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Aviation History
1956
1956 - 1601.PDF
9 November 1956 759 27 Compressor disc driving-dogs 28 Eighth-stage air bleed holes to pressurize front-bearing oil seal 29 Blanking diaphragm plate 30 Compressor rotor disc 11 Rotating shrouds (stages 1-12) 12 Stator shroud rings (stages 1-7) 33 Curvic coupling ring 34 Triangulated 13th-stage rotor disc 35 Alternate coupling teeth omitted to allow passage of 13th-stage cooling air for turbine 36 Centre roller bearing 37 Centre-bearing-scroll oil seal 38 Spherical bearing 39 Thrust equalizer labyrinth seal and disc 40 Centre-bearing diaphragm 41 Turbine mainshaft 42 Rear-bearing-scroll oil seal 43 Rear roller bearing 44 Rear-bearing-scroll oil seal 45 Turbine labyrinth seal 44 Turbine diaphragm 47 Inner flame-tube seal ring 48 Turbine lock-nut 49 Taper pins mounting turbine discs to stub-shaft 50 Turbine blanking plug 51 Outer flame-tube seal ring 52 First-stage turbine nozzle blades 53 First-stage turbine rotor blades 54 Second-stage turbine nozzle blades 55 Second-stage turbine rotor blades So Torque-ring dogs 57 Centre-section conical extension 58 Heat shield 59 Inner flame-tube dilution ports 40 Outer flame-tube with corrugated film-cooling strip 61 Fuel distributors 42 Fuel feed pipes 13 Burner pipes 44 Primary air tube (5 Secondary air tube 44 Combustion chamber back-plate 67 Centre-section aerofoil strut 48 Oiffuser entry to combustion cham- ber 49 Compressor outlet straightener vanes 70 Stator case joint 71 Centre section 72 Stiffeners and diffuser attachment in aerofoil strut 73 Rear-bearing vent pipe 74 Rear-bearing scavenge pipe 75 De-king bleed 7* Teddington gate valve 77 Triple feed pipe 78 De-icing hot-air manifold 79 Hollow de-iced fixed inlet guide vanes 80 Manifold to transfer hot air for de- icing spider and bullet 81 Passage for hot air from (80) 82 De-icing air outlet from spider 83 De-icing air feed pipes for bullet 84 Metering orifice for bullet de-icing 85 Outlet holes for bullet de-icing air 84 Fuel pump 87 Cabin-heating air bleed with Ted- dington gate valve 88 Fuel-pump outlet pipe 89 Fuel pressure transmitter pipe 90 Distributor drain pipe 91 Graviner fire-extinguisher pipe 92 Flowmeter 93 Cooler outlet to P.I.V. fuel pipe 94 Centre and rear bearing vent con- nector 95 Centre and rear bearing vent pipe 94 Fuel-cooled oil cooler 97 Primer ring 98 Firewall seal (silicone-rubber seal -covered with asbestos cloth) 99 Firewall 100 Vapour outlet pipe from centre section 101 P4 pipe to fuel pump 102 Collector-box drain 103 Centre-section breather valve 104 Priming solenoid valve 105 Combustion chamber outer casing 104 Combustion chamber and exhaust- cone heat shield 107 Combustion chamber exhaust- cone and jet-pipe near cooling-air inlet 108 Exhaust cone outer skin 109 Insulating blanket 110 Exhaust-cone bullet 111 Exhaust-cone stay tubes 112 Exhaust-cone aerofoils 113 Heat shroud ring-joint to jet-pipe 114 Exhaust-cone rear flange incor- porating piston-ring seal 115 Conduit for leads to Graviner fire detectors 114 Distributor drain connection to exhaust cone 117 Lodge high-energy igniter 118 Engine-mounting trunnion 119 Oil-feed connections for centre and rear bearings 120 Air-fuel ratio control 121 Low-pressure fuel filter 122 Barometric flow control 123 Oil tank (stainless steel) 124 Inlet and outlet to fuel-cooled oil cooler 12$ Oil-tank vent connection to intake casing 124 Oil-pressure feed pump 127 Cross-shaft bevel box 128 Scavenge filter cap 129 Oil tank sump 130 Compressor outlet (P2) pressure tapping, for A/F.R.C. (120) 131 Steady trunnion 132 Oil drain pipe to (123) 133 Air-intake pressure tapping for flow control 134 Starter lead terminal 135 Pressure filter cap ANNULAR COMBUSTION CHAMBER TWO "STAGETURBINE 113 Armstrong Siddeley Sapphire ASSa.7 turbojet. Overall diameter, 37.4in; overall length including nose fairing and exhaust cone, 132in; dry weight (including anti-icing, turbo-starter, high- energy igniters and oil tank), 3,075 Ib; rated thrust, 11,000 Ib; specific fuel consumption, 0.89 at maximum sea-level thrust.
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