Experimental investigations of mixing characteristics in model rotating detonation engine geometries

This work examines the mechanisms of reactant mixing in a model Rotating Detonation Engine (RDE) geometry. RDEs are emerging as one of the highest potential applications for achieving Pressure Gain Combustion (PGC). Reactant mixing has been identified as a crucial component of efficient RDE operation. Therefore, a scaled model of a typical RDE engine geometry was examined in a water tunnel using Planar Laser Induced Fluorescence (PLIF) to observe the influence of fuel injection position, confinement geometry, and blowing ratio on the mixing characteristics and quality of mixing

On the response of a rectangular supersonic jet to a near-field located parallel flat plate

In this paper, the flow and acoustic fields of a rectangular over-expanded supersonic jet interacting with a parallel plate are investigated using compressible LES. The jet exits from a converging diverging rectangular nozzle of aspect ratio 2 with a design Mach number 1.5. Four simulations with four different distances between the lower inner lip of the rectangular jet in the minor axis plane and the plate ranging from 0 to 3 equivalent diameters are performed. The geometry of the nozzle, the positions of the plate, and the exit conditions are chosen in order to match those in an experimental study conducted at the University of Cincinnati. Snapshots and mean velocity fields are first presented. A good agreement with the PIV experimental measurements is found. The overall sound pressure levels are then plotted along the minor and major axis. In a previous paper, the corresponding free jet has been found to undergo a strong flapping motion in the minor axis plane due to the screech feedback mechanism. In the present study, it is seen that the intensity of the screech feedback mechanism increases for some distances from the ground and decreases for some others, as compared to the corresponding free jet. A study of the jets shear-layers is then proposed, first by looking at two points space-time cross correlations of the axial velocity. The convection of the turbulent flow structures is thus studied. Then, two points space-time cross correlations of the pressure along the jets shear-layers are proposed and an amplification of the aeroacoustic feedback mechanism leading to screech noise is observed in the lower jet shear-layers for two cases. It is also observed that the screech feedback mechanism establishes mainly between the nozzle lips and the end of the tenth shock cell. The acoustic loading on the plate is finally studied. As pointed out in a previous study, the flapping motion of the jet at the screech frequency seems to yield to an asymmetric organization of the Mach wave radiation also at the screech frequency. Those organized Mach waves impinge on the plate, are reflected, and propagate back towards the jet, exciting the shear-layer at the screech frequency. This will amplify the screech mechanism in the lower jet shear-layer. However, this amplification happens only for some nozzle-to-plate distances. The mechanism leading to this behaviour is explained

Temperature effects on the aerodynamic and acoustic fields of a rectangular supersonic jet

In the first part of the paper, a modified artificial dissipation mechanism permitting to perform Large-Eddy Simulations of highly compressible flows is proposed. This dissipation mechanism is evaluated using one linear 2-D test case and two non-linear 2-D test cases. In the second part, the flow and acoustic near-field of rectangular supersonic jets are explored using compressible LES based on this modified artificial dissipation mechanism. At the exit of a converging diverging rectangular nozzle of aspect ratio 2 and of design Mach number 1.5, the jets are overexpanded. Four simulations with four different temperature ratios ranging from 1 to 3 are performed in order to characterize the effect of the temperature on the aerodynamic and aeroacoustic fields of the jets. The geometry of the nozzle and the exit conditions are chosen in order to match those in the experimental study conducted at the University of Cincinnati. It is shown that the total number of cells in the shock cell structure decreases with the increase of the temperature ratio. However, the temperature does not influence the size of the first shock cell and the linear decrease of the shock cell size in the downstream direction. The Overall Sound Pressure Levels are then plotted along the minor and major axis. It is seen that the intensity of the screech feedback mechanism increases with the Temperature Ratio. Moreover, for JetTR25 and JetTR3, the strong flapping motion of the jet along the minor axis due to the screech feedback mechanism seems to yield to an asymmetric organization of the Mach wave radiation. The convection velocity of the turbulent structures in the jet shear layers along the minor axis is then studied. Once normalized by the jet exit velocity, the convection velocity is shown to decrease with the jet temperature ratio. In the last part of the paper, the near- and far-field acoustic are studied. In the near-field, screech tones which frequencies are consistent with both experimental data and a theoretical model are observed. In the far-field, four acoustic components typical of non-ideally supersonic jets are observed, namely the screech noise, the broadband shock-associated noise, the mixing noise and the Mach wave noise. Their directivities and frequencies are in agreement with experimental results and models

Impaired aortic distensibility and elevated central blood pressure in Turner Syndrome:a cardiovascular magnetic resonance study

Abstract Background Women with Turner Syndrome have an increased risk for aortic dissection. Arterial stiffening is a risk factor for aortic dilatation and dissection. Here we investigate if arterial stiffening can be observed in Turner Syndrome patients and is an initial step in the development of aortic dilatation and subsequent dissection. Methods Fifty-seven women with Turner Syndrome (48 years [29–66]) and thirty-six age- and sex-matched controls (49 years [26–68]) were included. Distensibility, blood pressure, carotid-femoral pulse wave velocity (PWV), the augmentation index (Aix) and central blood pressure were determined using cardiovascular magnetic resonance, a 24-h blood pressure measurement and applanation tonometry. Aortic distensibility was determined at three locations: ascending aorta, transverse aortic arch, and descending aorta. Results Mean aortic distensibility in the descending aorta was significantly lower in Turner Syndrome compared to healthy controls (P = 0.02), however, this was due to a much lower distensibility among Turner Syndrome with coarctation, while Turner Syndrome without coarctation had similar distensibility as controls. Both the mean heart rate adjusted Aix (31.4% vs. 24.4%; P = 0.02) and central diastolic blood pressure (78.8 mmHg vs. 73.7 mmHg; P = 0.02) were higher in Turner Syndrome compared to controls, and these indices correlated significantly with ambulatory night-time diastolic blood pressure. The presence of aortic coarctation (r = − 0.44, P = 0.005) and a higher central systolic blood pressure (r = − 0.34, P = 0.03), age and presence of diabetes were inversely correlated with aortic distensibility in TS. Conclusion Aortic wall function in the descending aorta is impaired in Turner Syndrome with lower distensibility among those with coarctation of the aorta, and among all Turner Syndrome higher Aix, and elevated central diastolic blood pressure when compared to sex- and age-matched controls. Trial registration The study was registered at ClinicalTrials.gov (#NCT01678274) on September 3, 2012

How Chevrons Decrease Broadband Jet Noise in Cruise.

Broadband shock noise is reduced because chevrons increase the shear-layer thickness between the flight stream and the jet. It is shown experimentally and with results of a theory of Michalke that this is directly related to a reduction of the axial variation of the pressure amplitudes in the mean flow field of the jet. Since broadband shock noise is the result of an interaction between the turbulence in a jet and the axial variation of the mean flow field the chevrons yield a reduced noise emission. The effects of chevrons on the sound emission from nozzles operating at underexpanded conditions are demonstrated with experimental results. In a cruise condition with a flight Mach number 0.85, the chevron nozzle yields a lower broadband shock noise. It is shown experimentally as well as with the theory of Michalke that chevrons reduce the shock cell spacing, which explains the higher frequencies for broadband shock noise