Note Turbine Engine Compatibility Mode PDF
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Malaysian Institute of Aviation Technology
2006
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Summary
This document is an introduction to turbine engines and jet propulsion, explaining the history of jet propulsion, from ancient times to modern advancements. It also covers different types of jet propulsion, including rockets and ramjets, and their various applications in aviation, power generation, and other sectors. The document is intended for training purposes at the Malaysian Institute of Aviation Technology.
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FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology INTRODUCTION Started during 2nd world war Offered many advantages over piston engine. – Higher speed of the aircraft – Incr...
FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology INTRODUCTION Started during 2nd world war Offered many advantages over piston engine. – Higher speed of the aircraft – Increase reliability and more efficient – less maintenance – Ease of operation at high altitude – Commercial – aircraft – power generation – shipping industries – modern vehicle Page No: 1 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 2 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 3 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 4 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology APPLYING NEWTON THIRD LAW FOR EVERY ACTION THERE ARE EQUAL AND OPPOSITE DIRECTION ACCELARATION IS THE ACTION AND FORWARD MOVEMENT IS THE REACTION EXAMPLE SQUID TAKES SEA WATER INTO THE BODY EXPELS IN FORM OF JET AND PROPEL TO MOVE FORWARD LIKE BALLON PROPEL FORWARD WHEN OPEN THE OPENING Page No: 5 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology SQUID RE A CT IO AC N TIO N Page No: 6 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TURBINE ENGINE HISTORY OF JET PROPULSION 250 B.C. A WRITER AND MATHEMATICIAN NAME HERO CREATE A TOY CALLED AEOLIPILE THAT USED THE REACTION PRICIPLE Page No: 7 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Dr. Sanford Moss research apply some of his concepts in the development of the turbo-supercharger Research by Frank Whittle has create the first successful turbojet engine His granted first patent for the jet engine in 1930 and 11 years later, engine completed its first fly in a Gloster model E28/29 aircraft produced 1000 pounds of thrust Page No: 8 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Revision Issue No : Original : 001 WHITTLE W1 Page No: 9 Subject Code: AFR 1021 Issue Date: 30 August 2006 GLOSTER E28/39 GLOSTER E28/39 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Hans Von Ohain, a German engineer, designed and built a jet engine that installed in Heinkel He-178 aircraft and make a successful flight on August 27,1939 produced 1100 pounds of thrust In 1941 the General Electric Company received a contract to research and develop a gas turbine engine The results the GE-1A engine, a centrifugal- compressor type engine that produced about 1650 pounds of thrust used to powered Bell XP-59 (flew 1942) not for the combat due to limited flight time of 30 minutes Page No: 12 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 HEINKEL HE-178 GLOSTER METEOR FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology JET PROPULSION TODAY TODAY COMMERCIAL A/C FLY 600 MPH CAN CARRY 400 PASSENGER OR MORE AND SEVERAL TONS OF CARGO COMMERCIAL AND MILITARY AVIATION ABILITY TO PRODUCE ENGINE TO PROPEL FASTER THAN THE SPEED OF SOUND SR-71 BLACKBIRD CAN FLY OF MACH FIVE CONCORDES CAN FLY 2.2 TIMES THE SPEED OF SOUND MILITARY AND COMMERCIAL USE JET PROPUISION TODAY Page No: 15 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TYPES OF JET PROPULSION ROCKET Nonairbreathing engine that carries its own fuel and oxygen for fuel to burn 2 types: 1. Solid-propellant rockets 2. Liquids-propellant rockets Page No: 16 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TYPES OF JET PROPULSION Solid-propellant rockets Use a solid fuel that is mixed with an oxidizer and former into a specific shape that promotes an optimum burning rate Used to propel some military weapon and provide additional thrust for takeoff of heavily loaded aircraft Liquids-propellant rockets Uses fuel and an oxidizing agent such as liquid oxygen The resulting high velocity gas jet behind the rocket provides enough thrust to propel an object Page No: 17 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 LIQUID-FUEL ROCKET LIQUID HYDROGEN AS THE FUEL AND LIQUID OXYGEN AS THE OXIDIZER, CARRIED IN TANKS ABOARD THE ROCKET. The space shuttle uses liquid-fuel rockets. FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology ROCKET SOLID PROPELLENT Page No: 20 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 21 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology ROCKET MISSILE SOLID PROPELLENT Page No: 22 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 RATO, or rocket assisted takeoff devices are small, solid propellant rocket motors that are attached to an airplane to provide additional thrust for high altitude or overweight takeoff conditions. FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TYPES OF JET PROPULSION RAMJET An athodyd, or aero-thermodynamic-duct Air-breathing engine with no moving part. To produce thrust, a ramjet must be moving forward at a high velocity since it has no rotating compressor to draw air into the engine Once air enters the engine, fuel is injected and ignited to provide the heat needed to accelerate the air and produces thrust Ramjet used in some military weapons delivery system where the vehicle is accelerated to a high initial velocity so the ramjet can take over for sustained flight Page No: 25 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology RAMJET Page No: 26 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 27 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 28 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology PULSEJET Similar to ramjet except the air intake duct is equipped with a series of shutter valves that are spring loaded to the open position Air drawn through the open valves enters a combustion chamber where its heated by a burning fuel When air is expand, shutter valves is force closed as air pressure increase and moves rearward to produce thrust More useful than ramjet because pulsejet produce thrust prior to being accelerated to a high forward speed Page No: 29 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology PULSEJET Page No: 30 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology IN THE PULSEJET ENGINE, AIR IS DRAWN INTO COMBUSTION CHAMBER AND MIXED WITH FUEL WHEN THE SHUTTER VALVES OPEN Page No: 31 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology AS THE FUEL BURNS, THE AIR PRESSURE WITHIN THE CHAMBER IS INCREASES AND FORCE THE SHUTTER VALVE TO CLOSE,THEN EXPANDING AIR WITHIN THE ENGINES ACCELERATES THROUGH THE EXHAUST TO PRODUCE THRUST Page No: 32 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology GAS TURBINE ENGINE Most practical form of jet engine in use today Became the standard on nearly all transport category, business and military aircraft Has 4 types: 1. Turbojet engine 2. Turboprop engine 3. Turbo shaft engine 4. Turbofan engine Page No: 33 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 34 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 35 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 36 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TYPE AND CONSTRUCTION Turbojet engine Basic principle of turbo jet is, air enter through inlet duct and go to compressor where it compressed and go to combustion section where fuel is added and ignited The heat was generated that make air is expand and continuous flow to rearward that hit the spin the turbine wheel and compressor because it was attach to same shaft EPR= engine pressure ratio EPR is a ratio of turbine discharge pressure to the engine inlet air pressure Page No: 37 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TURBOJET ENGINE Page No: 38 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology EPR gauge readings are an indication of the amount of thrust being produced for a given power lever setting EPR are used as verification of power settings for take off, climbs and cruise Page No: 39 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 40 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 41 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 42 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turboprop engine Is a gas turbine engine that delivers power to a propeller Similar design to turbojet engines except the power produced by a turboprop engine is delivered to a reduction gear system that spins a propeller Page No: 43 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Reduction gear is important because optimum propeller performance is achieved at much slower speeds than the engine’s operating rpm Used in business and commuter type aircraft Advantages: provide the best specific fuel consumption of any gas turbine engine and provides good performance characteristic at speeds between 300 and 400 miles per hour Page No: 44 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 TURBOPROPELLER ENGINE REDUCTION GEAR ASSEMBLY FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 50 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turboshaft engine A gas turbine engine that delivers power to a shaft that can drive something else Difference between turbojet and turboshaft engine is that turboshaft, most of the energy produced by the expanding gases is used to drive a turbine rather than a produce thrust Used in helicopter and widely used in auxiliary power units and in industrial applications to drive electrical generators and surface transportation systems Output is measured by shaft horsepower rather than thrust Page No: 51 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 Turboshaft engine FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TURBOSHAFT REVERSE FLOW Page No: 54 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turbofan engine Consists of a multi-bladed ducted propeller driven by a gas turbine engine Developed to provide a compromise between the best features of the turbojet and the turboprop Has 2 types: 1. Forward-fan engines Engines that have the fan mounted in front of the compressor 2. Aft-fan engines Engine that have the fan mounted to turbine section Page No: 55 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 56 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 AFT-FAN TURBOFAN ENGINE FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 59 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 60 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 61 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 62 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology With bypass engines, there are 3 terms must be familiar: Thrust ratio - Comparison of the thrust produced by the fan to the thrust produced by the engine core exhaust Bypass ratio - Ratio of incoming air that bypasses the fan to the amount of air that passes through the engine core - Divided into 3 classification i. Low bypass (1:1) ii. Medium (intermediate) bypass (2:1 or 3:1) iii. High bypass (4:1 or greater) - In a ducted fan engine, the bypass air is ducted along the entire length of the engine Fan pressure ratio Ratio of air pressure leaving the fan to the air pressure entering the fan Subject Code: AFR 1021 Revision : Original Page No: 63 Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology LOW BY-PASS ENGINE Page No: 64 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 HIGH-BYPASS TURBOFAN ENGINE WITH 80 PERCENT OF THRUST PROVIDED BY FAN AND ONLY 20 PERCENT BY THE CORE ENGINE FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology AIRFLOW MASS IN FAN SECTION IS THE SAME AS AIRFLOW MASS IN THE COMPRESSOR Page No: 66 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 67 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 68 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology BYPASS ENGINE Page No: 69 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology UNDUCTED FAN ENGINE New engines are designated ultra high bypass (UHB) propfan and unducted fan engine (UDF) Utilizes titanium, lightweight stainless steel and composites material Page No: 70 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology The use of composite blade reduces weight and allows safe operation at tips speeds higher than conventional blades Another design encases the propfan in a conventional cowl-type inlet which can achieve Mach 0.9 that known as ducted ultra high bypass engines Page No: 71 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 72 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 UNDUCTED FAN ENGINE FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology ENGINE COMPONENTS Air inlet Compressor section Combustion section Turbine section Exhaust section Accessory section Page No: 77 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 78 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology AIR INLET DUCTS Considered to be part of the airframe. Function:~ 1)-to recover as much of the total pressure of the free airstreams and deliver this pressure to the compressor. -known as ram recovery or pressure recovery. -inlets are shape to raise pressure Page No: 79 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology 2. to provide a uniform supply of air to the compressor. -Inlet duct must have little drag. -Inlet cover must be used to prevent damage/corrosion. Common location:~ -on the engine -in the wing -on the fuselage Page No: 80 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 WING-MOUNTED INLETS HAWKER SIDDELEY 801- NIMROD DE HAVILLAND COMET DH106 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 83 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 SINGLE-ENTRANCE FUSELAGE- MOUNTED INLET Canadair CL-13B Sabre FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Compressor section Component that forces air into the engine Compressor effectiveness is measure with compressor pressure ratio Support combustion Secondary function, supply bleed air For cooling purpose and etc Page No: 85 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Diffuser section Divergent shape Slow compressor discharge (V decrease) Increasing air pressure (P increase) As the air leave axial comp the velocity is 500 fps This air is to fast to support combustion the velocity is slow down at same time increase the pressure Page No: 86 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Combustion section Make from corrosion resistance steel 4 basic element; I. One or more combustion chamber II. A fuel injection system III. Ignition source IV. Fuel drainage system Primary air (25%-35%) Secondary air (65%-75%) Page No: 87 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turbine Section To extracted the energy after fuel and air is been burned To transforms a portion of kinetic energy witch it is the hot gases into mechanical energy to drive the compressor and accessories The turbine absorbs approximately 60% to 80% of total pressure energy from hot gasses Page No: 88 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology EXHAUST SECTION The design of a turbojet exhaust section exerts tremendous influence of the performance of an engine such as shape and size of the exhaust section. A typical exhaust section extends from the rear of the turbine section to the point where the exhaust gases leave the engine. It comprised of several components including the exhaust cone, exhaust duct and exhaust nozzle. Page No: 89 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology ACCESSORY SECTION ALSO KNOWN AS ACCESSORY DRIVE. THIS ACCESSORY DRIVE USE TO POWER BOTH ENGINE AND AIRCRAFT ACCESSORIES SUCH AS : a) ELECTRIC GENERATORS b) HYDRAULIC PUMPS c) FUEL PUMPS d) OIL PUMPS Page No: 90 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology THE OTHER FUNCTION OF ACCESSORIES DRIVE ARE a) ACTING AS AN OIL RESERVOIR b) HOUSING THE ACCESSORY DRIVEGEAR AND REDUCTION GEARS. Page No: 91 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology COLD AND HOT SECTION HOT SECTION - combustion, turbine and exhaust COLD SECTION - air inlet, compressor section Page No: 92 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 93 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology AIR INLET DUCTS Page No: 94 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Considered to be part of the airframe. Function:~ 1)-to recover as much of the total pressure of the free airstreams and deliver this pressure to the compressor. -known as ram recovery or pressure recovery. -inlets are shape to raise pressure Page No: 95 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology 2. to provide a uniform supply of air to the compressor. -Inlet duct must have little drag. -Inlet cover must be used to prevent damage/corrosion. Common location:~ -on the engine -in the wing -on the fuselage Page No: 96 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 97 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Engine Mounted Inlets -Air inlets duct located directly in front of the compressor and mounted to the engine. -mounting inlets with engine reduces air inlets length and to increase inlet efficiency. Page No: 98 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 99 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Wing Mounted Inlets some aircraft with engine mounted inside the wing feature air inlets ducts in the wing leading edge. -positioned near the wing root area. Page No: 100 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 101 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Fuselage Mounted Inlets some military aircraft use air inlet ducts mounted on the sides of the fuselage. -by mounting an intake on each side of aircraft, the duct length can be shortened without drag. -disadvantage:~ When flight maneuvers can cause imbalance in ram air pressure between two intakes. Page No: 102 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 103 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 104 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 105 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Subsonic Inlets Consists of fixed geometry duct whose diameter increase from front to back Divergent shape ~velocity DECREASE ~pressure increase Added pressure increase engine efficiency and produce most compression for best fuel economy. Page No: 106 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Supersonic Inlets Has inlet duct either fixed or variable geometry whose diameter decrease, then increase from front to back This convergent-divergent shape is used to slow incoming airflow to subsonic speed before reaches the compressor Supersonic inlets also employ a movable plug or throat that change duct geometry which for wide range of flight speed. Subject Code: AFR 1021 Revision : Original Page No: 107 Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 108 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 109 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Bell mouth inlet duct Have convergent profile to obtain very high aerodynamic efficiency when stationary or in slow flight Used for:~ -helicopters -slow moving a/c -engine run in ground test stands inlet short in length has rounded shoulders offering little resistance. Page No: 110 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 111 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turbofan Inlets Similar in design to a turbojet inlet except that the inlet discharge only a portion of its air into the engine The remainder of inlet air is bypasses the engine core to create thrust This helps cool the engine and reduce noise Page No: 112 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turbofan engine use:~ 1)short duct design :~allow a large percentage of fan air to bypass the engine core & produce thrust -used on the high bypass engine 2)Full fan duct :~reduce aerodynamic drag&noise emission -has converging discharge nozzle -not used on high bypass engine Page No: 113 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology SHORT DUCT DESIGN Page No: 114 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology FULL FAN DUCT DESIGN Page No: 115 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 116 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Airflow Principles Air flowing at subsonic speeds is incompressible Air flowing at supersonic is compressible Air flowing at supersonic reacts differently when force through convergent/divergent Page No: 117 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Example:~ >flows through convergent duct -density increase -velocity decrease -pressure increase >flows through divergent duct -density decrease -velocity increase -pressure decrease Page No: 118 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Inlet Design To slow inlet air,supersonic aircraft utilize convergent-divergent When supersonic air enters the convergent portion of duct,velocity decrease.At this point,air has slowed to the speed of sound and shock wave forms. As air passes through the shock wave,it enters the divergent portion of inlet where velocity continues to decrease & pressure increased. Page No: 119 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Once the air reaches the compressor,the velocity below sonic speed and its pressure has increased Supersonic aircraft utilizes variable geometric construction Several method are used to vary geometry or shape of inlet duct. 1)movable wedge: -is retracted during slow speed flight -as a/c accelerate to supersonic speed, the wedge extended into inlet airstreams to produce convergent- divergent shape Page No: 120 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology 2)dump valve & spill valve -during subsonic,dump valve is opened into the airstreams to allow more air into the diverging portion of the inlet -spill valve also open to help prevent turbulence -during supersonic,both dump and spill valve open to allow excess airflow to vent to atmosphere Page No: 121 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology 3)movable spike or plug -to alter the shape of the inlet as a/c speed changes -during transonic (mach.75 to 1.2)the movable spike is extended forward to produce normal shock wave/bow wave at the inlet. -as a/c speed, the spike is repositioned to shift the CD duct for optimum inlet shape. -normal shock wave will form at lip of the inlet. Page No: 122 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 123 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turboprop inlet Engine develop thrust with propeller Inlet smaller Used ducted spinner:~ -heavier -difficult to maintain -harder to deice Conical spinner:~ modified version of streamline spinner Page No: 124 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TURBOPROP INLET Page No: 125 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology DUCTED AND CONICAL SPINNER A. DUCTED SPINNER THE MOST EFFICIENT DESIGN FOR TURBO- PROP ENGINES B. ALTHOUGH LESS EFFICIENT, CONICAL SPINNER INLETS PRESENT FEWER DESIGN PROBLEMS THAN DUCTED SPINNERS Page No: 126 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 127 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turboprop filter/separator To prevent foreign object damage Use:~ 1)inlet screen 2)sand or ice separators -consist of air intake with at least 1 venturi and a series of sharp bends -venturi is use to accelerate flow of incoming air -debris has enough inertia that cannot flow the bends in intake. -one type is movable vane that is operated by operator through control handle in the cockpit. Page No: 128 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology INLET SCREEN Page No: 129 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 130 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Turboshaft filter/separator 1)Use particle separator on the engine inlet :~relies on venturi and sharp directional changes in airflow to filter sand and ice particles. 2)Swirl camber :~the swirling motion create centrifugal force to throw the dirt particles outside of the camber. -then the compressor bleed air will blown overboard through holes. Page No: 131 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 132 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology DEFLECTOR Is an area specifically designated for engine ground run Reduce hazard to personal, hangars, and others equipment Engine run in front of a blast shield or deflector Page No: 133 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology VORTEX DISSIPATER Some gas turbine have tendency to form vortex between the ground and inlet This vortex can become strong enough to lift water and debris as sand, small stones or small hardware into the engine Using high pressure bleed air to destroy vortex sometime called vortex destroyer or blow-away jet Located at lower part of engine cowl Page No: 134 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 135 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology AIR INLET ICING Ice formation on inlet guide vanes or inlet screens restricted the air flows Loss of thrust and raise in exhaust gas temperature Anti icing is use to melt the ice formation If ice once formed at the inlet can cause damage to the blade when the ice get into the engine Page No: 136 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Inlet Anti-Ice Systems Ducts high temperature bleed air from compressor to air inlet which to prevent ice formation. Bleed valve direct hot air to inlet duct leading edge, nose dome and inlet guide vanes. Disadvantage is engine power output decrease because bleed air is taken from turbine engine Indicated by slight rise in EGT and shift in both EPR & fuel flow To accommodate:~ electric anti-ice system Page No: 137 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Compressor section Page No: 138 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Compressor Section Introduction Type Advantages Disadvantages Compressor stall Combination compressor Page No: 139 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Compressor section Component that forces air into the engine Compressor effectiveness is measure with compressor pressure ratio Primary air to support combustion Secondary function, supply bleed air For cooling purpose Compressor must increase the intake pressure 20 to 30 time outlet pressure The air velocity of 400 to 500 ft per second Page No: 140 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Type of compressor section 2 type of compressor Centrifugal flow compressor Axial flow compressor Page No: 141 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology AXIAL FLOW COMPRESSOR Page No: 142 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology CENTRIFUGAL FLOW COMPRESSOR Page No: 143 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TYPE OF COMPRESSORS CENTRIFUGAL COMPRESSORS – ANOTHER NAME RADIAL OUTFLOW CENTRIFUGAL COMPRESSOR – USED IN SMALL ENGINE OR APU CONSIST OF 3 MAIN COMPONENTS I. IMPELER II. DIFFUSER III. MANIFOLD IMPELER - SINGLE STAGE - DOUBLE STAGE - DOUBLE SIDE ( DOUBLE ENTRY IMPELLER ) DIFFUSER - VELOCITY DECREASE - PRESSURE INCREASE MANIFOLD I. HAVE OUTLED DUCTS WITH TURNING VANES ( CASCADE VANES ) Page No: 144 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology IMPELLER OF CENTRIFUGAL-FLOW COMPRESSOR Page No: 145 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 146 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology DOUBLE STAGE IMPELLER Page No: 147 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 148 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 149 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 150 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 151 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology OPERATION THE IMPELLER TAKE THE AIR AND ACCELERATE IT OUT BY COMPRESSED THE AIR DUE TO CENTRIFUGAL FORCE THIS AIR IS THAN EXPELLED INTO THE DIFFUSER WHERE THE VELOCITY IS REDUCE AND PRESSURE INCREASE THE OUTLET DUCT / MANIFOLD CHANGE THE RADIAL DIRECTION OF AIR TO AXIAL DIRECTION TURNING VANE OR CASCADE VANES FITTED INSIDE THE OUTLED DUCT Page No: 152 TURN THE AIR FAR Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 153 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 154 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 155 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 156 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 157 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 158 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 T FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 159 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Advantages Simplicity easy to manufacture Low cost Low starting power requirement Operating efficiency over a wide range of rotational speed Compressor ratio of 15:1 Page No: 160 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Disadvantages Large frontal area Limits on the number of stages Page No: 161 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Axial flow compressor 2 main element I. Rotor (increase airflow/pressure) II. Angle and airfoil force air reward same as propeller I. Stator (decrease velocity/airspeed) II. It is to raise pressure rather than velocity decrease III. Single stages can produce pressure ratio 1.25:1 IV. Axial flow compressor maintain the velocity nearly constant while air pressure increase Page No: 162 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology AXIAL FLOW COMPRESSOR Page No: 163 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology ROTOR BLADE Page No: 164 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology STATOR VANE Page No: 165 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology In axial compressor, airflow velocity is maintain nearly constant while air pressure increases as the airflow through each stage Page No: 166 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 167 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 168 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Compressor rotor blades 10 – 18 compressor stages Airfoil cross section varying angle Made from stainless steel alloy fit loosely into the rotor disk to allows for easy assembly and vibration damping. Rotor blade roots designed (bulb, fir tree, dovetail) Page No: 169 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 170 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 171 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 172 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Compressor stator vanes Act as diffuser Decreasing its velocity and raising its pressure Prevent swirling and direct the flow of air coming off each stage to the next stage at appropriate angle Airfoil shape Made from steel or nickel, titanium Shrouded at tips, minimize vibrations tendencies Page No: 173 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology The first stage stator called inlet guide vanes The purpose to direct the air flow into the first stage at the best angle The last set vanes called outlet vane assembly To straighten air flow and eliminate any swirling motion or turbulence Page No: 174 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 175 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 176 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology ADVANTAGES OF AXIAL COMPRESSOR Ability to obtain higher compressor ratio by adding additional stage Small frontal area reduce aerodynamic drag Page No: 177 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology DISADVANTAGES OF THE AXIAL FLOW COMPRESSORS High weight and high starting power requirement Have low pressure rise per stage of 1.25:1 Expensive and difficult to manufacture Page No: 178 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology MULTIPLE-SPOOL COMPRESSOR Single-spool comp N1 Dual-spool or twin-spool comp-low pressure or N1 and high pressure or N2 Triple-spool comp- low pressure N1, intermediate N2 and high pressure N3 Page No: 179 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 180 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology SINGLE-SPOOL ENGINE SINGLE-SPOOL COMPRESSOR CONNECTED BY THE SAME SHAFT TO THE TURBINE SECTION Page No: 181 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 182 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology DUAL-SPOOL COMPRESSOR Page No: 183 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 184 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology TRIPLE-SPOOL COMPRESSORS Page No: 185 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology COMPRESSOR SECTION con’d COMPRESSOR STALL Described as imbalance between the two vector quantities, inlet velocity and compressor rotational speed. Occur when the compressor blade angle of attack exceeds the critical angle of attack or smooth airflow is interrupted and turbulence is created with pressure fluctuation. Compressor stall cause air flowing in the compressor to slow down and stagnate or sometimes reversing. Indication on the cockpit with fluctuation in RPM and high EGT Compression stall can be transient stall or hung stall Transient stall not harmful to the engine and often correct themselves. Page No: 186 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology COMPRESSOR SECTION con’d COMPRESSOR STALL con’d Hang stall can impair the engine performance cause loss of power and damage the engine. Reduce the angle of attack on the rotor blades using variable inlet guide vane and variable stator vane which direct the incoming air into the rotor blade at appropriate angle. Position of stator vane is controlled automatically by FCU by monitors compressor inlet temperature and engine speed. Another way by bleeding off some of the air pressure within the compressor through automatic air-bleed valve operate during low rpm and during engine star-up Compressors stall occur when engine inlet air becomes turbulent or disrupted Page No: 187 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology COMPRESSOR SECTION con’d FACTORS CAN CAUSE COMPRESSORS STALL 1. Fly in severe turbulent or perform abrupt flight maneuvers 2. Excessive fuel flow produced by the sudden acceleration accompanied by incompatible engine RPM and airflow. 3. Damage to compressor blade, stator vanes or turbine components Page No: 188 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Combination compressor Hybrid axial flow centrifugal flow compressor Used in small engine Eg; business jet and helicopter Page No: 189 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of Aviation Technology Page No: 190 Subject Code: AFR 1021 Revision : Original Issue Date: 30 August 2006 Issue No : 001 FOR TRAINING PURPOSE ONLY Malaysian Institute of
