Turbos to Create A Jet

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Turbos to Create A Jet

• P M V Subbarao
• Professor
• Mechanical Engineering Department

A Techno-economically Feasible Creation of Strong
and Reliable Muscles for the Aircraft
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The Concept of Turbo Technology

• A control volume based engine to create Jet.
• Turbo-machinery execute -vdp work.
• Force or torque is generated with steady flow.
• Continuous transfer conversion of energy is
  possible at steady flow and steady state.
• Basic Architecture is

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Open Cycle Using Turbos
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5 Jet
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5 Jet
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Necessity is the Mother of Invention !?!?!??!
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Gas Turbine Technology

• 1791 A patent was given to John Barber, an
  Englishman, for the first true gas turbine.
• His invention had most of the elements present in
  the modern day gas turbines.
• The turbine was designed to power a horseless
  carriage.
• 1872 The first true gas turbine engine was
  designed by Dr Franz Stikze, but the engine never
  ran under its own power.
• 1903 A Norwegian, Ægidius Elling, was able to
  build the first gas turbine that was able to
  produce more power than needed to run its own
  components, which was considered an achievement
  in a time when knowledge about aerodynamics was
  limited.
• Using rotary compressors and turbines it produced
  11 hp (massive for those days).
• He further developed the concept, and by 1912 he
  had developed a gas turbine system with separate
  turbine unit and compressor in series, a
  combination that is now common.

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• 1914 Application for a gas turbine engine filed
  by Charles Curtis.
• 1918 One of the leading gas turbine
  manufacturers of today, General Electric, started
  their gas turbine division.
• 1920 The practical theory of gas flow through
  passages was developed into the more formal (and
  applicable to turbines) theory of gas flow past
  airfoils by Dr A. A. Griffith.

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THE WORLDS FIRST INDUSTRIAL GAS TURBINE SET GT
NEUCHÂTEL
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4 MW GT for Power Generation
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Gas Turbine Power Generation

• Experience gained from a large number of
  exhaust-gas turbines for diesel engines, a temp.
  of 538C was considered absolutely safe for
  uncooled heat resisting steel turbine blades.
• This would result in obtainable outputs of
  2000-8000 KW with compressor turbine efficiencies
  of 73-75, and an overall cycle efficiency of
  17-18.
• First Gas turbine electro locomotive 2500 HP
  ordered from BBC by Swiss Federal Railways.
• The advent of high pressure and temperature steam
  turbine with regenerative heating of the
  condensate and air pre-heating, resulted in
  coupling efficiencies of approx. 25.
• The gas turbine having been considered
  competitive with steam turbine plant of 18 which
  was considered not quite satisfactory.

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A Death Leading to New Life

• The Gas turbine was unable to compete with
  modern base load steam turbines of 25
  efficiency.
• There was a continuous development in steam power
  plant which led to increase of Power Generation
  Efficiencies of 35
• This hard reality required consideration of a
  different application for the gas turbine.
• 1930 Sir Frank Whittle patented the design for a
  gas turbine for jet propulsion.

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Turbojets

• As invented by Hans Von Ohain Frank Whittle.
• Typical Turbojet
• Schematics

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Turbojets - Basic Operating Features

• Five basic components
• intake captures air and efficiently delivers it
  to compressor.
• compressor increases air pressure and
  temperature.
• combustor adds kerosene to the air and burns the
  mixture to increase the temperature and energy
  levels further.
• turbine extracts energy from the gases to drive
  the compressor via a shaft.
• nozzle accelerates the gases further.
• High levels of engineering required for efficient
  operation, especially for compressor and turbine
  - therefore costly compared with rocket.

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World's first operational jet engine

• Dimensions 1.48 m long, 0.93 m diameter
• Weight 360 kg
• Thrust 450 kgf (4.4 kN) _at_ 13,000 rpm and 800
  km/h
• Compression ratio 2.81
• Specific fuel consumption 2.16 gal/(lbh) 18.0
  L/(kgh)

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World's first Aircraft He178

• General characteristics
• Crew One
• Length 7.48 m (24 ft 6 in)
• Wingspan 7.20 m (23 ft 3 in)
• Height 2.10 m (6 ft 10 in)
• Wing area 9.1 m² (98 ft²)
• Empty weight 1,620 kg (3,572 lb)
• Max takeoff weight 1,998 kg (4,405 lb)
• Powerplant 1 HeS 3 turbojet, 4.4 kN (992 lbf)
• Performance
• Maximum speed 698 km/h (380 mph)
• Range 200 km (125 mi)

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Present Turbojet Engines

• The Rolls-Royce/Snecma Olympus 593 was a reheated
  (afterburning) turbojet which powered the
  supersonic airliner Concorde.
• General characteristics
• Type Turbojet
• Length 4039 mm (159 in)
• Diameter 1212 mm (47.75 in)
• Dry weight 3175 kg (7,000 lb)

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• Components
• Compressor Axial flow, 7-stage low pressure,
  7-stage high pressure
• Combustors Nickel alloy construction annular
  chamber, 16 vapourising burners, each with twin
  outlets
• Turbine High pressure single stage, low pressure
  single stage
• Fuel type Jet A1
• Performance
• Maximum Thrust 169.2 kN (38,050 lbf)

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• Overall pressure ratio 15.51
• Specific fuel consumption 1.195 (cruise), 1.39
  (SL) lb/(hlbf)
• Thrust-to-weight ratio 5.4

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Turbojets for Guided Weapons
Harpoon
Teledyne J402-CA-400

• Jet velocity 350 - 1200 m/s.
• Better propulsive efficiency than rockets (lower
  than turbofans).
• Compact low weight.
• More complex, costly and unreliable than
  rockets.

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Harpoon General Characteristics

• Primary function Air-, surface-, or
  submarine-launched anti-surface (anti-ship)
  missile
• Contractor The McDonnell Douglas Astronautic
  Company - East
• Power plant Teledyne Teledyne J402 turbojet,
  660 lb (300 kg)-force (2.9 kN) thrust, and a
  solid-propellant booster for surface and
  submarine launches.
• Length
• Air launched 3.8 metres (12 ft) 7 in)
• Surface and submarine launched 4.6 metres
  (15 ft)

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• Weight
• Air launched 519 kilograms (1,140 lb)
• Submarine or ship launched from box or canister
  launcher 628 kilograms (1,380 lb)
• Diameter 340 millimetres (13 in)
• Wing span 914 millimetres (36.0 in)
• Maximum altitude 910 metres (3,000 ft) with
  booster fins and wings

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• Range Over-the-horizon (approx 50 nautical
  miles)
• AGM-84D 220 km (120 nmi)
• RGM/UGM-84D 140 km (75 nmi)
• AGM-84E 93 km (50 nmi)
• AGM-84F 315 km (170 nmi)
• AGM-84H/K 280 km (150 nmi)
• Speed High subsonic, around 850 km/h (460 knots,
  240 m/s, or 530 mph)

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• Guidance Sea-skimming cruise monitored by radar
  altimeter, active radar terminal homing
• Warhead 221 kilograms (490 lb), penetration
  high-explosive blast
• Unit cost US720,000

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Teledyne CAE J402-CA-400

• DimensionsLength 74.8 cm (29.44 in.), Width
  31.8 cm (12.52 in.
• Physical DescriptionType Turbojet
• Thrust/speed 2,937 N (660 lb) at 41,200 rpm
• Compressor 1-stage axial flow, 1-stage
  centrifugal flow
• Combustor annular
• Turbine 1-stage axial flow
• Manufacturer Teledyne CAE, Toledo

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Micro-turbojets for Weapons
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Variation of Jet Technologies
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Thermal Energy Distribution
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Turbofans

• Compromise between turbojet and turboprop with
  propeller now a fan enclosed within the engine.

• Two air streams passing through engine, one of
  which bypasses internal core.

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Turbofans - Basic Operating Features

• Similar to turbojet but turbine split into two
  with low pressure turbine used to drive separate
  fan ahead of compressor via twin-shaft
  arrangement.
• Bypass effect increases the available mass flow
  rate and thus reduces the jet velocity needed for
  a given amount of thrust (improves propulsive
  efficiency).

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Turbofan

• The Pratt Whitney F119 is an afterburning
  turbofan engine developed for the Lockheed Martin
  F-22 Raptor.
• The engine delivers thrust in the 35,000 lbf
  (160 kN) class, and is designed for supersonic
  flight without the use of afterburner.
• Delivering almost 22 more thrust with 40 fewer
  parts than conventional, fourth-generation
  military aircraft engine models, the F119 allows
  sustained supercruise speeds of up to Mach 1.72.

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Specifications F119

• General characteristics
• Type Twin-Spool, Augmented Turbofan
• Length 16 ft 11 in (5.16 m)
• Diameter
• Dry weight 3,900 lb
• Components
• Compressor Twin Spool/Counter Rotating/Axial
  Flow/Low Aspect Ratio
• Combustors Annular Combustor
• Turbine Axial Flow/Counter-Rotating

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• Nozzle Two Dimensional Vectoring
  Convergent/Divergent
• Performance
• Maximum Thrust gt35,000 lbf (156 kN) (with
  afterburner)
• Thrust-to-weight ratio 91

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Turbofans for GW
Tomahawk

• Very good propulsive efficiency and low specific
  fuel consumption
• Only very long range applications
• Large volume and difficult to design to small
  scales.

• Jet velocity 200 600 m/s
• Bypass ratio 0.51 (much higher in aircraft
  applications)

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Intakes - Turbofan/Turbojet
Tomahawk/ALCM
Harpoon/SLAM
Williams F107
Teledyne J402
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Turboprops

• Turbine extracts most of the jet thrust to run a
  propeller at the front, via a gear box.

• Limited GW applications (possibly future UAVs).
• Mainly low-speed aircraft applications (limited
  to about Mach 0.6).

Typical Turboprop Schematic