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Turbos to Create A Jet

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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 ... – PowerPoint PPT presentation

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Title: Turbos to Create A Jet


1
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
2
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

3
Open Cycle Using Turbos
3
4
2
T
5 Jet
1
s
3
2
4
p
5 Jet
1
s
4
Necessity is the Mother of Invention !?!?!??!
5
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.

6
  • 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.

7
THE WORLDS FIRST INDUSTRIAL GAS TURBINE SET GT
NEUCHÂTEL
8
4 MW GT for Power Generation
9
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.

10
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.

11
Turbojets
  • As invented by Hans Von Ohain Frank Whittle.
  • Typical Turbojet
  • Schematics

12
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.

13
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)

14
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)

15
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)

16
  • 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)

17
  • Overall pressure ratio 15.51
  • Specific fuel consumption 1.195 (cruise), 1.39
    (SL) lb/(hlbf)
  • Thrust-to-weight ratio 5.4

18
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.

19
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)

20
  • 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

21
  • 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)

22
  • 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

23
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

24
Micro-turbojets for Weapons
25
Variation of Jet Technologies
26
Thermal Energy Distribution
27
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.

28
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).

29
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.

30
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

31
  • Nozzle Two Dimensional Vectoring
    Convergent/Divergent
  • Performance
  • Maximum Thrust gt35,000 lbf (156 kN) (with
    afterburner)
  • Thrust-to-weight ratio 91

32
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)

33
Intakes - Turbofan/Turbojet
Tomahawk/ALCM
Harpoon/SLAM
Williams F107
Teledyne J402
34
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
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