High-speed optical measurements of an underexpanded supersonic jet impinging on an inclined plate

2008 ◽  
Author(s):  
Adam Risborg ◽  
Julio Soria
Keyword(s):  
High Speed ◽  
Supersonic Jet ◽  
Optical Measurements ◽  
Inclined Plate ◽  
Underexpanded Supersonic Jet

Acoustic Phenomena from Correctly Expanded Supersonic Jet Impinging on Inclined Plate

AIAA Journal ◽  
2015 ◽  
Vol 53 (7) ◽  
pp. 2061-2067 ◽  
Author(s):  
Masahito Akamine ◽  
Yuta Nakanishi ◽  
Koji Okamoto ◽  
Susumu Teramoto ◽  
Takeo Okunuki ◽  
...  
Keyword(s):  
Supersonic Jet ◽  
Inclined Plate

Fuel Influence on Targeted Gas Turbine Combustion Properties: Part I — Detailed Diagnostics

2014 ◽  
Author(s):  
Thomas Mosbach ◽  
Victor Burger ◽  
Barani Gunasekaran
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Leading Edge ◽  
Operating Conditions ◽  
Optical Measurements ◽  
Test Facility ◽  
Research Centre ◽  
High Speed Imaging ◽  
Combustion Properties ◽  
First Results

The threshold combustion performance of different fuel formulations under simulated altitude relight conditions were investigated in the altitude relight test facility located at the Rolls-Royce plc. Strategic Research Centre in Derby, UK. The combustor employed was a twin-sector representation of an RQL gas turbine combustor. Eight fuels including conventional crude-derived Jet A-1 kerosene, synthetic paraffinic kerosenes (SPKs), linear paraffinic solvents, aromatic solvents and pure compounds were tested. The combustor was operated at sub-atmospheric air pressure of 41 kPa and air temperature of 265 K. The temperature of all fuels was regulated to 288 K. The combustor operating conditions corresponded to a low stratospheric flight altitude near 9 kilometres. The experimental work at the Rolls-Royce (RR) test-rig consisted of classical relight envelope ignition and extinction tests, and ancillary optical measurements: Simultaneous high-speed imaging of the OH* chemiluminescence and of the soot luminosity was used to visualize both the transient combustion phenomena and the combustion behaviour of the steady burning flames. Flame luminosity spectra were also simultaneously recorded with a spectrometer to obtain information about the different combustion intermediates and about the thermal soot radiation curve. This paper presents first results from the analysis of the weak extinction measurements. Further detailed test fuel results are the subject of a separate complementary paper [1]. It was found in general that the determined weak extinction parameters were not strongly dependent on the fuels investigated, however at the leading edge of the OH* chemiluminescence intensity development in the pre-flame region fuel-related differences were observed.

scholarly journals Conditional sampling analysis of high-speed schlieren movies of Mach wave radiation in a supersonic jet

2019 ◽  
Vol 145 (1) ◽  
pp. EL122-EL128 ◽  
Author(s):  
Masahito Akamine ◽  
Koji Okamoto ◽  
Susumu Teramoto ◽  
Seiji Tsutsumi
Keyword(s):  
High Speed ◽  
Supersonic Jet ◽  
Wave Radiation ◽  
Conditional Sampling ◽  
Mach Wave

Numerical study of the ejection properties of a jet flowing into flooded space

2020 ◽  
Author(s):  
A.Yu. Lutsenko ◽  
V.A. Kriushin
Keyword(s):  
Pressure Distribution ◽  
Nozzle Exit ◽  
Software Package ◽  
Numerical Study ◽  
Supersonic Jet ◽  
Underlying Surface ◽  
Ansys Fluent ◽  
Fluent Software ◽  
Underexpanded Supersonic Jet ◽  
Jet Axis

The purpose of the study was to carry out a numerical simulation of the interaction of an underexpanded supersonic jet flowing into a flooded space with a normally located obstacle, and with the underlying surface. We performed the calculations in the ANSYS Fluent software package and presented flow patterns. For the case when the obstacle is located normally to the axis of the jet, we compared the pressure distribution in the radial direction with experimental data and made a conclusion about the changes in the integral load on the wall with a change in the distance to the nozzle exit. For the case when the obstacle is parallel to the jet axis, we presented the pressure distribution along the wall in the plane of symmetry, estimated the relative net force acting on the underlying surface, analyzed the nature of its change at various values of the off-design coefficient, the Mach number on the nozzle exit and the distance to the jet axis.

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