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009576/01 PPT18/03/99
Technology overviewTechnology overview
end
009576/30 PPT18/03/99
Industrial RB211 DLE gas generatorIndustrial RB211 DLE gas generator
end
009576/02 PPT18/03/99
1 Combustion systems
2 Control systems
3 Aero / thermodynamics
4 Materials
5 Integration
1 Combustion systems
2 Control systems
3 Aero / thermodynamics
4 Materials
5 Integration
Key technologies for industrial enginesKey technologies for industrial engines
end
Combustion SystemsCombustion Systems
009576/03 PPT18/03/99
end
009576/04 PPT18/03/99
Rolls-Royce aeroderivative gas turbines Rolls-Royce aeroderivative gas turbines
DLE technology is incorporated across the product rangeDLE technology is incorporated across the product range
Allison 501 and 601Allison 501 and 601
TrentTrent
AvonAvon
RB211RB211
end1400 1500 1600 1700 1800 1900 20001400 1500 1600 1700 1800 1900 2000
NOx emissions
ppm
NOx emissions
ppmCO emissions
ppm
CO emissions
ppm
3030
2525
2020
1515
1010
55
00
120120
100100
4040
2020
00
8080
6060
Influence of temperature on CO and NOx emissionsInfluence of temperature on CO and NOx emissions
Combustion temperature KCombustion temperature K
009576/05 PPT18/03/99
COCONOxNOx
end
009576/06 PPT009576/06 PPT18/03/9918/03/99
Industrial RB211 DLE combustion systemIndustrial RB211 DLE combustion system
Objectives :-
25 vppm NOx and CO simultaneously
Flexible operation - compliance over a wide load and ambient temperature range
No effect on performance (power output, fuel consumption, maintainability or
availability)
Retrofit capability - changes restricted to high pressure 04 module
On going programme to further advance low emissions technology
Minimum changes to site configuration at retrofit
Objectives :-
25 vppm NOx and CO simultaneously
Flexible operation - compliance over a wide load and ambient temperature range
No effect on performance (power output, fuel consumption, maintainability or
availability)
Retrofit capability - changes restricted to high pressure 04 module
On going programme to further advance low emissions technology
Minimum changes to site configuration at retrofit
end
009576/07 PPT18/03/99
Industrial RB211 DLE combustion systemIndustrial RB211 DLE combustion system
Technology selected :-
Premix lean burn - Control combustion temperature
Fuel staging - Turndown over the load and
ambient temperature range
Series fuel staging - To provide flexible operation
with wide stability range
Technology selected :-
Premix lean burn - Control combustion temperature
Fuel staging - Turndown over the load and
ambient temperature range
Series fuel staging - To provide flexible operation
with wide stability range
end
009576/08 PPT18/03/99
Industrial RB211 DLE combustion systemIndustrial RB211 DLE combustion system
Benefits :-
Constant primary zone combustion temperature achieved by fuel scheduling only
- no airflow management
- no performance loss due to need for compressor bleed
- wide stability margin providing complete operational flexibility
Series fuel staging
- low CO over wide operating range due to substantial pre-heat
from upstream stage
Incorporates conventional diffusion flame
- proven starting reliability
- stable low power operation
Benefits :-
Constant primary zone combustion temperature achieved by fuel scheduling only
- no airflow management
- no performance loss due to need for compressor bleed
- wide stability margin providing complete operational flexibility
Series fuel staging
- low CO over wide operating range due to substantial pre-heat
from upstream stage
Incorporates conventional diffusion flame
- proven starting reliability
- stable low power operation
end
009576/09 PPT18/03/99
Industrial RB211 - Comparative diagrams of conventional and DLE combustor systemsIndustrial RB211 - Comparative diagrams of conventional and DLE combustor systems
Single annular combustor
18 off conventional fuel injectors
Single annular combustor
18 off conventional fuel injectors
Conventional
9 off pre mix
lean burn combustors
9 off pre mix
lean burn combustors
DLE
end
DLE fuel staging
Power
Primary zone premix
Secondary zonepremix
Conventionalcombustion
Fuel flow
Secondary Primary
Secondary mixing ductPrimary
mixing duct
Primaryfuel
Centraldiffusioninjector
Secondary fuel
Premix leanburn series staged combustor
009576/10 PPT18/03/99
Industrial RB211 DLE combustion systemIndustrial RB211 DLE combustion system
end
009576/11 PPT18/03/99
Industrial RB211 DLE combustion systemIndustrial RB211 DLE combustion system
Airflow
Pre-mix flow
Combustor
Cooling air
Airflow
Pre-mix flow
Combustor
Cooling air
DLE 04 moduleDLE 04 module
Torch igniter
Injector
Combustor
Air transfer casing
HP turbine
Discharge nozzleDiffuser
end
009576/12 PPT18/03/99
Industrial Avon - Comparative diagrams of conventional and DLE combustor systemsIndustrial Avon - Comparative diagrams of conventional and DLE combustor systems
Conventional
8 off combustors
Conventional
8 off combustors
DLE
Existing cannular arrangement retained
but with pre mix lean burn combustors
DLE
Existing cannular arrangement retained
but with pre mix lean burn combustors
end
009576/13 PPT18/03/99
Industrial Avon DLE combustion systemIndustrial Avon DLE combustion system
Power
Fu
el f
low
Dilution zonePrimary
fuel
Combustor casing
Secondary zoneSecondary zone
fuel inlet
Primary
fuel inlet
Primary zoneSecondary zone
fuel feed
Pre-mix duct
Secondary
fuel
end
009576/14 PPT18/03/99
Industrial Avon DLEIndustrial Avon DLE
Low risk programme
Changes confined to combustion system only
Low risk programme
Changes confined to combustion system only
DLE design changescontained within this area
DLE design changescontained within this area
Existing enginesupport system retained
Existing enginesupport system retained
end
Allison 601 Programme reviewAllison 601 Programme review
Dry Low Emissions systemDry Low Emissions system
009576/15 PPT18/03/99
DLE Features
RB211 DLE combustor applied to the 601-K
Three combustion liners adapted to the 601-K outer case
601-KB11 airflow is 1/3 of RB211
Pressure ratio and firing temperature virtually identical
DLE Features
RB211 DLE combustor applied to the 601-K
Three combustion liners adapted to the 601-K outer case
601-KB11 airflow is 1/3 of RB211
Pressure ratio and firing temperature virtually identical
end
Control SystemsControl Systems
009576/16 PPT18/03/99
end
Industrial RB211 DLE control systemIndustrial RB211 DLE control system
Entered service 1994
Joint Rolls-Royce EnTronic Controls Development Team
Same equipment standard installed at all Rolls-Royce test sites
Can be used for operation of conventional RB211 gas generator
Single bay Engine Electronic Control System
Electric fuel metering and distribution system
18 channel ignition system
Entered service 1994
Joint Rolls-Royce EnTronic Controls Development Team
Same equipment standard installed at all Rolls-Royce test sites
Can be used for operation of conventional RB211 gas generator
Single bay Engine Electronic Control System
Electric fuel metering and distribution system
18 channel ignition system
009576/17 PPT009576/17 PPT18/03/9918/03/99
end
009576/18 PPT18/03/99
Engine control systemEngine control system
System integration requires minimal changes to existing UPCSystem integration requires minimal changes to existing UPC
Existing unit control panelExisting unit control panel
DLE engine control systemDLE engine control system
Engine
sensors
Compressor control
Yard valves
Unit sequencing
Power turbine lube oil
Compressor control
Yard valves
Unit sequencing
Power turbine lube oil
18 channel
ignition
system
Fuel metering
units
Engine control unitIn
terf
ace
end
Aero / ThermodynamicsAero / Thermodynamics
009576/19 PPT18/03/99
end
Evolution of the RB211 and Trent familyEvolution of the RB211 and Trent family
Trent 8104Trent 8104
Trent800
Trent800
Trent700
Trent700
-22B-22B
-524B-524B -524C-524C TrentTrent
2000 and beyond2000 and beyond
TrentIFB
TrentIFB
-524D4-524D4
-524G-524G-524H-524H
RB211-24GRB211-24G
RB211-22RB211-22RB211-24CRB211-24C
RB211-24ARB211-24A
1975 1980 1985 1990 19951975 1980 1985 1990 1995
400
350
300
250
200
150
400
350
300
250
200
150
Thr
ust
(kN
)T
hrus
t (k
N)
75
50
25
75
50
25
Po
wer
(MW
)P
ow
er (M
W)
FutureTrent
FutureTrent
75
50
25
75
50
25
Po
wer
(MW
)P
ow
er (M
W)
RB211-24GUpgradeRB211-24GUpgrade
end
Industrial RB211 performanceIndustrial RB211 performance
009576/21 PPT18/03/99
60
50
40
30
20
10
0
5
10
15
Improved SFC and power
1975 1980 1985 1990 1995 2000
% P
ow
erin
crea
se%
SF
Cim
pro
vem
en
t
Improved componentefficiency
Improved materials
Advanced coolingtechniques
24G
RB211-24GUpgrade
24C
24A
-24A
-24C
-24G RB211-24GUpgrade
end
009576/22 PPT18/03/99
RB211-24G IP compressorRB211-24G IP compressor
Current standard Upgrade standard Current standard Upgrade standard
end
009576/23 PPT18/03/99
IP compressor 1st and 2nd stage rotorIP compressor 1st and 2nd stage rotor
end
MaterialsMaterials
009576/24 PPT18/03/99
end
Turbine technology developmentsTurbine technology developments
Approximate year of availability Approximate year of availability
009576/25 PPT18/03/99
1940 1950 1960 1970 1980 1990 2000 1940 1950 1960 1970 1980 1990 2000
Turbine temperature capabilityTurbine temperature capability
Cooling improvements
Coating developments
Cooling improvements
Coating developments
Firing tempFiring temp
SC cast
alloys
SC cast
alloysDC cast
alloys
DC cast
alloysConventionally
cast alloys
Conventionally
cast alloys
Wrought alloysWrought alloys
Fir
ing
tem
per
atu
re (
oK
)F
irin
g t
emp
erat
ure
(oK
)
1600 1600
1550 1550
1500 1500
1450 1450
1400 1400
1350 1350
1300 1300
1250 1250
1200 1200
1150 1150
1100 1100
Met
al t
emp
erat
ure
(o
C)
Met
al t
emp
erat
ure
(o
C)
1100 1100
1050 1050
1000 1000
950 950
900 900
850 850
800 800
end
Industrial RB211 - HP turbine rotor bladesIndustrial RB211 - HP turbine rotor blades
Aero -22B -524 -524G Trent
Ind -22 -24A/C -24G -24G Upgrade
Aero -22B -524 -524G Trent
Ind -22 -24A/C -24G -24G Upgrade
009576/26 PPT18/03/99
Forged Conventional
casting
DS
casting
Single
crystal
end
Trent HP turbine bladeTrent HP turbine blade
Low pressure loss
cooling passages
Sophisticated '3D' shaped
film cooling holes
Advanced internal heat
transfer augmentation
Increased efficiency
trailing edge
009576/27 PPT18/03/99
Cross flow
ribs
View with top of shroud removed
to show cooling passages
Damper
LP
Cooling airHP
end
IntegrationIntegration
009576/28 PPT18/03/99
end
Industrial RB211/Trent product familyAeroderivative heritageIndustrial RB211/Trent product familyAeroderivative heritage
009576/29 PPT18/03/99
Aero RB211 / TrentAero RB211 / Trent
3 shaft flexibility3 shaft flexibility
Industrial RB211Industrial RB211 Industrial TrentIndustrial Trent
Common component flowCommon component flow
end
Derivation of industrial unit from aero engineDerivation of industrial unit from aero engine
Aero based RB211 industrial unit - 30.78 MW
009576/31 PPT18/03/99
New compressor
first stage
Power
turbine
Power
drive
Basic aero engine RB211-524
222.4kN thrust (50,000lb)
end
Industrial Trent derived from aero Trent 800Industrial Trent derived from aero Trent 800
009576/32 PPT18/03/99
New bleed duct
New bleed duct
Modified casingsModified casings
Low emission combustion system
Low emission combustion system
Modified power turbineModified power turbine
Industrial TrentIndustrial Trent
Aero TrentAero Trent
New compressorNew compressor
Common IP and HP systemsCommon IP and HP systems
end
Industrial RB211 modular constructionIndustrial RB211 modular construction
009576/33 PPT18/03/99
Air intake
Module 01 IP Compressor
Module 02 Intermediate
casing
Module 03
HP system
Module 04 IP turbine
Module 05
504 Kg
(1110lb)
366 Kg
(740lb)
800 Kg
(1765lb)320 Kg
(705lb)
418 Kg
(922lb)
end
Advantages of modular constructionAdvantages of modular construction
High gas generator availability
Maximised repair by local labour ease of transportation
Reduced spares holding
Optimised use of capital equipment
Updating and uprating capability
High gas generator availability
Maximised repair by local labour ease of transportation
Reduced spares holding
Optimised use of capital equipment
Updating and uprating capability
009576/34 PPT18/03/99
end
RB211 Upgrade - Gas generator developmentRB211 Upgrade - Gas generator development
Performance objectives -
Build on basic Industrial RB211 experience
Boost performance from modest flow and temperature
increases
Incorporation of improved efficiency HP compressor
How -
Use latest aero technology to achieve performance objectives
at low risk
- Aerodynamics - IP compressor flow increase
- Components - HP compressor
- HP turbine
- Materials - IP turbine
Performance objectives -
Build on basic Industrial RB211 experience
Boost performance from modest flow and temperature
increases
Incorporation of improved efficiency HP compressor
How -
Use latest aero technology to achieve performance objectives
at low risk
- Aerodynamics - IP compressor flow increase
- Components - HP compressor
- HP turbine
- Materials - IP turbine
009576/35 PPT009576/35 PPT18/03/9918/03/99
end
009576/36 PPT18/03/99
Gas generator development - Upgrade featuresGas generator development - Upgrade features
Performanceenhancingfeatures
Reliability/maintainability
features
RVDT VIGVcontrol
IPC OGVredesign
Revised HPspeed probe
HPC boroscoperelocated
ESD air supply
Turbine casingcooling
Single panelturbine support
CMSX4IPT blade
CMSX4HPT blade
OptimisedDLE combustion
system
Trent 800HP compressor
Increased flowIP compressor
end
COBERRA 6761COBERRA 6761
RB211-24GUpgrade
009576/37 PPT18/03/99
RT61
end
Allison 601 gas generatorAllison 601 gas generator
end
Allison 601 engine seriesAllison 601 engine series
601-KB9/-KC9 601-KB11/-KC11
601-KF9 (Marine) 601-KF11 (Marine)
601-KB9D/-KC9D 601-KB11D/-KC11D
end
Allison 601 engine configurationAllison 601 engine configuration
94.4 in (2396.9 mm)
Est. Weight 3,000 lbs
Introductory Engine
Performance
-Kx9 -Kx9 -Kx11 -Kx11 Natural Gas Diesel Natural Gas DieselPower, shp 9,000 8,765 11,000 10,500Power, kw 6,715 6,340 8,200 7,830Heat Rate, B/shp-hr 7,540 7,640 7,900 8,000
40 inch Dia.(1000 mm)
122.6 in (3114.0 mm)
40 inch Dia.(1000 mm)
Est. Weight 4,000 lbs
end
Allison 601 program statusAllison 601 program status
Rig Development TestingCombustion Rig Tests Complete
Compressor Rig Test Complete
Gas Generator Rig Testing Completed
Engine Development TestingPerformed Instrumented Diagnostic and Component Tests
Completed Functional Testing
Performance and Operability
Lubrication and Vent System
Gaseous and Liquid Fuels
Engine Endurance TestingCompleted 150 Hour Endurance Test
Assembly of 2000 Hour Field Endurance Engine in Process
Rig Development TestingCombustion Rig Tests Complete
Compressor Rig Test Complete
Gas Generator Rig Testing Completed
Engine Development TestingPerformed Instrumented Diagnostic and Component Tests
Completed Functional Testing
Performance and Operability
Lubrication and Vent System
Gaseous and Liquid Fuels
Engine Endurance TestingCompleted 150 Hour Endurance Test
Assembly of 2000 Hour Field Endurance Engine in Process
end
Industrial TrentIndustrial Trent
The world's most powerful and most efficient aeroderivative gas turbineThe world's most powerful and most efficient aeroderivative gas turbine
009576/38 PPT18/03/99
end
Industrial Trent modularityIndustrial Trent modularity
009576/39 PPT18/03/99
Intermediatecasing
Intermediatecasing
IP compressorIP compressor
Intercompressorduct
Intercompressorduct
LP compressorrotor
LP compressorrotor
Air intakecasing
Air intakecasing
GearboxGearboxHP core
and combustionsystem
HP coreand combustion
system
InterturbineNGV
InterturbineNGV
LP turbineLP turbine
end
Benefits of modern aeroderivatives over single shaft machinesBenefits of modern aeroderivatives over single shaft machines
2 Spool engines allows better compensation for in-service degradation
automatic aerodynamic re-matching between spools
Each compressor spool is short with good bearing support
no bowing of drum, excellent concentricity control
Short bearing centre allows close tip clearances, seal control
minimum performance loss, minimum degradation
Modular arrangement allows flexibility of maintenance
Single row variable compressor blading
No accessory drives
2 Spool engines allows better compensation for in-service degradation
automatic aerodynamic re-matching between spools
Each compressor spool is short with good bearing support
no bowing of drum, excellent concentricity control
Short bearing centre allows close tip clearances, seal control
minimum performance loss, minimum degradation
Modular arrangement allows flexibility of maintenance
Single row variable compressor blading
No accessory drives
009576/40 PPT18/03/99
end
009576/01 PPT18/03/99
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