Innovation Takes Off 1
C lean Sky 2 Information Day dedicated to the 6 th Call for Proposal (CfP06) ENGINE ITD SAFRAN Rolls-Royce Brussels, 22 February 2017 Innovation Takes Off
ENGINE – ITD in Clean Sky 2 3
From Clean Sky towards Clean Sky 2 • Clean Sky, through SAGE (S ustainable A nd G reen E ngines ), is delivering significant step changes in key engine technologies along the following themes: – Open Rotor, Composites, Lean Burn combustors, high power gearboxes, enhanced turbines and compressors, advanced materials and improved structures • Clean Sky 2 is about providing and demonstrating new engine technology for the whole of the civil market • The Clean Sky 2 engines ITD will build on Clean Sky and demonstrate technology at a whole engine level
Overview of the ITD/IADP High-Level Objectives • Environmental objectives for the engines ITD are to demonstrate at TRL6 the following: – 20-30% reduction in CO 2 * – Significant contribution to ACARE 2020 NO x reduction target (-80%*) – Upto -11EPNdB per operation reduction in noise* *relative to year 2000 baseline • Industrial objectives are to ensure future competitiveness of European Aero Engine industry, securing trade, employment and high technology knowledge and skills
ITD ENGINES Work Breakdown Structure WP0: ITD Coordination (RRUK / Safran Aircraft Engines / MTU) WP2: UHPE Demonstrator for SMR aircraft (Safran Aircraft Engines) WP3: Business Aviation/SR Regional TP Demonstrator (Safran Helicopter Engines) ENGINE ITD WP4: Advanced Geared Engine Configuration (MTU) WP5: VHBR Middle of Market Turbofan Technology (RRUK) WP6: VHBR Large Turbofan Demonstrator (RRUK) WP7: Light weight and efficient jet-fuel reciprocating engine (Safran SMA) WP8: Reliable and more efficient operation of small turbine engines (PAI/GE Avio) WP9: ECO Design Activities (MTU / Safran Aircraft Engines / RRUK / FhG)
WP2 : Ultra High Propulsive Efficiency for SMR aircraft – Safran Aircraft Engines Main Technology Objectives from design to ground test of an engine demo to validate LP modules & nacelle technologies Key Technologies Low pressure ratio fan High power gear box High efficiency LP turbine & LP compressor Engine / aircraft specific integration Potential Partner participation: Fixed structures in propulsive system, low pressure turbine components, UHBR turbofan for SMR aircraft controls and systems components, shafts, bearings Safran Aircraft Engines proprietary data
WP3 : Business Aviation/SR Regional TP Demonstrator – Safran Helicopter Engines • Main Technology Objectives – From design to ground test of a new turboprop engine demo for business aviation and short range regional. – Improvement of advanced core engine From ARDIDEN 3 existing technologies turboshaft engine to full Integrated Turboprop System • Key Technologies – HP core small size – Advanced propeller / air inlet / gear box – Controls, lub & actuation systems
WP3 : Business Aviation/SR Regional TP Demonstrator – Safran Helicopter Engines
WP5 : VHBR Middle of Market Turbofan Technology WP6 :VHBR Large Turbofan Demonstrator Rolls-Royce Clean Sky 2 activities are split into two work packages: WP5: underlying technologies for VHBR WP6: VHBR technologies for the engines with focus on the “Middle -of- long range airliner market with Market” short range aircraft Engine Demonstrator Integration Composites Turbines Transmissions TM UltraFan Externals Control & & Structures Power Systems
WP8 :Reliable and more efficient operation of small turbine engines – Piaggio Aero / GE AVIO • Next generation turboprop engines and propeller for up to 19 seats aircraft PAI (WAL, requirement definition and integration with SAT GAM) Main Technology Objectives Virtual Engine Integration Technology Maturation Component/Module Validation Key Technologies Material Technologies Manufacturing Technologies Compressor Combustor Turbine Timeframe: 2015 - 2019
Overview of the ITD/IADP Engine ITD timelines 2016 2020 2022 2014 2018 Safran Aircraft WP2 UHPE demonstrator Ground Demonstrator Engines Safran WP3 Business Aviation Ground Demonstrator Helicopter Regional Turboprop Engines WP4 Geared engine Ground Demonstrator MTU Configuration (HPC-LPT) VHBR Turbofan WP5 Technology RR Middle of Market Demonstrator WP6 VHBR Turbofan Flight Demonstrator RR Long Range WP7 Small Aircraft Engine Several demonstrators SMA WP8 Reliable and more PAI/GE Technology Demonstrator efficient operation of Avio small turbine engines
Overview of ITD ENGINES topics Type of Value (Funding Identification Code Title Topic Leader Action in M € ) JTI-CS2-2017-CfP06- Bearing chamber in hot environment RIA 1,7 Safran Aircraft Engines ENG-01-15 JTI-CS2-2017-CfP06- Torque measurement in turbofan IA 1 Safran Aircraft Engines ENG-01-16 JTI-CS2-2017-CfP06- Advanced turbine system performance improvement through dual-spool rig tests IA 1,1 GEDE ENG-01-17 JTI-CS2-2017-CfP06- Development of innovative methods and tooling for machining of slender shafts RIA 0,4 GKN ENG-01-18 JTI-CS2-2017-CfP06- Thermoplastic Thrust reverser cascade IA 0,45 SAFRAN NACELLES ENG-01-19 JTI-CS2-2017-CfP06- Long Fiber Thrust reverser cascade IA 0,45 SAFRAN NACELLES ENG-01-20 JTI-CS2-2017-CfP06- Safran helicopter Aerothermal characterization in the engine compartment RIA 0,9 ENG-01-21 Engines JTI-CS2-2017-CfP06- Safran helicopter Advanced Instrumented Engine cradle of the Turboprop demonstrator IA 0,4 ENG-01-22 Engines JTI-CS2-2017-CfP06- IP Turbine Rear Stages Aero/Noise Rigs IA 2,25 ITP ENG-03-15 JTI-CS2-2017-CfP06- Development of non-intrusive engine emissions instrumentation capability IA 2 RRUK ENG-03-16 JTI-CS2-2017-CfP06- VHBR Engine – Journal Bearing Technology IA 3 RRUK ENG-03-17 JTI-CS2-2017-CfP06- Development of capability to understand & predict sub-idle & idle behaviour of geared RIA 1,02 RRUK ENG-03-18 VHBR engines. JTI-CS2-2017-CfP06- Intermediate Compressor Case Duct Aerodynamics RIA 0,5 GKN ENG-03-19 JTI-CS2-2017-CfP06- Advanced investigation of ultra compact RQL reverse flow combustor RIA 0,6 GE AVIO ENG-04-07 JTI-CS2-2017-CFP06- 14 Topics 15,77 ENG Preliminary information from Clean Sky JU website
CS2- CfP#6- ITD ENGINE TOPICS • 9 topics : – WP2 (Safran Aircraft Engines & its Core Partners) : 6 topics – WP3 (Safran Helicopter Engines) : 2 topics – WP5 & 6 (Rolls Royce and its Core Partners) : 5 topics – WP8 (PAI / GE AVIO) : 1 topic 16
6th Call for Proposal (CfP06) – ENGINE ITD WP2 TOPICS CS2 Info day, 22 February 2017
CfP#6 – Bearing chamber in hot environment – Safran Aircraft Engines Topic Description Images / Graphics • Improvement of design of compact bearing chamber in hot environment. Mixture Heat rejection • Determine influence of key parameters on heat Conduction Oil flow rejections and heat transfer.
CfP#6 – Torque Measurement – Safran Aircraft Engines Topic Description Images / Graphics • Measuring shaft torque is key to understand aircraft engine behavior. Nevertheless space around engine shaft is limited and current torque meters or telemetry systems cannot be easily implemented. • The aim of this CFP is to develop a torque measurement system without telemetry for engine test bench (possibility to use on a flying test bench would be an asset but is not mandatory it will not be embedded on a commercial flight)
CfP#6 – Long Fiber Thrust Reverser Cascade – Safran Nacelles Topic Description Objective: To develop an alternative Thrust reverser Cascade that offers improvements in cost and aerodynamic performance. The applicant will :- Assist in the DFM of a the cascades Manufacture demonstrator articles for test Assist in the testing and analysis of results Main tasks 1. Definition phase (T0 – T3 months) i. Definition of technology issues ii. Definition of test plan 2. Manufacture and testing of sub-scale test articles. (T4 – T15) i. Prototype/ specimen manufacture ii. Mechanical testing 3. Manufacture and test of full size demonstrator articles (T16 – T30) i. Prototype/ specimen manufacture ii. Demonstrator testing 4. Anaylsis of results (T30 – T36) i. Results analysis ii. Final reporting
CfP#6 – Thermoplastic Thrust reverser cascade – Safran Nacelles Topic Description Objective: To develop an alternative Thrust reverser Cascade that offers improvements in cost and aerodynamic performance. The applicant will :- Assist in the DFM of a the cascades Manufacture demonstrator articles for test Assist in the testing and analysis of results Main tasks 1. Definition phase (T0 – T3 months) i. Definition of technology issues ii. Definition of test plan 2. Manufacture and testing of sub-scale test articles. (T4 – T15) i. Prototype/ specimen manufacture ii. Mechanical testing 3. Manufacture and test of full size demonstrator articles (T16 – T30) i. Prototype/ specimen manufacture ii. Demonstrator testing 4. Anaylsis of results (T30 – T36) i. Results analysis ii. Final reporting
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