1. Technology overview
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2. Industrial RB211 DLE gas generator
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3. Key technologies for industrial engines
Combustion systems
Control systems
Aero / thermodynamics
Materials
Integration
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4. Combustion Systems
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5. Rolls-Royce aeroderivative gas turbines
Trent
RB211
Avon
Allison 501 and 601
DLE technology is incorporated across the product range
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6. Influence of temperature on CO and NOx emissions
NOx emissions
ppm
CO emissions 30 25 20 15 10 5
120
100 40 80 60
NOx CO
Combustion temperature K
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7. Industrial 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
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8. Industrial 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
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9. Industrial 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
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10. Single annular combustor 18 off conventional fuel injectors
Industrial RB211 - Comparative diagrams of conventional and DLE combustor systems
DLE
Conventional
Single annular combustor
18 off conventional fuel injectors
9 off pre mix
lean burn combustors
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11. Industrial RB211 DLE combustion system
DLE fuel staging
Power
Primary zone
premix
Secondary zone
Conventional
combustion
Fuel
flow
Secondary
Primary
mixing duct
fuel
Central
diffusion
injector
Premix leanburn series staged combustor
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12. Industrial RB211 DLE combustion system
Torch igniter
Injector
Combustor
Air transfer casing
HP turbine
Discharge nozzle
Diffuser
Airflow
Pre-mix flow
Combustor
Cooling air
DLE 04 module
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13. Industrial Avon - Comparative diagrams of conventional and DLE combustor systems
8 off combustors
DLE
Existing cannular arrangement retained
but with pre mix lean burn combustors
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14. Industrial Avon DLE combustion system
Primary
fuel
Combustor casing
Secondary zone
fuel inlet
Primary zone
fuel feed
Pre-mix duct
Secondary
Fuel flow
Dilution zone
Power
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15. contained within this area support system retained
Industrial Avon DLE
DLE design changes
contained within this area
Existing engine
support system retained
Low risk programme
Changes confined to combustion system only
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16. Allison 601 Programme review
Dry Low Emissions system
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
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17. Control Systems
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18. Industrial 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
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19. Engine control system Interface
Existing unit control panel
DLE engine control system
Engine
sensors
Compressor control
Yard valves
Unit sequencing
Power turbine lube oil
18 channel
ignition
system
Fuel metering
units
Engine control unit
Interface
System integration requires minimal changes to existing UPC
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20. Aero / Thermodynamics
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21. Evolution of the RB211 and Trent family75 50 25
Power (MW) 75 50 25
Power (MW)
Trent
800
400
350
300
250
200
150
Thrust (kN)
Trent
700
Future
Trent
-524H
-524G
Trent
IFB
Trent
-524D4
-524B
-524C
RB211-24G
Upgrade
-22B
RB211-24G
RB211-24C
RB211-24A
RB211-22
2000 and beyond

22. Industrial RB211 performance60 50 40 30 20 10 5 15
Improved SFC and power
% Power
increase
improvement
% SFC
Improved component
efficiency
Improved materials
Advanced cooling
techniques
24G
RB211-24G
Upgrade
24C
24A
-24A
-24C
-24G
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23. RB211-24G IP compressor Current standard Upgrade standard 18/03/99
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24. IP compressor 1st and 2nd stage rotor
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25. Materials
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26. Turbine technology developments
Turbine temperature capability
Cooling improvements
Coating developments
Firing temp
SC cast
alloys
DC cast
Conventionally
cast alloys
Wrought alloys
Firing temperature (oK)
1600
1550
1500
1450
1400
1350
1300
1250
1200
1150
1100
Metal temperature (oC)
1050
1000
950
900
850
800
Approximate year of availability
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27. Industrial RB211 - HP turbine rotor blades
Forged
Conventional
casting DS
Single
crystal
Aero B G Trent
Ind A/C G G Upgrade
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28. Trent HP turbine blade Cross flow ribs View with top of shroud removed
to show cooling passages
Damper LP
Cooling air HP
Low pressure loss
cooling passages
Sophisticated '3D' shaped
film cooling holes
Advanced internal heat
transfer augmentation
Increased efficiency
trailing edge
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29. Integration
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30. Industrial RB211/Trent product family Aeroderivative heritage
Aero RB211 / Trent
3 shaft flexibility
Industrial RB211
Industrial Trent
Common component flow
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31. Derivation of industrial unit from aero engine
Aero based RB211 industrial unit MW
New compressor
first stage
Power
turbine
drive
Basic aero engine RB
222.4kN thrust (50,000lb)
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32. Industrial Trent derived from aero Trent 800
Modified power turbine
Common IP and HP systems
New compressor
Modified casings
New bleed duct
Low emission combustion system
Industrial Trent
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33. Industrial RB211 modular construction
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)
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34. Advantages 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
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35. RB211 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
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36. Gas generator development - Upgrade features
Performance
enhancing
features
Reliability/
maintainability
RVDT VIGV
control
IPC OGV
redesign
Revised HP
speed probe
HPC boroscope
relocated
ESD air supply
Turbine casing
cooling
Single panel
turbine
support
CMSX4
IPT blade
HPT blade
Optimised
DLE combustion
system
Trent 800
HP compressor
Increased flow
IP compressor
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37. COBERRA 6761
RB211-24G
Upgrade
RT61
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38. Allison 601 gas generator

39. Allison 601 engine series 601-KB9/-KC9 601-KB11/-KC11 601-KF9 (Marine)
601-KB9D/-KC9D
601-KB11D/-KC11D

40. Allison 601 engine configuration
94.4 in ( mm)
Est. Weight 3,000 lbs
Introductory Engine Performance
-Kx Kx Kx Kx Natural Gas Diesel Natural Gas Diesel
Power, shp 9, , , ,500
Power, kw 6, , , ,830
Heat Rate, B/shp-hr 7, , , ,000
40 inch Dia.
(1000 mm)
122.6 in ( mm)
Est. Weight 4,000 lbs

41. Allison 601 program status
Rig Development Testing
Combustion Rig Tests Complete
Compressor Rig Test Complete
Gas Generator Rig Testing Completed
Engine Development Testing
Performed Instrumented Diagnostic and Component Tests
Completed Functional Testing
Performance and Operability
Lubrication and Vent System
Gaseous and Liquid Fuels
Engine Endurance Testing
Completed 150 Hour Endurance Test
Assembly of 2000 Hour Field Endurance Engine in Process

42. Industrial Trent
The world's most powerful and most efficient aeroderivative gas turbine
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43. Industrial Trent modularity
Air intake
casing
Interturbine
NGV
Intercompressor
duct
Intermediate
casing
IP compressor
LP compressor
rotor
Gearbox
HP core
and combustion
system
LP turbine
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44. Industrial Trent modularity
Air intake
casing
Interturbine
NGV
Intercompressor
duct
Intermediate
casing
IP compressor
LP compressor
rotor
Gearbox
HP core
and combustion
system
LP turbine
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45. Benefits 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
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46. End of Technology overview Please press “Esc” to return to main menu
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