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Technical Memorandum

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National Aeronautics and Space Administration

Lewis Research Center

Cleveland, Ohio 44135–3191

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National Aeronautics and Space Administration

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

July 1992

NASA TM–105694

AIAA–92–3090

E–7082

WU–537–02–20–00

12

A03

Experimental Study of Cross-Stream Mixing in a Rectangular Duct

D.S. Liscinsky, B. True, A. Vranos, and J.D. Holdeman

Dilution; Jet mixing flow; Gas turbine; Combustion chamber; Emissions

Unclassified -Unlimited

Subject Category: 07

Prepared for the 28th Joint Propulsion Conference and Exhibit cosponsored by the AIAA, SAE, ASME, and ASEE,

Nashville, Tennessee, July 6–8, 1992. D.S. Liscinsky and B. True, United Technologies Research Center, East Hartford,

Connecticut 06108; A. Vranos, A.B. Research Associates, South Windsor, Connecticut, 06074; J.D. Holdeman, NASA

Lewis Research Center. Responsible person, J.D. Holdeman, (216) 433–5846.

An experimental investigation of non-reacting cross-stream jet injection and mixing in a rectangular duct has been

conducted with application to a low emissions combustor. Planar digital imaging was used to measure concentration

distributions in planes perpendicular to the duct axis. Mixing rate was measured for 45° slanted slot and round orifice

injectors. It is shown that (1) mixing improves continuously with increasing momentum-flux ratio, (2) given a

momentum-flux ratio, there is an optimum, orifice spacing, (3) mixing is more dependent on injector geometry than

mass flow ratio, (4) mixing is influenced by relative slot orientation, and (5) jet structure is different for round holes

and slanted slots injectors. The utility of acquiring multipoint fluctuating properties of the flow field is also demonstrated.