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The Rolls-Royce Trent Engine 5 October 2000 Michael Cervenka Technical Assistant to Director - Engineering & Technology.

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Presentation on theme: "The Rolls-Royce Trent Engine 5 October 2000 Michael Cervenka Technical Assistant to Director - Engineering & Technology."— Presentation transcript:

1 The Rolls-Royce Trent Engine 5 October 2000 Michael Cervenka Technical Assistant to Director - Engineering & Technology

2 World No 2 in aero-engines World leader in marine propulsion systems Developing energy business Annual sales of over £4.5 billion Orders of over £13 billion World No 2 in aero-engines World leader in marine propulsion systems Developing energy business Annual sales of over £4.5 billion Orders of over £13 billion Rolls-Royce Today

3 Newtons 3rd Law EquilibriumReactionAction Thrust = Mass x Velocity (MV) MV

4 Propeller versus Jet Propulsion Propeller - moves LARGE MASS of air at low velocity Jet - moves small mass of gas at HIGH VELOCITY Mv aircraft mV jet Thrust = M(v aircraft - v jet ) mV aircraft Thrust = m(V aircraft - V jet ) Mv jet

5 Jet Engine Layout Compressor Combustion Chamber Turbine Shaft Exhaust Nozzle mV aircraft mV jet

6 Civil turbofan - Trent Civil turbofan - Trent Different Jet Engine Types Military turbofan - EJ200 Military turbofan - EJ200

7 Different Jet Engine Types - Mechanical drive Turboprop - AE 2100 Turboshaft - RTM322 Marine Trent Industrial Trent

8 Piston Engine versus Turboprop Piston engine Jet engine driven propeller (Turboprop) Air intake Compression Combustion Exhaust Intermittent Continuous

9 Pressure and Temperature Pressure (atmospheres) 0 40 Temperature (degrees C)

10 Axial Compressor and Turbine Operation

11 Stationary Nozzle Row Turbine Stages Gas flow Compressor Stages Stationary Vane Row Rotating Rotor Row Rotating Rotor Row Stationary Vane Row Airflow Rotating Rotor Row Rotating Rotor Row Stationary Nozzle Row

12 Multiple Shafts - Trent 95,000 lbs Thrust HP System 6 Compressor stages 1 Turbine stage >10,000 rpm HP System 6 Compressor stages 1 Turbine stage >10,000 rpm IP System 8 Compressor stages 1 Turbine stage >7,500 rpm IP System 8 Compressor stages 1 Turbine stage >7,500 rpm LP System 1 Fan stage 5 Turbine stages >3,000 rpm LP System 1 Fan stage 5 Turbine stages >3,000 rpm

13 Combustor Operation

14 Primary zone Intermediate zone Dilution zone Fuel spray nozzle

15 Reverse Thrust 85% thrust 15% thrust Net 25% to 30% thrust

16 New Product Introduction Process Stage 1: Preliminary Concept Definition Stage 2: Full Concept Definition Stage 3: Product Realisation Stage 4: Production Stage 5: Customer Support Capability Acquisition Product definition stages Preliminary concept defined for planning purposes Full concept defined, product launched Product developed, verified and approved Product produced and delivered to customer Product used by customer

17 New Project Planning Process BUSINESS MODEL Units sold Unit Cost Selling Price Concessions Sales Costs Development Costs Guarantee Payments Spares Turn Spares Price BUSINESS MODEL Units sold Unit Cost Selling Price Concessions Sales Costs Development Costs Guarantee Payments Spares Turn Spares Price ENGINEERING MODEL Safety Unit Cost Weight Noise Emissions Geometry Reliability Operability Performance ENGINEERING MODEL Safety Unit Cost Weight Noise Emissions Geometry Reliability Operability Performance MARKETING MODEL Market Size Selling Price Concessions Operating Costs Payload Range Maintenance Costs Fuel Burn Commonality MARKETING MODEL Market Size Selling Price Concessions Operating Costs Payload Range Maintenance Costs Fuel Burn Commonality

18 102 Million Hours of Service RB211 & Trent operating hours August B 26.7 million hours million hours million hours Trent 2.2 million hours 4260 engines ordered 3592 engines delivered 103 customers currently flying with RB211 or Trent engines Million hours Entry into service D -535C -535E4 -524G -524H Trent 700 Trent

19 Why 3 Shafts? Short / Medium-Haul (8, ,000lbs thrust): Long / Medium-Haul (40, ,000lbs thrust): Acquisition Cost Maintenance Simpler engine, hence moderate: - Overall pressure ratio - Turbine entry temperature - Bypass ratio Two-Shaft Configuration Three-Shaft Configuration Requires high: - Overall pressure ratio - Turbine entry temperature - Bypass ratio Range Fuel consumption

20 Evolution of Trent Family Fan diameter - in Trent 800 Trent 8104 Trent 900 Trent 700 Trent 500 Trent 600 RB G/H-T 60,000lb 72,000lb 95,000lb104,000lb 56,000lb 65,000lb 80,000lb Scaled core Boeing 777 Airbus A3XX Airbus A330 Airbus A340 Boeing 767 Boeing 747

21 Trent 700 & 800 Trent 700 Trent 800 Area of significant commonality Area of main geometric change Fan diameter increased to 2.8m (110.3in.) Five-stage LP turbine Single crystal HPT Single Crystal Uncooled IP turbine blade Fan diameter 2.47m (97.4in.) Four-stage LP turbine Phase 5 low emissions combustor 8 Stage IPC 3 Variables

22 Trent 500 Trent 700 Trent 500 Scaled IP & HP compressor 3D Aerodynamics Scaled combustor with tiled cooling HP & IP turbines have increased blade speeds High lift LP turbine blading

23 Material Strength Specific Strength Nickel Alloy Steel Aluminium Alloy Titanium Alloy Temperature

24 Engine Materials Titanium Nickel Steel Aluminium Composites Titanium Nickel Steel Aluminium Composites

25 Fan Blade Technology + 4% efficiency Clappered Wide-chord fan

26 Wide-chord Fan Technology Honeycomb construction 1st generation: nd generation: 1995 DB/SPF construction

27 Fan Section

28 Swept Fans

29 Compressor Aerodynamics

30 Trent 500 Tiled Combustor Cold supporting wall Cast tile Thermal barrier coating Tiles reduce wall cooling air requirements making more air available for NOx reduction A significant cost reduction relative to conventional machined combustors is also achieved Large airspray injectors for improved mixing and smoke control Large primary zone volume for altitude re-light Small total volume for NOx control

31 Improvements in Materials Equiaxed Crystal Structure Equiaxed Crystal Structure Directionally Solidified Structure Directionally Solidified Structure Single Crystal

32 Turbine Cooling Multi-pass Cooling air Thermal Barrier Coating Single pass

33 Performance Trends Straight jet Low bypass Medium bypass High bypass %sfc improvement (bare engine) Datum Avon 1958 Conway 1960 Spey B B4/D E G/H Propulsive efficiency Component efficiency Cycle efficiency Thermal efficiency RB211Trent

34 Electric Engine Concepts Air for pressurisation/cabin conditioning supplied by dedicated system All engine accessories electrically driven Generator on fan shaft provides power to airframe under both normal and emergency conditions Internal active magnetic bearings and motor/generators replace conventional bearings, oil system and gearboxes (typical all shafts) Pylon/aircraft mounted engine systems controller connected to engine via digital highway New Engine Architecture with reduced parts count, weight, advanced cooling, aerodynamics and lifing

35 Compressor Weight Reduction Conventional disk & blades Blisk - up to 30% weight saving Bling - Ti MMC - up to 70% weight saving

36 Metal Matrix Composites Titanium Metal Matrix Composite Titanium Alloy Nickel Superalloy Specific Strength Temperature (degrees C)

37 Future Emissions Improvements Pre-mixed double-annular combustor Pilot Main Double-annular combustor Pilot Main

38 Blended wing aircraft may offer up to 30% reduction in fuel consumption - 40% if combined with electric engine concepts Future Aircraft Configurations Flying wing Large diameter duct Gas generator Contra-rotating turbine Contra-rotating fan

39 Conclusion The three-shaft concept is now recognised as a world leader Customer-focused competitive technology is critical to its success Success is a tribute to many generations of people The RB211 & Trent family has a long and secure future

40 Rolls-Royce


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