Acoustic control of free jet mixing

1985 ◽  
Author(s):  
J. LEPICOVSKY ◽  
K. AHUJA ◽  
W. BROWN ◽  
P. MORRIS
Keyword(s):  
Jet Mixing ◽  
Free Jet ◽  
Acoustic Control

Acoustic control of free jet mixing

1986 ◽  
Vol 2 (4) ◽  
pp. 323-330 ◽  
Author(s):  
J. Lepicovsky ◽  
K. K. Ahuja ◽  
W. H. Brown ◽  
P. J. Morris
Keyword(s):  
Jet Mixing ◽  
Free Jet ◽  
Acoustic Control

On the Correlation of Analytical and Experimental Free Shear Layer Similarity Profiles by Spread Rate Parameters

1971 ◽  
Vol 93 (3) ◽  
pp. 377-382 ◽  
Author(s):  
H. H. Korst ◽  
W. L. Chow
Keyword(s):  
Similarity Solutions ◽  
Free Shear Layer ◽  
Spread Rate ◽  
Empirical Parameter ◽  
Jet Mixing ◽  
Free Jet ◽  
Rate Of Spread ◽  
Profile Matching ◽  
Entire Flow ◽  
Definition Of

Analysis of turbulent isobaric free jet mixing normally requires the introduction of suitably formulated viscosity models. Similarity solutions can then be established which contain one empirical parameter. Such a parameter, however, not only describes the rate of spread of the mixing region, but also determines in detail the structure of the entire flow field. It is pointed out that this “spread rate parameter” σ depends on the selected viscosity model, the method of theoretical analysis, and the definition of profile matching. A comparison of different theoretical profiles can only be accomplished after these factors are properly recognized. Any attempts to contribute to the rather incomplete knowledge of the spread parameter must be cognizant of its dependence on the theoretical mixing model employed. This paper also establishes theoretical relations which allow comparison and consolidation of information based on different analytical concepts.

Influence of bypass ratio on subsonic and correctly expanded sonic co-flowing jets with finite lip thickness

2018 ◽  
Vol 233 (7) ◽  
pp. 2536-2548 ◽  
Author(s):  
S Thanigaiarasu ◽  
R Naren Shankar ◽  
E Rathakrishnan
Keyword(s):  
Total Pressure ◽  
Strong Influence ◽  
Static Pressure ◽  
Pressure Variation ◽  
Jet Mixing ◽  
Free Jet ◽  
Pressure Decay ◽  
Sonic Jet ◽  
Mach Numbers ◽  
Bypass Ratio

The effects of bypass ratio on co-flowing subsonic and correctly expanded sonic jet decay have been studied experimentally. Co-flowing jets with lip thickness 1.0 Dp (where Dp is the diameter of primary nozzle and is equal to 10 mm) with bypass ratios of around 0.7, 1.4, and 6.4 at primary jet exit Mach numbers 0.6, 0.8, and 1.0 have been analyzed. A single free jet equivalent to primary nozzle of the co-flowing nozzle was considered for comparison. Primary jet centerline total pressure decay, spread, and static pressure variation were investigated. The results show that the mixing of the high bypass ratio co-flowing jet with lip thickness 1.0 Dp is superior to low bypass ratio co-flowing jet. Both lip thickness and bypass ratio have a strong influence on the co-flowing jet mixing. Bypass ratio 6.3 experiences a significantly higher mixing than bypass ratio 0.7 and 1.4. Selected jets were also investigated computationally. The computations capture the salient flow physics and reproduce well with the experiments.

Nozzle Aspect Ratio Effect on Supersonic Elliptic Jet Mixing

2017 ◽  
Vol 139 (10) ◽  
Author(s):  
S. M. Aravindh Kumar ◽  
E. Rathakrishnan
Keyword(s):  
Aspect Ratio ◽  
Nozzle Exit ◽  
Pressure Gradients ◽  
Ratio Effect ◽  
Jet Mixing ◽  
Free Jet ◽  
Aspect Ratios ◽  
Nozzle Pressure ◽  
Axis Switching ◽  
The Waves

Nozzle aspect ratio effect on the mixing of Mach 2 elliptic free jet, issuing from convergent–divergent elliptic nozzles of aspect ratios 2, 3, and 4, in the presence of adverse and marginally favorable pressure gradients at the nozzle exit has been studied experimentally. The results show that AR4 jet enjoys better mixing than AR2 and AR3 jets at all nozzle pressure ratios. The AR2 and AR3 jets displayed axis switching, whereas there is no axis switching for AR4 jet. The shadowgraph shows that the waves in AR4 jet are weaker than those in AR2 and AR3 jets.

Acoustic control of combustor primary zone air-jet mixing

1992 ◽  
Author(s):  
P. VERMEULEN ◽  
V. RAMESH ◽  
B. SANDERS ◽  
J. ODGERS
Keyword(s):  
Jet Mixing ◽  
Air Jet ◽  
Acoustic Control ◽  
Primary Zone

Jet Flow Control Using Semi-Circular Corrugated Tab

2018 ◽  
Vol 0 (0) ◽  
Author(s):  
Sathish Kumar K ◽  
Senthilkumar Chidambaram
Keyword(s):  
Experimental Validation ◽  
Jet Flow ◽  
Blockage Ratio ◽  
Potential Core ◽  
Convergent Nozzle ◽  
Jet Mixing ◽  
Free Jet ◽  
Core Length ◽  
The Relationship ◽  
Subsonic Jet

Abstract This investigation aims to present the jet mixing characteristics and thrust variations of the subsonic jet employed with plain triangular tab and semi-circular corrugated tab by numerical simulation. A triangular tab with semi-circular corrugations is used in this regard at the exit plane of a convergent nozzle, to study the behavior of the jet and its structure. The near jet flow field is studied for different Mach numbers of 0.6, 0.8 and 1, and the comparisons were done for the jet employed with plain triangular tab. To validate the numerical results, experimental validation is carried out for 0.6 Mach jet. The thrust and the potential core length of any jet depend mainly on the percentage of blockage ratio. Since the relationship between the thrust and blockage ratio is such that, the blockage ratio increases, the thrust and the potential core length decreases and vice-versa. The blockage ratio is kept 8.27 % for both the corrugated and plain triangular tabs. From the results, it is found that the Potential core length of the free jet is cut down to 66 % by the jet employed with plain triangular tab, whereas it is 64.5 % for the corrugated tab enabled jet. It is also concluded that the corrugated tab enhances the thrust by 4.43 % for the same blockage ratio and increases potential core length by 3.33 % when compared with the plain triangular tab. This increase in thrust is there by an added advantage of this investigation.

Experimental studies of chemically reactive /F + H2/ flow in supersonic free jet mixing layers

1973 ◽  
Author(s):  
W. SHACKLEFORD ◽  
A. WITTE ◽  
J. BROADWELL ◽  
J. TROST ◽  
T. JACOBS
Keyword(s):  
Experimental Studies ◽  
Mixing Layers ◽  
Jet Mixing ◽  
Free Jet

Compressible Flow Ejectors: Part I—Development of a Finite-Difference Flow Model

1974 ◽  
Vol 96 (3) ◽  
pp. 272-281 ◽  
Author(s):  
K. R. Hedges ◽  
P. G. Hill
Keyword(s):  
Boundary Layer ◽  
Finite Difference ◽  
Initial Conditions ◽  
Length Distribution ◽  
Mixing Length ◽  
Jet Mixing ◽  
Free Jet ◽  
Finite Difference Approximations ◽  
Constant Diameter ◽  
Wide Range

A general method of calculating two-dimensional (plane and axisymmetric) mixing of a compressible jet in variable-area ducts has been developed. The method incorporates finite-difference approximations to the conservation equations, and is applicable to a wide range of Mach number, mass flow ratio, and initial conditions. The model was based on mixing length approximations deduced from boundary-layer and free-jet mixing for the upstream portion of the flow, and on a new mixing length distribution for the downstream zone which is entirely occupied by shear flow. The method has been tested and found satisfactory with existing data on boundary layer, constant-diameter duct entrance flow, constant-pressure jet mixing, and jet mixing in variable-area ducts. Part II of the paper describes tests of the method with new data from an experimental ejector study.

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