux ◽  
Bypass Transition ◽  
Temperature Ratio ◽  
Isentropic Compression ◽  
Pressure Transducers

An investigation of thermal effects on bypass transition was conducted on the highly-loaded turbine guide vane LS89 in the short-duration isentropic Compression Tube (CT-2) facility at the von Karman Institute for Fluid Dynamics (VKI). Measurements from high response surface-mounted thin films coupled with analog circuits provided the time-resolved wall heat flux history whereas pneumatic probes, differential pressure transducers and thermocouples allowed the accurate definition of the inlet and outlet flow conditions. The gas-to-wall temperature ratio, ranging from 1.11 to 1.55, was varied by changing the inlet total temperature. The isentropic exit Mach number ranged from 0.90 to 1.00 and the global freestream turbulence intensity value was set at 0.8, 3.9 and 5.3%. The isentropic exit Reynolds number was kept at 106. The onset of transition was tracked through the wall heat flux signal fluctuations. Within the present operating conditions, no significant effect of the gas/wall temperature ratio was put in evidence. At the present (design) transonic exit conditions, the local free-stream pressure gradient appears to remain the main driver of the onset of transition. A wider range of operating conditions must be considered to draw final conclusions.

Analytical isentropic compression model and its application in a laser-direct-driven ramp compression experiment

2017 ◽  
Author(s):  
Quanxi Xue ◽  
Shaoen Jiang ◽  
Zhebin Wang ◽  
Feng Wang ◽  
Huan Zhang
Keyword(s):  
Isentropic Compression ◽  
Compression Model

Wake-Induced Unsteady Stagnation-Region Heat Transfer Measurements

1994 ◽  
Vol 116 (1) ◽  
pp. 29-38 ◽  
Author(s):  
P. J. Magari ◽  
L. E. LaGraff
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Heat Transfer Rate ◽  
Transfer Rate ◽  
Edge Region ◽  
Isentropic Compression ◽  
Stagnation Region ◽  
Stagnation Line ◽  
Wide Range ◽  
Mach Numbers

An experimental investigation of wake-induced unsteady heat transfer in the stagnation region of a cylinder was conducted. The objective of the study was to create a quasi-steady representation of the stator/rotor interaction in a gas turbine using two stationary cylinders in crossflow. In this simulation, a larger cylinder, representing the leading-edge region of a rotor blade, was immersed in the wake of a smaller cylinder, representing the trailing-edge region of a stator vane. Time-averaged and time-resolved heat transfer results were obtained over a wide range of Reynolds number at two Mach numbers: one incompressible and one transonic. The tests were conducted at Reynolds numbers, Mach numbers, and gas-to-wall temperature ratios characteristic of turbine engine conditions in an isentropic compression-heated transient wind tunnel (LICH tube). The augmentation of the heat transfer in the stagnation region due to wake unsteadiness was documented by comparison with isolated cylinder tests. It was found that the time-averaged heat transfer rate at the stagnation line, expressed in terms of the Frossling number (Nu/Re), reached a maximum independent of the Reynolds number. The power spectra and cross-correlation of the heat transfer signals in the stagnation region revealed the importance of large vortical structures shed from the upstream wake generator. These structures caused large positive and negative excursions about the mean heat transfer rate in the stagnation region.

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