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National Aeronautics and Space Administration

Washington, DC 20546–0001

Available electronically at http://gltrs.grc.nasa.gov

June 1984

NASA CR–174624

Garrett 21–4804

E–None

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NAS3–22110

238

Dilution Jet Mixing Phase II Program

R. Srinivasan, E. Coleman, and K. Johnson

Dilution-zone; Jet-mixing; Combustion

Unclassified -Unlimited

Subject Category: 00

Garrett Turbine Engine Company

A Division of the Garrett Corporation

Phoenix, Arizona 85010

Project Manager, James D. Holdeman, NASA Lewis Research Center, Cleveland, Ohio 44135.

The main objectives of the NASA Dilution Jet Mixing Phase II were to quantify the mixing of opposed rows of jets

(two-sided injection) in a confined cross-flow. Parametric tests were performed to determine the effects of the following

on jet mixing characteristics: 1) Orifice spacing to diameter ratio, S/D; 2) Duct height to diameter ratio, H0/D; 3) Jet-tomainstream momentum flux ratio, J; 4) Non-uniform mainstream profile upstream of the dilution orifices; and 5) Flow

area convergence. The general conclusions derived from the Phase II efforts are: 1) Jet penetrations for two-sided

injections are less than that for single-sided injections (investigated in Phase I), but the jet spreading rates are faster for a

given momentum ratio and orifice plate; 2) Flow area convergence generally enhances mixing. The mixing characteristics with asymmetric and symmetric convergence are similar; 3) For constant momentum ratio, the optimum S/H0 with

in-line injections is one-half of the optimum value for single-sided injections. For staggered injections, the optimum

S/H0 is twice the optimum value for single-sided injection; and 4) The correlations developed in this program predict the

temperature distributions within first order accuracy. They provide a useful tool for predicting jet trajectory and temperature profiles in the dilution zone with two-sided jet injections.