Ramjet

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Ramjet

  1. 1. PRESENTED BY KVK
  2. 2. PRINCIPLE OF RAMJET ENGINE THE FUNCTION OF A SUPERSONIC AND SUBSONIC DIFFUSER IS TO CONVERT THE KINETIC ENERGY OF THE ENTERING AIR INTO A PRESSURE RISE CALLED RAM PRESSURE.
  3. 3. RAMJET BASIC OPERATION Ramjet has no moving parts Achieves compression of intake air by forward speed of vehicle Fuel injectors
  4. 4. RAMJET BASIC OPERATION Air entering the intake of a supersonic aircraft is slowed by aerodynamic diffusion created by the inlet and diffuser to low velocities. Expansion of hot gases after fuel injection and combustion accelerates exhaust air to a velocity higher than that at inlet and creates positive thrust
  5. 5. HyFly RAMJET CONCEPT Hypersonic Flight Demonstration Program Cruise Flight Mach Number ~ 6 Range 600 nm (1111 km)
  6. 6. HyFly RAMJET CONCEPT HyFly program was initiated in 2002 by DARPA (Defense Advanced Research Projects Agency) and U.S. Navy's ONR (Office of Naval Research)  to develop and test a demonstrator for a hypersonic Mach 6+ ramjet-powered cruise missile Prime contractor for HyFly missile is Boeing, Aero jet builds sustainer engine Air-launched from F-15E and accelerated to ramjet ignition speed by solid-propellant rocket booster
  7. 7. •Engine runs on conventional liquid hydrocarbon fuel (JP-10) •Much easier to handle than cryogenic fuels (LH2) used on other hypersonic scramjet vehicles • Sustainer engine of HyFly is a dual-combustion ramjet (DCR) (very complex) •Two different air inlet systems •Operate as a "conventional" ramjet with subsonic combustion •Operate at hypersonic speeds as a scramjet •First scramjet engine (hybrid or otherwise) to demonstrate operability with LH2 fuel
  8. 8. Hercules MK 70 rocket booster
  9. 9. SUMMARY  Ramjet develops no static thrust  Relies on ‘ram’ compression of air  Requires high speed flight  Performance depends on increase in stagnation temperature across burner (combustor)  Efficiencies (thermal, propulsive, and overall) increase with increasing flight Mach number  Next step: We desire an engine that develops static thrust  Put in a device to mechanically compress air (compressor)  Put in a device to power compressor (turbine)  Solution: Turbojet engine
  10. 10. ADVANTAGES LOW FRONTAL AREA. CO-EFFICIENT DRAG IS LOW. HIGH PRESSURE AND TEMPERATURE CAN BE EMPLOYED. LOAD CAPACITY IS VERY HIGH.
  11. 11. DISADVANTAGES THERE WE HAVING ALTITUDE LIMITATION. LOW THERMAL EFFICIENCY. HIGH TSFC. EROSION OCCURS AT THE NOZZLE DUE HIGH TEMPERATURE OF GAS COMING OUT FROM THE NOZZLE.

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