Experimental and Numerical Similitude Study Using a Novel Turbocompressor Test Facility Operating With Helium-Neon Gas Mixtures

2021 ◽  
Author(s):  
Maxime Podeur ◽  
Damian M. Vogt
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Specific Heat ◽  
Gas Mixtures ◽  
Test Facility ◽  
Negative Contribution ◽  
Specific Heat Ratio ◽  
Neon Gas ◽  
The Individual ◽  
Helium Neon

Abstract A novel turbocompressor test facility has been designed for helium-neon gas mixtures and its specific features are presented. To account for the heat transfer originating from the motor coolant, a surrogate model has been derived. By combining these results with additional numerical ones, a similitude study is conducted quantifying the individual effects and contributions on efficiency of the Reynolds number, tip Mach number and specific heat ratio. Decoupling the effect of the different parameters shows that their respective contribution on efficiency variation is highly correlated to the Reynolds number actual value. The negative contribution of the tip Mach number and the positive effect of Reynolds number can be used to explain the efficiency variation with increasing tip Mach number. Specific heat ratio variation leads to minor changes in polytropic efficiency except at low tip Mach numbers.

Effects of Mach Number and Specific Heat Ratio on Low-Reynolds-Number Airfoil Flows

AIAA Journal ◽  
2015 ◽  
Vol 53 (6) ◽  
pp. 1640-1654 ◽  
Author(s):  
Masayuki Anyoji ◽  
Daiju Numata ◽  
Hiroki Nagai ◽  
Keisuke Asai
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Specific Heat ◽  
Low Reynolds Number ◽  
Specific Heat Ratio ◽  
Low Reynolds ◽  
Low Reynolds Number Airfoil

The Experimental Studies of Improving the Aerodynamic Performance of a Turbine Exhaust System

2014 ◽  
Vol 137 (1) ◽  
Author(s):  
Stephen Guillot ◽  
Wing F. Ng ◽  
Hans D. Hamm ◽  
Ulrich E. Stang ◽  
Kevin T. Lowe
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Experimental Studies ◽  
Experimental Result ◽  
Test Facility ◽  
Test Rig ◽  
Blow Down ◽  
Recovery Coefficient ◽  
Scale Test ◽  
Turbine Exhaust

Analysis and testing were conducted to optimize an axial diffuser–collector gas turbine exhaust. Two subsonic wind tunnel facilities were designed and built to support this program. A 1/12th scale test rig enabled rapid and efficient evaluation of multiple geometries. This test facility was designed to run continuously at an inlet Mach number of 0.41 and an inlet hydraulic diameter-based Reynolds number of 3.4 × 105. A 1/4th geometric scale test rig was designed and built to validate the data in the 1/12th scale rig. This blow-down rig facilitated testing at a nominally equivalent inlet Mach number, while the Reynolds number was matched to realistic engine conditions via back pressure. Multihole pneumatic pressure probes, particle image velocimetry (PIV), and surface oil flow visualization were deployed in conjunction with computational tools to explore physics-based alterations to the exhaust geometry. The design modifications resulted in a substantial increase in the overall pressure recovery coefficient of +0.07 (experimental result) above the baseline geometry. The optimized performance, first measured at 1/12th scale and obtained using computational fluid dynamics (CFD) was validated at the full scale Reynolds number.

Mechanism of Scintillation of Helium, Helium-Argon, and Helium-Neon Gas Mixtures Excited by Alpha Particles

1968 ◽  
Vol 165 (1) ◽  
pp. 225-230 ◽  
Author(s):  
SHINZOU KUBOTA ◽  
TAN TAKAHASHI ◽  
TADAYOSHI DOKE
Keyword(s):  
Gas Mixtures ◽  
Alpha Particles ◽  
Neon Gas ◽  
Helium Neon

scholarly journals Half widths of neutron spectra in dense helium-neon gas mixtures

1993 ◽  
Vol 48 (3) ◽  
pp. 1948-1959 ◽  
Author(s):  
P. Westerhuijs ◽  
L. A. de Graaf ◽  
I. M. de Schepper
Keyword(s):  
Gas Mixtures ◽  
Neutron Spectra ◽  
Neon Gas ◽  
Helium Neon

Optimisation and analysis of efficiency for contra-rotating propellers for high-altitude airships

2019 ◽  
Vol 123 (1263) ◽  
pp. 706-726
Author(s):  
J. Tang ◽  
X. Wang ◽  
D. Duan ◽  
W. Xie
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
High Altitude ◽  
Reference Frames ◽  
Lift Coefficient ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Optimization Approach ◽  
Axial Distance ◽  
The Individual

ABSTRACTAn improved variational optimization approach is established to optimize and analyse the propulsion efficiency of the high-altitude contra-rotating propellers for high-altitude airships based on the Vortex Lattice Lifting Line Method. The optimum radial circulation distribution, chord and pitch distribution are optimized under the maximum lift-to-drag ratio of aerofoils. To consider the effects of the actual Reynolds number and the Mach number of each aerofoil section, aerodynamics such as lift coefficient, drag coefficient and lift-to-ratio are obtained by interpolating a CFD database, which is established by numerical simulations under different Reynolds number, Mach number and angles-of-attack. The improved method is verified by validation cases on a high-altitude CRP using the three-dimensional steady Reynolds-averaged Navier-Stokes solver and moving reference frames technique. The optimization results of thrust, torque and efficiency for both the individual front/rear propeller and CRP are shown to agree reasonably well with the CFD results. Using the improved approach, the influence of blade numbers, diameter, rotation speeds, axial distance and torque ratio on the optimum efficiency of CRPs is illustrated in detail by conducting parametric studies.

Heat Transfer and Aerodynamics of a High Rim Speed Turbine Nozzle Guide Vane Tested in the RAE Isentropic Light Piston Cascade (ILPC)

1990 ◽  
Author(s):  
S. P. Harasgama ◽  
E. T. Wedlake
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Mach Number ◽  
Guide Vane ◽  
Weak Shock ◽  
Test Facility ◽  
Computational Techniques ◽  
Nozzle Guide ◽  
Annular Cascade ◽  
Nozzle Guide Vanes

Detailed heat transfer and aerodynamic measurements have been made on an annular cascade of highly loaded nozzle guide vanes. The tests were carried out in an Isentropic Light Piston test facility at engine representative Reynolds number, Mach number and gas-to-wall temperature ratio. The aerodynamics indicate that the vane has a weak shock at 65–70% axial chord (mid span) with a peak Mach number of 1.14. The influence of Reynolds number and Mach number on the Nusselt number distributions on the vane and endwall surfaces are shown to be significant. Computational techniques are used for the interpretation of test data.

Heat Transfer and Aerodynamics of a High Rim Speed Turbine Nozzle Guide Vane Tested in the RAE Isentropic Light Piston Cascade (ILPC)

1991 ◽  
Vol 113 (3) ◽  
pp. 384-391 ◽  
Author(s):  
S. P. Harasgama ◽  
E. T. Wedlake
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Mach Number ◽  
Guide Vane ◽  
Weak Shock ◽  
Test Facility ◽  
Computational Techniques ◽  
Nozzle Guide ◽  
Annular Cascade ◽  
Nozzle Guide Vanes

Detailed heat transfer and aerodynamic measurements have been made on an annular cascade of highly loaded nozzle guide vanes. The tests were carried out in an Isentropic Light Piston test facility at engine representative Reynolds number, Mach number, and gas-to-wall temperature ratio. The aerodynamics indicate that the vane has a weak shock at 65–70 percent axial chord (midspan) with a peak Mach number of 1.14. The influence of Reynolds number and Mach number on the Nusselt number distributions on the vane and endwall surfaces are shown to be significant. Computational techniques are used for the interpretation of test data.

The Experimental Studies of Improving the Aerodynamic Performance of a Turbine Exhaust System

2014 ◽  
Author(s):  
Stephen Guillot ◽  
Wing F. Ng ◽  
Hans D. Hamm ◽  
Ulrich E. Stang ◽  
Kevin T. Lowe
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Experimental Studies ◽  
Experimental Result ◽  
Test Facility ◽  
Test Rig ◽  
Blow Down ◽  
Recovery Coefficient ◽  
Scale Test ◽  
Turbine Exhaust

Analysis and testing was conducted to optimize an axial diffuser-collector gas turbine exhaust. Two subsonic wind tunnel facilities were designed and built to support this program. A 1/12th scale test rig enabled rapid and efficient evaluation of multiple geometries. This test facility was designed to run continuously at an inlet Mach number of 0.41 and an inlet hydraulic diameter-based Reynolds number of 3.4 × 105. A 1/4th geometric scale test rig was designed and built to validate the data in the 1/12th scale rig. This blow-down rig facilitated testing at a nominally equivalent inlet Mach number, while the Reynolds number was matched to realistic engine conditions via back pressure. Multi-hole pneumatic pressure probes, particle image velocimetry and surface oil flow visualization was deployed in conjunction with computational tools to explore physics-based alterations to the exhaust geometry. The design modifications resulted in a substantial increase in the overall pressure recovery coefficient of +0.07 (experimental result) above the baseline geometry. The optimized performance, first measured at 1/12th scale and obtained using CFD was validated at the full scale Reynolds number.

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