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UID:0-324@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20190925T163000

DTEND;TZID=Asia/Jerusalem:20190925T173000

DTSTAMP:20230527T132254Z

URL:https://aerospace.technion.ac.il/events/internal-ballistics-of-boron-c
 ontaining-solid-fuel-ramjet/

SUMMARY:Internal Ballistics of Boron Containing Solid Fuel Ramjet
DESCRIPTION:Lecturer:\n Faculty:\n Institute:\n Location:\n Zoom: \n Abstra
 ct: \n Details: \n The Ramjet engine is a simple air-breathing device with
 out any moving parts such as compressors or turbines. The basic idea behin
 d ramjet propulsion is aerodynamic compression of air\, making it suitable
  for supersonic flight speed. At Mach numbers of 2-4\, the ramjet is highl
 y efficient and has superiority over other types of engines.\nThe solid fu
 el ramjet (SFRJ) is the simplest type of a ramjet engine and it is charact
 erized by increased energy density\, simplicity\, relatively low cost and 
 safety. The solid fuel combustor is made of a hollow cylinder of fuel\, wh
 ere air flows through its port and combustion takes place between the gasi
 fying fuel surface and the bulk airflow. A diffusive flame is established 
 within the boundary layer over the solid fuel surface.\nMetal additives to
  the commonly used hydrocarbon fuels can provide better energetic performa
 nce\, especially for volume-limited systems. Boron exhibits remarkable the
 oretical energetic performance (40% more than hydrocarbons) with the highe
 st energy density of all elements\, about three times of hydrocarbon fuels
 . In order to realize these advantages\, the boron particles must ignite a
 nd combust completely within a limited time residence. However\, this is d
 ifficult since boron particles are initially coated with an oxide layer\, 
 which inhibits combustion.\nThe present study focuses on modeling the comb
 ustion of the hydrocarbon solid fuel with boron particles.\nA 2-D axisymme
 tric model of a ramjet combustor\, at Mach 2.5 was solved numerically util
 izing the ANSYS FLUENT computational fluid dynamics (CFD) code. A series o
 f simulations were performed for various parameters such as flight altitud
 e\, fuel port diameter\, bypass ratio\, boron content and boron particle d
 iameter. The sensitivity of the SFRJ flowfield and the performance on the 
 various parameters was studied. The results show a strong dependence of th
 e engine performance on particle initial diameter and after-burner length.
CATEGORIES:Seminars

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DTSTART:20190329T030000

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