Measuring of a Fuel Injector in a Supersonic Air Stream

Liviu-Constantin Stan; Ioan Calimanescu; Nicolae Buzbuchi

doi:10.1117/12.823711

7 January 2009 Measuring of a fuel injector in a supersonic air stream

Liviu-Constantin Stan, Ioan Calimanescu, Nicolae Buzbuchi

Proceedings Volume 7297, Advanced Topics in Optoelectronics, Microelectronics, and Nanotechnologies IV; 72972R (2009) https://doi.org/10.1117/12.823711
Event: Advanced Topics in Optoelectronics, Microelectronics, and Nanotechnologies IV, 2008, Constanta, Romania

Abstract

The new idea of liquid fuel (kerosene) aeroramp injector/plasma igniter was tested in cold flow using a supersonic wind tunnel at Mach 2.4. The liquid fuel (kerosene) injector is flush wall mounted and consists of a 2 hole aeroramp array of impinging jets that are oriented in a manner to improve mixing and atomization of the liquid jets. The two jets are angled downstream at 40 degrees and have a toe-in angle of 60 degrees. The plasma torch used nitrogen and air as feedstocks and was placed downstream of the injector as an ignition aid. First, schlieren and shadowgraph photographs were taken of the injector flow to study the behavior of the jets, shape of the plume, and penetration of the liquid jet. The liquid fuel aeroramp was found to have better penetration than a single, round jet at 40 degrees. The Sauter mean droplet diameter distribution was measured downstream of the injector. The droplet diameter was found to vary from 21 to 37 microns and the atomization of the injector does not appear to improve beyond 90 effective jet diameters from the liquid fuel aeroramp.

Citation Download Citation

Liviu-Constantin Stan, Ioan Calimanescu, and Nicolae Buzbuchi "Measuring of a fuel injector in a supersonic air stream", Proc. SPIE 7297, Advanced Topics in Optoelectronics, Microelectronics, and Nanotechnologies IV, 72972R (7 January 2009); https://doi.org/10.1117/12.823711

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