Patent Published


Deflagration To Detonation Supersonic Igniter

Patent No: 201941026005
Inventors:
Dr. Aldin Justin Sundararaj, Assistant Professor, Aerospace Engineering
Ms. Vinitha M Samuel PR16AE002, M.Tech batch 2016-18

In deflagration to detonation supersonic igniter the fuel and oxidizer is ignited with a conventional spark plug. The flame thus developed is made to travel through a Shchelkin spiral placed inside the tube. The spiral acted as a blockage and the subsonic flame gets converted to detonation wave. A introduction of secondary source of fuel in the detonating tube results in an effective enhancement of ignition in detonation engines. The supersonic igniter can be used to initiate supersonic /detonating wave in high enthalpy engines like Pulse Detonation Engines (PDE), Continuous Rotating Detonation Engines (CRDE).



Improved Blowing Suction System (IBSS) for enhanced aerodynamic performance in aircraft wing

Patent No: 202041046416 A
Inventors:
Dr. G. Jims John Wewssley, Assistant Professor, Aerospace Engineering
Mr. K. Balaji RPK17AE001, Ph.D scholar
In deflagration to detonation supersonic igniter the fuel and oxidizer is ignited with a conventional spark plug. The flame thus developed is made to travel through a Shchelkin spiral placed inside the tube. The spiral acted as a blockage and the subsonic flame gets converted to detonation wave. A introduction of secondary source of fuel in the detonating tube results in an effective enhancement of ignition in detonation engines. The supersonic igniter can be used to initiate supersonic /detonating wave in high enthalpy engines like Pulse Detonation Engines (PDE), Continuous Rotating Detonation Engines (CRDE).