Propulsion 2 Notes by N.TAMILSELVAM, Assistant Professor, Department of Aeronautical Engineering, Adhiyamaan college of Engineering (Autonomous), Hosur,tamilnadu-635109.Full description
equipos de propulsion, helice, sentido de giro, timonDescripción completa
Descripción completa
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Descrição: propulsion
Propulsion 2 Notes by N.TAMILSELVAM, Assistant Professor, Department of Aeronautical Engineering, Adhiyamaan college of Engineering (Autonomous), Hosur,tamilnadu-635109.
Introductory Notes for Novice naval architectute students
www.klasifikasiindonesia.comFull description
propulsionFull description
REPORT
TECHNICAL VISIT TO KENYA AIRWAYS HANGER SECTION
th
26 November 2014
Denis Ngene Mbugua
Reg. no. 11!""#1$
%.ENG AERONA&TICAL
YEAR '( SEMESTER SEMESTER
Topic: Technical Technical visit to Kenya Ken ya airways hanger section
Objective: To understand propulsion system of an aircraft
Introduction: A propulsion propulsion system is a machine that is produces thrust to push an object forward. On airplanes, thrust is usually generated through some application of Newtons third law of action and reaction. The wor!ing fluid is accelerated by the engine and the reaction to this acceleration produces a force on the engine. The amount of thrust generated depends on the mass flow through the engine and the e"it velocity of the gas. #ifferent propulsion systems generate thrust at slightly different ways. These different engines that generate thrust are categori$ed under the power engines and the reaction engines. %eaction engines derive thrust by jet reaction e"ample are turbo jet, high&low by'pass &turbo fan engines. On the other end power engines provide mechanical output to drive another device that generates the propulsive force. ("amples are turbo prop, turbo shaft as used in the helicopter. The propulsion system of the aircraft must serve two purposes 1. The thrust from the propulsion system must balance the drag of the airplane when the airplane is cruising. 2. The thrust from the propulsion system must e"ceed the drag of the airplane for the airplane to accelerate.
)oeing *+*'-- aircraft was used for our case study.
7assenger 5apacity 03 4remier 5lass6 027 4(conomy 5lass6 +9+ 5at ;; 0-- #< And 0,2-- %=% ;a&imum range +,-3- nm
5alibration unit metric
;86 083+-- lb
O6 7+7+9 )
5argo 0999 cu ft
;a&. Taach -.*
I8' 5ategory 5AT ;; TO7' ?es @ 0minutes
;a&imum thrust 4engine6 2*,+-- lb ;in. runway length 8,--- ft
;a&imum fuel capacity 23,-2-
Boeing !"#$$ technical configurations
%ire category %ire e&tinguishing system installed in forward and aft lower lobe cargo compartments. 'ystem certified for 1() minutes fire suppression *+ef: $22,"$$$$!-" /T0 +034. 5onforms to %+ 2).#) 5lass 5 O6" operational empty weight: is the sum of manufacturers ma nufacturers empty weight, standard items and operator items TO7'' e"tended range twin operations. (TO/ certification allows twin'engine airliners to fly long distances, for being aircraft operating with twin engine is certified for 0- minutes, this means it is permitted to fly any route not more than 0- minutes single engine flying time to the nearest suitable airport I8'' instrument landing system is a ground based instrument approach system that provides precision lateral and vertical guidance to an aircraft approaching and landing on a runway. 5T 5T 2 I8' is more highly calibrated with respect to ground e1uipment, runway occupancy, clearance areas and aircrew training. These system can be carried o ut in +9+s as low as 02-- as used in Boeing !"#$$
)oeing *+*'-- have a non'circular air inta!e, the aircraft uses a turbofan engine giving a significant gain in fuel economy and reduction in noise by incorporating perforated composite wall material at the inta!e fan and a honey comb design at the propelling no$$le. inglets present present in the aircraft help in reducing reduc ing fuel burn by reducing vorte" drag in turn reducing engine wear and less noise on ta!eoff )oeing uses a high by pass turbo fan jet engine
