Easa part 66 module 15 Gas Turbine Engine CH 16/25.
Introduction to Afterburning PDF.
PDF will be displayed in few seconds… (Please see below: paragraph Afterburning PDF ).
Afterburning may be a technique of augmenting the essential thrust of an engine to boost the craft take-off, climb and (for military aircraft) combat performance. The redoubled power may well be obtained by the employment of a bigger engine, however as this would increase the burden, cortical region and overall fuel consumption, afterburning provides the most effective technique of thrust augmentation for brief periods.
The Jet Engine by Rolls Royce
Chapter 1/25 : Basic mechanics (page 1 to 10)
Chapter 2/25 : Working cycle and airflow (page 11 to 18)
Chapter 3/25 : Compressors (page 19 to 34)
Chapter 4/25 : Combustion chambers (page 35 to 44)
Chapter 5/25 : Turbines (page 45 to 58)
Chapter 6/25: Exhaust system (page 59 to 64)
Chapter 7/25 : Accessory drives (page 65 to 73)
Chapter 8/25 : Basic mechanics (page 73 to 85)
Chapter 9/25 : Lubrication (page 85 to 94)
Chapter 10/25 : Internal air system (page 95 to 120)
Chapter 11/25 : Fuel system (page 121 to 132)
Chapter 12/25 : Starting and ignition (page 133 to 146)
Chapter 13/25 : Ice protection (page 147 to 152)
Chapter 14/25 : Fire protection (page 153 to 158)
Chapter 15/25 : Thrust reversal (page 159 to 168)
Chapter 16/25 : Afterburning (page 169 to 180)
Chapter 17/25 : Water injection (page 181 to 186)
Chapter 18/25 : Vertical/short take-off and landing (page 187 to 198)
Chapter 19/25 : Noise suppression (page 199 to 206)
Chapter 20 & 21 /25 : Thrust distribution & Performance (page 207 to 214)
Chapter 22/25 : Manufacture (page 215 to 228)
Chapter 23/25 : Power Plant Installation (page 229 to 242)
Chapter 24/25 : Maintenance (page 243 to 262)
Chapter 25/25 : Overhaul (page 251 to 264)
Download Full Document from Amazon Last edition (2015-07-20).
Afterburning ( Chapter 16/25) PDF.
Afterburning Protection rolls Royce the jet
Part 66 Mos
2. Afterburning consists of the introduction and burning of fuel between the engine rotary engine and therefore the jet pipe dynamical nozzle, utilizing the change state gas within the exhaust gas to support combustion (fig. 16-1).
The resultant increase within the temperature of the exhaust gas offers AN redoubled rate of the jet departure the dynamical nozzle and thus will increase the engine thrust.
3. because the temperature of the device flame is in way over one,700 deg. C., the burners are typically organized in order that the flame is targeted round the axis of the jet pipe. this permits a proportion of the rotary engine discharge gas to flow on the wall of the jet pipe and so maintain the wall temperature at a secure worth part 66 mos.
4. the world of the afterburning jet pipe is larger than a traditional jet pipe would be for the identical engine, to get a reduced rate gas stream. to produce for operation below all conditions, AN afterburning jet pipe is fitted with either a two-position or a variablearea dynamical nozzle (fig. 16-2). The nozzle is closed throughout non-afterburning operation, however once afterburning is chosen the gas part 66 mos temperature will increase and therefore the nozzle opens to administer AN exit space appropriate for the resultant increase within the volume of the gas stream. This prevents any increase in pressure occurring within the jet pipe which might have an effect on the functioning of the engine and permits afterburning to be used over a large vary of engine speeds. part 66 mos.
5. The thrust of AN afterburning engine, while not afterburning operating, is slightly but that of an identical engine not fitted with afterburning equipment; this is often thanks to the additional restrictions within the jet pipe. the general weight of the ability plant is additionally redoubled due to the heavier jet pipe and afterburning instrumentality.
Any questions or Comment, please submit it in Community forum
Module 15: Gas Turbine Engine
No topics were found here