Numerical Investigation of Swirl Injector LOX/GH2 Ratio Influence Over Combustion Conditions Into a Liquid Rocket Engine

Swirl injectors are widely used in liquid rocket engines, gas turbine engines, diesel engines, industrial furnaces and so forth. Even though the design procedure of a swirl injector is more difficult than that of an impinging jet injector, swirl injectors have many advantages, such as atomization quality, wide operation range with stability and uniform mixing efficiency. The spraying mechanism of a swirl injector is such that a liquid sheet is injected with the tangential velocity due to tangential entries, so a liquid sheet is discharged with a specific spray angle which corresponds to the ratio of axial and tangential velocity and the air core is formed. The mixture ratio of Liquid O2 and Fuel (H2) for such types of injectors may be throttled from 2:1, which is the upper limit for functioning for current Liquid Rocket Engines (LRE) impinging jet axial injectors, up to 10:1. This paper intends to numerically investigate the impact of swirl injector LOX/GH2 ratio over combustion conditions into a LRE using state of the art numeric simulation technologies. The outcome of this work is to completely define the relation between LOX/GH2 ratio and the combustion conditions inside the rocket engine.

Language

  • English

Media Info

Subject/Index Terms

Filing Info

  • Accession Number: 01345060
  • Record Type: Publication
  • Files: TRIS
  • Created Date: Jul 5 2011 4:38PM