Title: Turbos to Create A Jet
1Turbos 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
2The 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
3Open Cycle Using Turbos
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5 Jet
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5 Jet
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4Necessity is the Mother of Invention !?!?!??!
5Gas 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.
7THE WORLDS FIRST INDUSTRIAL GAS TURBINE SET GT
NEUCHÂTEL
84 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.
10A 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.
11Turbojets
- As invented by Hans Von Ohain Frank Whittle.
- Typical Turbojet
- Schematics
12Turbojets - 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.
13World'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)
14World'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)
15Present 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
18Turbojets 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.
19Harpoon 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
23Teledyne 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
24Micro-turbojets for Weapons
25Variation of Jet Technologies
26Thermal Energy Distribution
27Turbofans
- 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.
28Turbofans - 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.
30Specifications 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
32Turbofans 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)
33Intakes - Turbofan/Turbojet
Tomahawk/ALCM
Harpoon/SLAM
Williams F107
Teledyne J402
34Turboprops
- 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