EFFECT OF SWIRL INJECTOR ON HIGH SPEED FLOW USING SUPERSONIC COMBUSTOR

Authors

  • KARKUVEL RAJA A PG Scholar,Thermal engineering, R.V.S College of Engineering and Technology
  • VENKATESHWARAN V PG Scholar, Thermal Engineering, R.V.S College of Engineering and Technology
  • SATHISHKUMAR N Assistant professor, Department of Mechanical Engineering, R.V.S College of Engineering and Technology

Keywords:

Swirl injector, aft ramp angle, length to depth ratio

Abstract

Mixing characteristics of swirl coaxial jet injector are investigated experimentally with a model of air
injection in supersonic flow test facility with Mach number of 1.5. The injector, widely used in a highperformance combustor, the air is injected vertically for annular swirl flow. The swirl injector is placed at a
distance of 25mm from inlet of the combustor. The cavities are used to discover the mixing of the air and fuel.
Cavities having constant length to depth ratio of 5 with varying ramp angles of 15,20 and 30 degrees were used as
the aft wall of the cavity. Wall static pressure were made by using of pressure transducer with various pressures
4bar and 5 bar. It was compared with and without injection. The swirl generator develops a pressure drop across
the generator during the time of fuel is expelled in which pressure drops aids in enhancing the closure time of
the injector. The swirl generator minimizes the volume of fuel remaining in the injector.

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Published

2016-06-25

How to Cite

KARKUVEL RAJA A, VENKATESHWARAN V, & SATHISHKUMAR N. (2016). EFFECT OF SWIRL INJECTOR ON HIGH SPEED FLOW USING SUPERSONIC COMBUSTOR. International Journal of Advance Research in Engineering, Science & Technology, 3(6), 174–178. Retrieved from https://ijarest.org/index.php/ijarest/article/view/797

Issue

Vol. 3 No. 6 (2016): Volume: 03, Issue: 06 - June, 2016.

Section

Articles