Ramjet engines

presiontation of ramjet engines for engineering study...

1. ACTIVE LEARNING PROCESS TITLE : The Ramjet engine NAME OF FACULTY: Proff . Nishant Rajput NAME OF THE STUDENTS Akshit Sanghani Chiragbha Zala Rushit Vaishnav Datt Patel Harsh Patel

2. Sardar Vallabhbhai Patel Institute Of Technology,Vasad Group Members: 1) Akshit Sanghani(16beaeg019) 2) Chiragbha Zala (16beaeg011) 3) Datt Patel(16beaeg010) 4) Rushit Vaishnav (16beaeg008) 5)Harsh Patel(16beaeg017) Branch - Aeronautical Batch - A Subject - Elements of mechanical engineering Topic - Ramjet engine Guided by - proff . Nishant Rajput

3. Ram jet engines

4. Objectives Introduction(what is Ram jet engine?) History of ramjet engine Basic configuration or design of ramjet engine Characteristics of Ramjet engine Basic operating features Use of ram jet engine Advantage of ramjet engine Disadvantage of ramjet engine

5. History of Ramjet engine In the Soviet Union, a theory of supersonic ramjet engines was presented in 1928 by Boris stechkin Yuri Pobedonostsev, chief of   GIRD 's 3rd Brigade, carried out a great deal of research in ramjet engines The first engine, the GIRD-04, was designed by I.A. To simulate supersonic flight, it was fed by air compressed to 20,000 kilopascals (200   atm), and was fueled with hydrogen. The GIRD-08 phosphorus-fueled ramjet was tested by firing it from an artillery cannon. These shells may have been the first jet-powered projectiles to break the speed of sound.

6. What is Ram jet engine?

7. C onfiguration s

8. Characteristics Ramjet engines can not produce static thrust 1) It is operated from A/c in flight. 2) Initial velocity is provided by launching rockets. Incapable of steady operation at M<1 Diffuser In the Ram jet engine there are two types of diffuser are use as per its application, 1)supersonic diffuser 2)subsonic diffuser

9. During the compression process in Ram jet engine ,kinetic energy of incoming atmospheric air is converted in to the potential energy by the diffuser. This energy transformation is occurred by Ram effect. High flight speeds render increase in pressure rise. Supersonic diffusion is caused through a system of shocks. Diffuser must be designed very efficiently. Supersonic diffuser at a given Mach number does not perform well at other Mach number, unless the geometry is variable

10. Beyond M = 6,the combustion is inefficient and incomplete because of very high temperature of entryair , and this gives improper expansion in the nozzle. M = 0.2 to 0.3 at combustor inlet. Flame holders(a shielding device to maintain the flame at high velocity streams)is necessary. Combustor temperature = 3000 K

11. Temperature(T) Entropy(S) graph T S (a) (02) (0a) (b) P a P 02 (04) (06)

12. Graph Analysis 1)Vertical line (a) to (02) represents compression process. 2)inclined line (02) to (04) represents combustion process. 3)and further continuous line (04) to (06) represents expansion process. 4) here compression and expansion processes are Reversible and adiabatic.

13. Uses of Ramjet engine There are two main uses of ramjet engine In some Aircraft propultion system In supersonic missiles propultion system

14. Aircrafts in which ramjet use 1)Hiller hornet helicopter

15. 2) Focke-wulf triebflugel

16. 3) Focke-wulf ta 283

17. 4) Leduce experimental aircraft

18. 5) Lokheed d-21

19. 6) Lokheed x-7

20. 7)Nord 1500 griffon

21. 8)Republic XF-103

22. 9)SR-71 blackbird

23. 10)Skoda- kauba SK p.14

24. 11) Focke -wulf super lorin

25. Missiles in which Ramjet use 1) Bomarc

26. 2) Brahmos

27. 3)MBDA meteor

28. 4)Bristol bloodhound

29. 5) Bendix RIM-8 T alos

30. 6)GQM-163 coyote

31. 7)North american SM-64 navaho

32. 8)P-270 Moskit

33. 9) Aakash missile

34. 10)Sea dart missile

35. 11)2k11 krug

36. 12)MBDA ASMP

37. Advantages No moving parts like compressors and turbines, so it reduces cost. Simple or easy design It can produce thrust 3 Mach to 9 Mach(so basically used in super sonic Cruz missiles and supersonic aircrafts

38. Disadvantages It need high initial velocity(typically M>2) before it can produce useful thrust It also required complicated super sonic intake to avoid shock losses

39. Reference and web resources Mattingly, j.d. ,(1996),Elements Of Gas Turbine Propulsion, McGraw Hill Oates,G.C.,(1988)Aerothermodynamics Of Gas Turbine and Rocket propulsion,AIAA,New York http://www.aero.hq.nasa.gov/edu/index.html http://www.ge.com/aircraftengines http://www.howthingswork.virginia.edu/

40. Thank you