This document summarizes a student group project on ramjet engines presented to their professor. It includes the names of the group members and faculty guide. The document then outlines the topics to be covered, including the history, basic configuration, characteristics, operating features, uses, advantages, and disadvantages of ramjet engines. It discusses how ramjet engines work by compressing incoming air through shockwaves in the supersonic diffuser and converting the kinetic energy to potential energy. It also provides examples of ramjet engine applications in supersonic aircraft and missiles.

1. ACTIVE LEARNING PROCESS
TITLE: The Ramjet engine
 NAME OF FACULTY:
Proff. Nishant Rajput
 NAME OF THE STUDENTS
1. Akshit Sanghani
2. Chiragbha Zala
3. Rushit Vaishnav
4. Datt Patel
5. 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

4. 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.

9. 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

10. 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

11. 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

12. Temperature(T) Entropy(S) graph
T
S
(a)
(02)
(0a)
(b)
Pa
P02
(04)
(06)

13. 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.

15. There are two main uses of ramjet engine
1) In some Aircraft propultion system
2) In supersonic missiles propultion system

39. 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

40. 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

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