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- Title
NUMERICAL INVESTIGATION OF SWIRL INJECTOR LOX/GH<sub>2</sub> RATIO INFLUENCE OVER COMBUSTION CONDITIONS INTO A LIQUID ROCKET ENGINE.
- Authors
CALIMANESCU, IOAN; GRIGORESCU, LUCIAN
- Abstract
Swirl injectors are widely used in liquid rocket engines, gas turbine engines, diesel engines, industrial furnaces and so forth. Even though 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. Spraying mechanism of a swirl injector is that liquid sheet is injected with the tangential velocity due to tangential entries, so liquid sheet is discharged with 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 type 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 paperwork intend 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.
- Subjects
LIQUID propellant rocket engines; INJECTORS; INTERNAL combustion engines; GAS turbines; DIESEL motors
- Publication
Annals (Constanţa Maritime University), 2011, Vol 11, Issue 14, p67
- ISSN
2067-0427
- Publication type
Article