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JET ENGINE MECHANICAL ARRANGEMENT

JET ENGINE MECHANICAL ARRANGEMENT. More generally known as ‘ GAS TURBINE ’ Engine. THE WORKING PARTS OF A JET ENGINE. Rolls-Royce AVON – Canberra – 1950’s technology. Fuel, Oil, and Hydraulic Pumps, Electrical Generators, RPM Governor.

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JET ENGINE MECHANICAL ARRANGEMENT

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  1. JET ENGINE MECHANICAL ARRANGEMENT More generally known as ‘GAS TURBINE’ Engine THE WORKING PARTS OF A JET ENGINE

  2. Rolls-Royce AVON – Canberra – 1950’s technology

  3. Fuel, Oil, and Hydraulic Pumps, Electrical Generators, RPM Governor. Rolls-Royce AVON - (Graphic Representation) Compressor Handling Bleed Valve Front Engine Mount Rear Compressor Case Combustion Chambers (Cans) Intake Anti-Icing Tube Jet Pipe (Exhaust) Front Compressor Casing Accessory Gearbox Oil Tank Turbine Section Rear Engine Mount

  4. Turbo-jet = no Bypass Duct

  5. FRONT BULLET AND SUPPORT VANES SUPPORT BEARINGS REAR CONE AND SUPPORT VANES NOZZLE GUIDE VANES (NGV’S) STATOR VANES COMPRESSOR OUTER CASINGS COMBUSTION OUTER CASINGS COMBUSTION INNER CASING COMBUSTION FLAME TUBE Engine Casings – Static Assembly

  6. Compressor Blades Turbine Blades Shaft Assembly Rotating Assembly

  7. 2,500 Deg C Above ambient 450 Deg C 1,000 Deg C Ambient temp The shaded area is called the ‘GAS PATH’. These sections expand first Problem! Temperature changes cause the shaft and casings to expand and contract But by different amounts! This could put tremendous unwanted forces on the casings and shaft leading to failures (We’ll look at what happens to the air passing through the GAS PATH in Gas Turbine Operation.) Solution? Its all in the bearings!

  8. Front Bearing Chamber Centre Bearing Chamber Rear Bearing Chamber Roller Bearing Ball Bearing (Location Bearing) Roller Bearing Bearing Chambers

  9. Ball Bearings Provide Positive Axial Location Hot section Casing Shaft Front Bearing Chamber Centre Bearing Chamber Rear Bearing Chamber Casing Representation of jet engine bearing layout

  10. Casing Then, with ‘heat soak’ the shaft expands Casing Shaft and Casing have no differential movement at this point The casing expands first - pushing the rear outer bearing with it The same happens at the front with pressured air and heat sink from the combustor heating the hardware The engine is actually designed to dimensions based on normal operating temperatures Shaft

  11. JET ENGINE COMBUSTOR OPERATION WHERE THE POWER IS PRODUCED

  12. THE COMBUSTION PROCESS IN A PISTON ENGINE: - FUEL IS MIXED WITH AIR BEFORE ENTERING THE CYLINDERS THE FUEL/AIR MIXTURE IS THEN COMPRESSED THEN IT IS IGNITED BY A SPARK ONCE FOR TWO REVS OF THE ENGINE (IN THE 4 STROKE CYCLE) IN A JET ENGINE: - AIR IS COMPRESSED AND FORCED INTO THE COMBUSTOR FIRST THEN THE FUEL IS SPRAYED IN UNDER PRESSURE IT IS THEN IGNITED BY A SPARK (BUT ONLY ONCE FOR STARTING) COMBUSTION IS THEN CONTINUOUS WHILST THE ENGINE IS RUNNING THE SAME AS A PLUMBERS BLOW TORCH!

  13. We’re going to look in detail at what happens here But first we’ll look at the layout of the combustion system

  14. COMBUSTOR LAYOUT – (ALSO HISTORICAL DEVELOPMENT) ENGINE STRUCTURE AND SHAFTS EACH CAN HAS A FUEL SPRAY NOZZLE (FSN) OUTER CASING INNER CASING INDIVIDUAL COMBUSTORS – ‘CANS’ 1st JET ENGINES WHITTLE ETC FLAME CONTAINED WITHIN THIS TUBE ‘FLAME-TUBE’

  15. IGNITERS COMBUSTOR LAYOUT – (ALSO HISTORICAL DEVELOPMENT) CANS CONNECTED TOGETHER TO EQUALISE PRESSURES AND TO SPREAD THE FLAME ON START UP TYPICAL OF DART SERIES TURBO PROPS

  16. INDIVIDUAL CANS WITH INTER-CONNECTORS ANNULAR OUTER CASING IGNITERS COMBUSTOR LAYOUT ‘CAN-ANNULAR’ LAYOUT ALSO FORMS THE ENGINE STRUCTURE TYPICAL OF SPEY &TAY BYPASS ENGINES

  17. JET ENGINE COMBUSTER OPERATION

  18. ANNULAR OUTER CASING ANNULAR INNER CASING ANNULARLAYOUT COMBUSTOR LAYOUT GIVES EVEN TEMPERATURE FACE TO TURBINE BLADES THE LAYOUT OF CHOICE FOR MODERN BYPASS ENGINES ALLOWS MORE FSN’S TO BE FITTED

  19. JET ENGINE COMBUSTER OPERATION

  20. THE CROSS SECTION OF ALL THESE LAYOUTS IS VIRTUALLY IDENTICAL AND THEREFORE SO IS THE AIRFLOW!

  21. Outer Combustion Casing 82% Cooling Flow Inner Flame Tube 1st Stage NGV’s 18% Vortex Flow Recirculating Vortex Fuel Feed

  22. Any Questions?

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