13. It then speeds this air up and splits it into two parts. One part continues through the "core" or center of the engine, where it is acted upon by the other engine components.
14.
15. The compressor is made up of fans with many blades and attached to a shaft.
16. The compressor squeezes the air that enters it into progressively smaller areas, resulting in an increase in the air pressure. This results in an increase in the energy potential of the air.
17.
18. The fuel burns with the oxygen in the compressed air, producing hot expanding gases.
19. The inside of the combustor is often made of ceramic materials to provide a heat-resistant chamber.
20.
21. The turbines are linked by a shaft to turn the blades in the compressor and to spin the intake fan at the front.
22.
23. The nozzle is the exhaust duct of the engine. This is the engine part which actually produces the thrust for the plane.
24. The variable geometry causes these nozzles to be heavier than a fixed geometry nozzle
28. The core airflow needs to be large enough to give sufficient core power to drive the fan.
29. Efficiently done, the resulting turbofan would probably operate at a higher nozzle pressure ratio but with a lower exhaust temperature to retain net thrust.
30. Since the temperature rise across the whole engine (intake to nozzle) would be lower, the (dry power) fuel flow would also be reduced, resulting in a better specific fuel consumption (SFC)
31.
32. High-bypass turbofan engine was the General Electric TF39, designed in mid 1960s to power the Lockheed C-5 Galaxy military transport aircraft.
![<br />MAHARANA PRATAP UNIVERSITY OF AGRICULTURE AND TECHNOLOGY<br />UDAIPUR, (RAJ) INDIA<br />A<br />SEMINAR REPORT<br />ON<br />“TURBOFAN ENGINE”<br />SEMINAR GUDIED BY-PRESENTED BY-<br />Astt.Prof. B.L SALVIVARUN JAIN<br />Mechanical DepartmentBE Final Year<br />Mechanical Engineering<br /> CONTENTS<br />CHAPTER 1<br />,[object Object]](https://image.slidesharecdn.com/seminarreport-110218042643-phpapp02/85/seminar-report-1-320.jpg)
![historyCHAPTER-2 PARTS <br />2.1 Fan<br />2.2 compressor<br />2.3 combustor<br />2.4 turbine<br />2.5 nozzle<br />CHAPTER 3 PRINCIPLE AND WORKING<br />3.1 brayton cucle<br />3.2 proplusion<br />3.3 how does turbofan engine work<br />CHAPTER 4 TYPES OF TURBOFAN<br />4.1 low bypass turbofan<br />4.2 high bypass turbofan<br />4.3 Afterburning turbofan<br />CHAPTER 5 PERFORMANCE PARAMETER<br />5.1 mach number<br />5.2 thrust<br />5.3 thrust ratio<br />5.4 thrust specific fuel consumption<br />5.5 proplusion efficiency<br />Chapter 6 conclusion<br /> CHAPTER - 1 <br /> <br />1.1 INTRODUCTION <br />A “TURBOFAN ENGINE” is a type of aircraft engine consisting of a ducted fan which is powered by a gas turbine. Part of the airstream from the ducted fan passes through the gas turbine core, providing oxygen to burn fuel to create power. However, most of the air flow bypasses the engine core, and is accelerated by the fan blades in much the same manner as a propeller. The combination of thrust produced from the fan and the exhaust from the core is a more efficient process than other jet engine designs, resulting in a comparatively low specific fuel consumption.<br /> Turbofans have a net exhaust speed that is much lower than a turbojet. This makes them much more efficient at subsonic speeds than turbojets, and somewhat more efficient at supersonic speeds up to roughly Mach 1.6, but have also been found to be efficient when used<br />with continuous afterburner at Mach 3 and above.<br /> All of the jet engines used in currently manufactured commercial jet aircraft are turbofans. They are used commercially mainly because they are highly efficient and relatively quiet in operation. Turbofans are also used in many military jet aircraft. such as the F-15 Eagle and in unmanned aerial vehicles such as the RQ-4 Global Hawk.<br />1.2 HISTORY<br />,[object Object]](data:image/gif;base64,R0lGODlhAQABAIAAAAAAAP///yH5BAEAAAAALAAAAAABAAEAAAIBRAA7)