MAE 5350: Gas Turbines

1
MAE 5350 Gas Turbines

• Lecture 1 Introduction and Overview
• Mechanical and Aerospace Engineering Department
• Florida Institute of Technology
• D. R. Kirk

2
LECTURE OUTLINE

• Introduction
• What is an air-breathing engine
• Key questions
• Propulsion Options
• Rocket Propulsion Overview and Basic Operation
• Air-Breathing Propulsion Overview and Basic
  Operation
• Momentum Exchange Physics
• Air-Breathing Engine Components
• Nomenclature
• Component Functionality
• Engine Types
• Turbojet ( afterburner), Turbofan, Turboprop,
  Ramjet, Scramjet
• Examples of Current Aircraft Engines
• Introduction to Propulsion Performance Parameters

3
ROCKET VS. AIR-BREATHING PROPULSION

• Take mass stored in a vehicle and throw it
  backwards
• ? Use reaction force to propel vehicle
• All fuel and oxidizer are carried onboard the
  vehicle

• Capture mass from environment and set that mass
  in motion backwards
• ? Use reaction force to propel vehicle
• Only fuel is carried onboard
• Oxidizer (air) is harvested continuously during
  flight

4
AIR-BREATHING PROPULSION

• Gas turbine engines power every modern aircraft
  and will for foreseeable future
• Gas turbines used for land-based power
  application, rocket engine turbo-pumps, marine
  applications, ground vehicles (tanks), etc.
• Many technical challenges to be addressed (Fuel
  Economy, Emissions, Noise)
• Fluid mechanics, thermodynamics, combustion,
  controls, materials, etc.
• One of most complicated, parts, extreme
  environment device on earth
• Enormous market vast research and development
• Development time of engine gt development time of
  aircraft (53)
• Market is so competitive that engines are sold
  for a loss

5
DESIGN DRIVER FUEL ECONOMY
American Airlines Stock Price Last 5 Years
American Airlines CEO explains AA
bankruptcy http//money.cnn.com/video/news/2011/1
1/29/n_amr_american_bankruptcy.cnnmoney/
6
FUEL CONSUMPTION TREND

• U.S. airlines, hammered by soaring oil prices,
  will spend 5 billion more on fuel this year or
  even a greater sum, draining already thin cash
  reserves
• Airlines are among the industries hardest hit by
  high oil prices, which have jumped 38 percent in
  just 12 months.
• Airline stocks fell at the open of trading as a
  spike in crude-oil futures weighed on the sector

JT8D
Fuel Burn
JT9D
PW4084
Future Turbofan
PW4052
NOTE No Numbers
1950
1960
1970
1980
1990
2000
2010
2020
Year
7
FUEL COST DRIVEN EXAMPLE

• With fuel now largest component of operating
  costs, air carriers are turning to fuel-saving
  measures that once seemed hardly worthwhile
• Upswept wingtips to increase range and improve
  aerodynamics
• Taxi to and from runway on one engine to save
  fuel
• Does it make sense to actually fly slower?
• Do you polish an airplane or paint it?
• Airlines have new program to wash their
  aircraft/engines
• Other cost saving measures
• 1st and 2nd bag check fee (and many others new
  fees)
• Remove all pillows from MD-80s

8
CHEMICAL EMISSIONS
9
GREENHOUSE GAS EMISSIONS
10
AIRCRAFT NOISE
11
AIRCRAFT AND ENGINE NOISE
12
COMMERCIAL ENGINES
707
757
727
767
737
777
747
787
13
TRENDS TO BIGGER ENGINES
1995 Boeing 777, FAA Certified
1958 Boeing 707, United States' first commercial
jet airliner
Similar to PWJT4A T17,000 lbf, a 1
PW4000-112 T100,000 lbf , a 6
14
VARIOUS NUMBER OF ENGINE CONFIGURATIONS
2 Engines
3 Engines
4 Engines
6 Engines
15
SR-71 J-58 TURBO RAMJET
16
DRONES IN THE NEWS
17
X-51
18
LAND-BASED POWER GENERATION
19
LARGEST GAS TURBINE ENGINE SGT5-8000H

• Power 340 MW
• Extrapolated mass flow based on SGT100-SGT1000
  series 900 kg/s
• Average of SGT100-SGT1000, Assume pc 15
• Assumed tc (isentropic, g1.35) 2
• Assume 24 burners (consistent with SGT5-series)
• Combustor total CFM 216,000
• CFM per burner 9,000
• Full-scale, single-burner testing can be
  accomplished
• Trends
• If combustor inlet temperature is lower, CFM is
  lower
• If combustor inlet pressure is higher, CFM is
  lower

http//www.powergeneration.siemens.com/en/products
/gasturbinesseries/largescale/sgt5_8000h/index.cfm
20
GE 9H HOW LARGE IS THE DEVICE?
21
FURTHER EXAMPLES
22
WHY AIR-BREATHING PROPULSION

• Propulsion Goal Create a Force to Propel a
  Vehicle (N.S.L)
• 2 Choices for Propulsion
• Take mass stored in a vehicle and throw it
  backwards ? Use reaction force to propel vehicle
• Rocket Propulsion (MAE 4262)
• All fuel and oxidizer are carried onboard vehicle
• Capture mass from environment and set that mass
  in motion backwards ? Use reaction force to
  propel vehicle
• Air-Breathing Propulsion (MAE 4261)
• Only fuel is carried onboard
• Oxidizer (air) is harvested continuously during
  flight
• Airplanes are very sensitive to environment in
  which they operate
• Rockets are highly insensitive to operational
  environment

23
HOW ALL ROCKET WORKS

• Rocket Propulsion Produces thrust by ejecting
  stored matter
• Propellants combined in combustion chamber where
  chemically react to form high TP gas
• Gases accelerated and ejected at high velocity
  through nozzle, imparting momentum to engine
• Thrust force is reaction experienced by structure
  due to ejection of high velocity matter
• Same phenomenon pushes garden hose backward as
  water flows from nozzle, gun recoil
• QUESTION
• Could a rocket engine exert thrust while
  discharging into a vacuum (with not atmosphere to
  push against)?

F
Chemical Energy
Thermal Energy
Kinetic Energy
24
HOW AN AIRCRAFT ENGINE WORKS
Chemical Energy
Thermal Energy
Kinetic Energy

• Flow through engine is conventionally called
  THRUST
• Composed of net change in momentum of inlet and
  exit air
• Fluid that passes around engine is conventionally
  called DRAG

25
SUMMARY ESTIMATES FOR THRUST
Rocket Air-Breathing Engine

• Points to remember
• Mass flow for rocket is propellant carried
  onboard (fuel oxidizer)
• Mass for air-breathing engine is fuel carried
  onboard and air harvested from environment as
  airplane flies
• Rockets usually require far higher thrust levels
  than airplanes
• Airplanes usually fly for far greater durations
  than rockets

26
ENGINE OVERALL LAYOUT
27
CROSS-SECTIONAL EXAMPLE GE 90-115B
Compressor
Nozzle
Fan
Turbine
Combustor
Inlet

• Why does this engine look the way that it does?
• How does this engine push an airplane forward,
  i.e. how does it generate thrust?
• What are major components and design parameters?
• How can we characterize performance and compare
  with other engines?

28
EXAMPLE OF MILITARY ENGINETURBOJET OR
LOW-BYPASS RATIO TURBOFAN
Extreme Temperature Environment
Compressor
Combustor
Turbine
Afterburner
29
MAJOR GAS TURBINE ENGINE COMPONENTS

• Inlet
• Continuously draw air into engine through inlet
• Slows, or diffuses, to compressor
• Compressor / Fan
• Compresses air
• Generally two, or three, compressors in series
• Raises stagnation temperature and pressure
  (enthalpy) of flow
• Work is done on the air
• Combustor
• Combustion or burning processes
• Adds fuel to compressed air and burns it
• Converts chemical to thermal energy
• Process takes place at relatively constant
  pressure

30
MAJOR GAS TURBINE ENGINE COMPONENTS

• Turbine
• Generally two or three turbines in series
• Turbine powers, or drives, the compressor
• Air is expanded through turbine (P T ?)
• Work is done by the air on the blades
• Use some of that work to drive compressor
• Next
• Expand in a nozzle
• Convert thermal to kinetic energy (turbojet)
• Burning may occur in duct downstream of turbine
  (afterburner)
• Expand through another turbine
• Use this extracted work to drive a fan (turbofan)
• Nozzle
• Flow is ejected back into the atmosphere, but
  with increased momentum
• Raises velocity of exiting mass flow

31
2. COMPRESSORS WHERE IN ENGINE? PW2000
Fan
Compressor
Purpose of fan is to increase efficiency of
turbojet engine Much of air bypasses core of
engine
32
TURBOFAN ENGINES
Engine Core
33
TURBOFAN ENGINES
Bypass Air
Core Air
Bypass Ratio, B, a Ratio of by pass air flow
rate to core flow rate Example Bypass ratio of
61 means that air volume flowing through fan and
bypassing core engine is six times air volume
flowing through core
34
TRENDS TO BIGGER ENGINES
1995 Boeing 777, FAA Certified
1958 Boeing 707, United States' first commercial
jet airliner
Similar to PWJT4A T17,000 lbf, a 1
PW4000-112 T100,000 lbf , a 6
35
HOW LARGE IS THE 777-300 ENGINE?
11 ft 7 in (3.53 m)
11 ft 3 in (3.43 m)
Engine is largest and most powerful turbofan
built (11 ft 3 in (3.43 m) in diameter) In this
case, 737 cabin is a mere 3 wider than 777
engine
36
2 SPOOL DEVICE PW2000
Low Pressure Compressor (wlow)
High Pressure Compressor (whigh)
37
3. COMBUSTOR (BURNERS) LOCATION
Commercial PW4000
Combustor
Military F119-100
Afterburner
38
4. TURBINES LOCATION
Low Pressure Compressor (wlow)
High Pressure Compressor (whigh)
High and Low Pressure Turbines
39
NOISE SUPPRESSION
40
5. NOZZLES PW119 (F22 ENGINE)
41
MILITARY ENGINES PW F119
42
AFTERBURNER TESTING
43
COMMERCIAL AND MILITARY ENGINES(APPROX. SAME
THRUST, APPROX. CORRECT RELATIVE SIZES)
GE CFM56 for Boeing 737 T30,000 lbf, a 5
PW 119 for F- 22, T35,000 lbf, a 0.3
44
THRUST VS. PROPULSIVE EFFICIENCY
Important for both fighter and commercial
aircraft T/W usually more important for military
aircraft (maneuverability) Large mass flow means
high W Fighter ? DV Extremely important for
commercial aircraft, much less so for
fighter Efficiency critical for commercial Low
DV, high mass flow
Conflict
45
ENGINE STATION NUMBERING CONVENTION
2.0-2.5 Fan
3 Combustor
0 Far Upstream 1 Inlet
4 Turbine
2.5 Compressor
5 Nozzle
One of most important parameters is TT4 Turbine
Inlet Temperature Performance of gas turbine
engine ? with increasing TT4 ?
46
MAE 4261 REPRESENTATION OF AN ENGINE
Freestream 0
1
2
5
3
4
47
TYPICAL PRESSURE DISTRIBUTION THROUGH ENGINE
48
BOEING 747-400 AT TOUCHDOWN
49
BOEING 747-400 AT ROLLOUT
Thrust Reverse on Landing
50
SIMPLE THRUST REVERSE MODEL HOMEWORK 2
51
TWO OTHER LAYOUTS
GTF Geared Turbofan http//www.flug-revue.rotor.c
om/FRHeft/FRHeft07/FRH0710/FR0710a.htm
UDF Unducted Fan Concept http//www.aerospaceweb.
org/question/propulsion/q0067.shtml
52
HIGH EFFICIENCY TURBINE ENGINE (HETE) FTT50FTA30
1 ft

• Ideal and non-ideal cycle analysis
• Combustor scaling with Da (tflow/tchem),
  catalyst, porous metal
• Detailed component design (variable stators,
  electric generator, spin test rig, altitude test
  rig)

53
MICRO TURBOMACHINERY
1 cm
54
EXAMPLES OF GAS TURBINE COMPONENTS
Example of Film-Cooled 1st Turbine Blade
Cooling Holes

• Why film cooling?
• Turbine inlet temperatures gt melting temperatures
  of turbine blade materials
• Air provides a thin, cool, insulating blanket
  along external surface of turbine blade

55
RAMJETS AND SCRAMJETS
56
SCRAMJET PROPULSION X-43 MACH 10!
57
X-43A DETAILS
58
NASA'S X-43A SCRAMJET BREAKS SPEED RECORD

• NASA's X-43A research vehicle screamed into the
  record books again Tuesday, demonstrating an
  air-breathing engine can fly at nearly 10 times
  the speed of sound. Preliminary data from the
  scramjet-powered research vehicle show its
  revolutionary engine worked successfully at
  nearly Mach 9.8, or 7,000 mph, as it flew at
  about 110,000 feet.
• NASA's X-43A scramjet program successfully
  smashed its own world speed record for aircraft
  by flying at nearly 10 times the speed of sound.
  The flight proves its radical, air-breathing
  engine can function at speeds of nearly 12,000
  kilometers per hour.
• Aviation history was made today as NASA
  successfully flew its experimental X-43A research
  vehicle, a forerunner of craft that could well
  offer alternate access to space in the future.

59
AIRCRAFT ENGINE BASICS

• All aircraft engines are HEAT ENGINES
• Utilize thermal energy derived from combustion of
  fossil fuels to produce mechanical energy in form
  of kinetic energy of an exhaust jet
• Momentum excess of exhaust jet over incoming
  airflow produces thrust
• Thrust Force Time Rate Change of Momentum
• In studying these devices we will employ two
  types of modeling
• Fluid Mechanic
• Relate changes in pressure, temperature and
  velocity of air to physical characteristics of
  engine
• Thermodynamic (Cycle Analysis)
• Thermal ? mechanical energy from thermal is
  studied using thermodynamics
• Study change in thermodynamic state of air as
  passed through engine
• Geometry of engine NOT important, but rather
  processes are important

60
THERMODYANMICS BRAYTON CYCLE MODEL
61
ENGINE SURGE EVENT
Surge Violent reverse flow situation Burning
combustion gases driven upstream through
compressor and out of engine Usually accompanied
by downstream fire Engine must maintain
structural integrity and be able to be shut down
62
ENGINE TESTING BIRD STRIKE
http//100.rolls-royce.com/facts/view.jsp?id215 h
ttp//www.aviationexplorer.com/a6_engine_ingestion
.htm
63
Supplemental SlidesAircraft Engine Manufacturers
64
AIRCRAFT ENGINE MANUFACTURERS

• 3 Major Aircraft Manufacturers in World Today
  (Commercial and Military)
• Pratt and Whitney (USA)
• General Electric (USA)
• Rolls Royce (GB)
• Applications for Gas Turbines
• Commercial and Military Aircraft Engines,
  Helicopters
• Chemical Rocket Engines
• Industrial (marine turbines, yachts, assault
  ships, etc.)
• Power Plants
• Interesting Note
• Companies sell product at a loss
• Profit is made many years later on refurbishment,
  spare parts, maintenance

65
COMMERCIAL AIRCRAFT ENGINES JT8D
Engine Models JT8D-7/7A JT8D-9/9A JT8D-15/15A JT8D
-17/17A JT8D-17R/17AR JT8D-217C JT8D-219 Airplanes
Powered Boeing 727 Boeing 737-100/-200 McDonnell
Douglas DC-9 Boeing MD-80
66
COMMERCIAL AIRCRAFT ENGINES JT8D

• PW introduced JT8D to commercial aviation in
  February 1964 (Boeing's 727-100)
• 8 models of JT8D standard engine family cover
  thrust range from 14,000 to 17,400 pounds and
  power 727, 737, and DC-9 aircraft
• More than 11,800 JT8D standard engines produced,
  over one-half billion hours of service operation.
  New Program emphasis is on compliance with noise
  regulations
• For -200 models, a new low-emissions combustion
  system, or E-Kit, has been FAR 25 certified.
  Reduces NOx by 25 percent, unburned hydrocarbons
  by 99 percent and smoke by 52 percent relative to
  current models
• The -200 is also the exclusive power for the
  Super 27 re-engining program, in which Pratt
  Whitney, in cooperation with Goodrich
  Aerostructures, is offering 727 operators a
  solution to achieve Stage 3/Chapter 3 compliance
  with improved performance. Involves replacing two
  outboard engines with new JT8D-217C/219 models
  and adding noise suppression equipment. The Super
  27 can increase range up to 1,200 nautical miles
  and permits carrying up to 30 more passengers or
  up to 10,000 pounds in additional cargo.
• Engine Characteristics
• Fan tip diameter 39.9 - 49.2 in
• Length, flange to flange 120.0 - 154.1 in
• Takeoff thrust 14,000 - 21,700 lb
• Bypass ratio 0.96 - 1.74
• Overall pressure ratio 15.4 - 21.0
• Fan pressure ratio 1.92 - 2.21

67
COMMERCIAL ENGINES PW 4000 SERIES
68
COMMERCIAL ENGINES PW 4000 SERIES

• PW 94 inch
• Engine Models
• PW4052
• PW4056
• PW4060
• PW4062
• PW4062A
• PW4152
• PW4156A
• PW4156
• PW4158
• PW4460
• PW4462
• Airplanes Powered
• Boeing 747-400
• Boeing 767-200/-300
• Boeing MD-11
• Airbus A300-600
• Airbus A310-300

• PW 100 inch
• Engine Models
• PW4164
• PW4168
• PW4168A
• Airplanes Powered
• Airbus A330-300
• Airbus A330-200

• PW 112 inch
• Engine Models
• PW4074
• PW4077
• PW4077D
• PW4084
• PW4084D
• PW4090
• PW4098
• Airplanes Powered
• Boeing 777-200/-300

69
PW 4000 SERIES 94 INCH FAN

• Pratt Whitney's PW4000 94-inch fan model is the
  first in a family of high-thrust aircraft engines
• Certified thrust ranging from 52,000 to 62,000
  pounds, it powers the Airbus A310-300 and
  A300-600 aircraft and Boeing 747-400, 767-200/300
  and MD-11 aircraft. For twin-engine aircraft, the
  PW4000 is approved for 180-minute ETOPS
  (Extended-range Twin-engine Operations).
• Entered service in 1987. Advanced, service-proven
  technologies, such as single-crystal superalloy
  materials and its Full-Authority Digital
  Electronic Control (FADEC) for superior fuel
  economy and reliability. The engine's
  attractiveness is further enhanced by excellent
  performance retention, long on-wing times and low
  maintenance costs.
• Meets all current and anticipated emissions and
  noise regulations with margin. For a further
  reduction in emissions, especially NOx, TALON
  (Technology for Advanced Low NOx) combustor
  technology is now available as an option. Derived
  from the 112-inch fan model, TALON has segmented,
  replaceable liner panels for maintainability and
  air blast fuel nozzles for excellent fuel
  atomization and mixing
• Engine Characteristics
• Fan tip diameter 94 in
• Length, flange to flange 132.7 in
• Takeoff thrust 52,000 - 62,000 lb
• Flat rated temperature 86 or 92 F
• Bypass ratio 4.8 to 5.1
• Overall pressure ratio 27.5 to 32.3
• Fan pressure ratio 1.65 - 1.80

70
PW 4000 SERIES 100 INCH FAN

• PW4000 100-inch fan engine is first derivative
  model in PW4000 family. Developed specifically
  for Airbus Industrie's A330 twinjet, certified
  from 64,500 to 68,600 pounds of thrust.
• PW4168 features the industry's lightest weight
  and most advanced nacelle. Incorporates a number
  of service-proven technologies in materials,
  aerodynamics and controls to enhance performance,
  reliability and durability. The engine was the
  first in aviation history to qualify for ETOPS
  (Extended-range Twin-engine Operations) prior to
  entering service. It is now approved for
  180-minute ETOPS. Meets all present and
  anticipated noise and exhaust emissions
  regulations.
• PW4000 100-inch engines have accumulated more
  than three million hours of revenue service and
  are the leading engine on the A330
• Engine Characteristics
• Fan tip diameter 100 in
• Length, flange to flange 163.1 in
• Takeoff thrust 64,500 - 68,600 lb
• Bypass ratio 5.1
• Overall pressure ratio 32.0
• Fan pressure ratio 1.75

71
PW 4000 SERIES 112 INCH FAN

• PW4000 112-inch fan engine is second derivative
  model in PW4000 engine family. The PW4084,
  certified at 86,760 pounds thrust, was the launch
  engine for Boeing's 777 super twinjet. It entered
  service in June 1995 with United Airlines,
  already qualified for 180-minute ETOPS
  (Extended-range Twin-engine Operations). First
  engine to operate with approval for 207-minute
  ETOPS. The PW4090, certified at 91,790 pounds of
  thrust, entered service on the Boeing 777-200ER
  airplane in March 1997. The most recent model,
  the PW4098, was certified in July 1998. The
  PW4098, at 99,040 pounds of thrust, is available
  for 777-200ER and 777-300 models.
• For transportability, the engine can be shipped
  in a 747F as a complete engine. Also, the fan
  case is easily separated from the engine's core
  for split shipment without disturbing the bearing
  compartments.
• Engine Characteristics
• Fan tip diameter 112 in
• Length, flange to flange 191.7 in
• Takeoff thrust 74,000 - 98,000 lb
• Bypass ratio 5.8 to 6.4
• Overall pressure ratio 34.2 - 42.8
• Fan pressure ratio 1.70 - 1.80

72
GE 90 FAMILY MOST POWERFUL ENGINES IN WORLD

• GE Aircraft Engines was specified by Boeing to
  develop a 115,000 pound-thrust GE90 derivative
  engine for all longer-range 777-200LR and -300ER
  derivatives.
• Derivative engine represents the successful
  culmination of GE's strategy in the early 1990s
  to build a new centerline engine for the Boeing
  777 family. Since its initial testing, the
  GE90-115B has set numerous aviation records
  including reaching a sustained record 122,965
  lbs. of thrust during initial ground testing at
  GE's outdoor test facility

73
PW / G.E. GP7000 FAMILY
74
WORLDS LARGEST PASSENGER AIRLINER A380-800
A380-800 Wing span 79.8m (261ft 10in), length 73m
(239ft 6in). Height 24,1 m (79ft 1in)
75
PW / G.E. GP7000 DETAILS AND SPECIFICATIONS

• Joint effort between Pratt Whitney and General
  Electric
• GP7000 is derived from some of the most
  successful widebody engine programs in aviation
  history (GE90 and PW4000 families)
• Industry leading ETOPS reliability from service
  entry
• Over 250 million hours of performance
• Built on GE90 core and PW4000 low spool, but with
  many new technologies
• Best of GE Aircraft Engines and Pratt Whitney
  technologies
• Two-spool simplicity for reliability and
  maintainability
• Best payload capability, performance and
  performance retention.
• Quietest and lowest emissions in its class.
• Engine Characteristics
• Fan tip diameter 116 in
• Length, flange to flange 187 in
• Takeoff thrust 70,000 lb
• Flat rated temperature 86 F
• Bypass ratio 8.7

76
FUEL CONSUMPTION TREND

• U.S. airlines, hammered by soaring oil prices,
  will spend 5 billion more on fuel this year or
  even a greater sum, draining already thin cash
  reserves
• Airlines are among the industries hardest hit by
  high oil prices, which have jumped 38 percent in
  just 12 months.
• Airline stocks fell at the open of trading
  Tuesday as a spike in crude-oil futures weighed
  on the sector

JT8D
Fuel Burn
JT9D
PW4084
Future Turbofan
PW4052
NOTE No Numbers
1950
1960
1970
1980
1990
2000
2010
2020
Year
77
MILITARY ENGINES PW F100
78
PW F100 DETAILS AND SPECIFICATIONS

• Powers all current F-15 figher aircraft and F-16
  fighter aircraft in 21 countries. More than 6,900
  engines produced and over 16 million flight
  hours.
• F100-PW-229 is the most mature Increased
  Performance Engine (IPE) available and is the
  engine of choice for air forces worldwide. It is
  the only IPE engine operationally matured in both
  the F-15E and F-16 Block 52 aircraft. Using
  technology developed from the F119 and F135
  engine programs for the F/A-22 Raptor and F-35
  Joint Strike Fighter, the current production
  PW-229 incorporates modern turbine materials,
  cooling management techniques, compressor
  aerodynamics and electronic controls.
• In addition to offering the most technologically
  advanced IPE available, Pratt Whitney offers a
  comprehensive range of maintenance management
  programs and engine overhaul services to meet all
  customer requirements. These programs provide
  customers with low-cost maintenance solutions and
  superb operational readiness.
• Engine Characteristics
• Thrust 23,770 - 29,160 lb
• Weight 3,740 lb
• Length 191 in
• Inlet Diameter 34.8 in
• Maximum Diameter 46.5 in
• Bypass Ratio 0.36
• Overall Pressure Ratio 32 to 1

79
MILITARY ENGINES PW F119
80
PW F119 DETAILS AND SPECIFICATIONS

• PW F119 turbofan engine. In the 35,000 pound
  thrust class, engine is a dual spool,
  counter-rotating turbofan that enables aircraft
  operation at supersonic speeds for extended
  periods.
• F119 is equipped with a number of advanced
  technologies. Three-stage fan has shroudless
  titanium fan blades and is powered by a
  single-stage low-pressure turbine. The engine's
  core has an aerodynamically efficient six-stage
  compressor driven by a single-stage high-pressure
  turbine featuring the next generation of
  single-crystal superalloy blades with improved
  cooling management. Robust, but compact,
  high-pressure compressor features integrally
  bladed rotor disks for improved durability and
  three-dimensionally designed airfoils.
• Convergent/divergent nozzle vectors thrust 20
  degrees either up or down. Nozzle position
  management is automatically controlled by the
  full-authority digital electronic control
  (FADEC), which controls hundreds of other engine
  and aircraft operating parameters.
• F/A-22 full operational capability is expected in
  2005.
• Engine Characteristics
• Type Twin-Spool, Augmented Turbofan
• Thrust 35,000 Pound Thrust Class
• Engine control Full-Authority Digital Electronic
  Control
• Compression system Twin Spool/Counter
  Rotating/Axial Flow/Low Aspect Ratio
• Combustor Annular
• Turbine Axial Flow/Counter-Rotating
• Nozzle Two Dimensional Vectoring
  Convergent/Divergent

81
JSF ENGINE CONCEPTS VSTOL
82
A GOOD PLACE FOR MARKET NEWS

• Singapore Airlines places US7.35 bln Boeing
  order
• August 25, 2004 041357 (ET)
• SINGAPORE, Aug 25 (Reuters) - Singapore Airlines
  Ltd. ((SIAL.SI)), the world's second-largest
  airline by market value, said on Wednesday it had
  ordered 31 Boeing Co (BA,Trade) long-range
  777-300ERs worth about US7.35 billion in a fleet
  renewal programme.
• The aircraft will be powered by engines from
  General Electric Co (GE,Trade), Asia's most
  profitable airline said.
• The national carrier had asked airframe
  manufacturers Boeing Co (BA,Trade) and Airbus SAS
  ((EAD.DE))((EAD.PA)) to bid for new plane orders
  it may place later this year.
• Boeing, the No. 2 maker of jetliners, is in a
  dogfight for market share with No. 1 Airbus.
• The planes will cover the medium-haul and
  regional needs of the 57 percent government-owned
  airline over the coming years.

83
ONLINE REFERENCES

• http//www.aircraftenginedesign.com/enginepics.htm
  l
• http//www.pratt-whitney.com/
• http//www.geae.com/
• http//www.geae.com/education/engines101/
• http//www.ueet.nasa.gov/StudentSite/engines.html
• http//www.aeromuseum.org/Education/Lessons/HowPla
  neFly/HowPlaneFly.html
• http//www.nasm.si.edu/exhibitions/gal109/NEWHTF/H
  TF532.HTM
• http//www.aircav.com/histturb.html
• http//inventors.about.com/library/inventors/bljje
  tenginehistory.htm
• http//inventors.about.com/library/inventors/bleng
  inegasturbine.htm
• http//www.gas-turbines.com/primer/primer.htm

84
SIEMENS POWER GENERATION ORLANDO

• SGT-800 Industrial Gas Turbine 45MW
• The SGT-800 combines reliable, robust industrial
  design with the high efficiency and low emission
  levels of the latest turbine technology. It
  allows you to implement rapid, low-cost solutions
  for combined heat and power production. Moreover,
  it's environmentally sound, compact and easy to
  install.
• Designed for continuous, heavy-duty operation,
  the SGT-800 is the obvious choice where
  reliability, environmental concerns and low
  life-cycle costs are key factors. In combined
  cycle installations, this turbine affords very
  competitive life-cycle costs. It also offers high
  efficiency in simple cycle operation. And its
  powerful heat production capability in
  cogeneration installations makes it the ideal
  choice for the process industry.

• The SGT-300 Industrial Gas Turbine for Power
  Generation (ISO) 7.90MW(e)
• The SGT-300 is available with a Dry Low Emissions
  (DLE) combustion system, providing extremely low
  NOx levels with gas and liquid fuels and a full
  dual fuel capability. The SGT-300 design is
  uniquely simple, employing a single twin bearing
  rotor with heavy duty casings. This allows full
  site maintenance to be carried out.
• The generator set package is very compact,
  providing a small footprint and a high
  power-to-weight ratio. The single-shaft
  configuration provides excellent load acceptance
  and rejection characteristics, allowing robust
  and reliable operation in all applications.