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UID:0-346@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20181224T163000

DTEND;TZID=Asia/Jerusalem:20181224T173000

DTSTAMP:20230527T135026Z

URL:https://aerospace.technion.ac.il/events/study-of-a-ducted-rocket-with-
 a-hybrid-gas-generator/

SUMMARY:Study of a Ducted Rocket with a Hybrid Gas Generator
DESCRIPTION:Lecturer:Daniel Komornik\n Faculty:Department of Aerospace Engi
 neering\n Institute:Technion – Israel Institute of Technology\n Location
 :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra
 ct: \n Details: \n Air-breathing engines as ramjets\, scramjets\, turbojet
 s\, and turbofans have higher specific impulse and energetic performance a
 nd\, hence\, longer range for the same amount of fuel than rockets. Ramjet
 s operate at high Mach numbers\, typically within the rocket flight speed 
 range of Mach 2-5\, beyond the efficient operating flight speeds of turboj
 et engines. The ducted rocket (ram-rocket) is one of the types of ramjet e
 ngines\, which may be considered for different missiles (e.g.\, long range
  air to air missiles or supersonic cruise missiles). It consists of two co
 mbustion chambers: a gas generator chamber where fuel is burned with a sma
 ll amount of oxidizer (a fuel-rich propellant combination) to generate fue
 l-rich gases\; and a ram combustor where the gases generated in the first 
 chamber are introduced and burned further with ambient air coming through 
 inlets.\nThis study presents a ducted rocket (DR) using a hybrid gas gener
 ator. Such a novel arrangement may exhibit improved safety (due to the sep
 aration of fuel and oxidizer)\, availability\, better performance\, contro
 llability\, and a possible operation with a lower content of oxidizer in t
 he gas generator. The present study simulates flight at Mach 2.5 at an alt
 itude of 3 km. Over 150 successful static firing tests of a ducted rocket 
 with a hybrid gas generator have been performed. These tests took place in
  a connected pipe facility\, simulating multiple ramjet inlet and gas gene
 rator conditions. Characteristic velocity efficiency was between 0.8 and 1
 . Fuel regression rate at the gas generator is displayed. Based on the tes
 t performed\, it is demonstrated that thrust and fuel-to-air ratio can be 
 controlled via modulating the cold oxidizer flow rate over a broad range o
 f missions and flight conditions. This cold flow control is one of the maj
 or advantages of using a hybrid gas generator for a ducted rocket.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20181028T010000

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