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Innovation Takes Off
Clean Sky 2 Information Day Engines ITD
François Mirville : SAFRAN/Snecma
Simon Weeks: Rolls-Royce Gerhard Ebenhoch: MTU Aero Engines
Brussels , 16th sept 2014
From Clean Sky towards Clean Sky 2
• Clean Sky, through SAGE (Sustainable And Green Engines), 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
High-Level Objectives
• Environmental objectives for the engines ITD are to demonstrate at TRL6 the following:
– 20-30% reduction in CO2*
– Significant contribution to ACARE 2020 NOx reduction
target (-80%*)
– Upto -11EPNdB per operation reduction in noise*
• Industrial objectives are to ensure future competitiveness of European Aero Engine industry, securing trade, employment and high technology knowledge and skills
*relative to year 2000 baseline
High-Level Objectives
• Engine ITD timelines are as follows:
WP1 SNECMA
2014 2018 2022 2016 2020
WP2 SNECMA
WP3 TM
WP4 MTU
WP5 RR
WP6 RR
WP7 SMA
VHBR Turbofan Long Range
VHBR Turbofan Middle of Market
Business Aviation Regional Turboprop
Geared engine Configuration (HPC-LPT)
Open Rotor Flight Test
UHPE demonstrator
Flight Demonstrator
Ground Demonstrator
Ground Demonstrator
Ground Demonstrator
Flight Demonstrator
Technology Demonstrator
…timescales to be defined… Small Aircraft Engine
Setup and Implementation
WP1- SNECMA Clean Sky 2 activities: Contra Rotating Open Rotor for Flight Test Demo
This WP is now integrated in IADP_LPA Large Passenger Aircraft – WP1.1.- CROR Engine Demonstrator FTD 2 topics issued in CS2-CPW1 : PoWer Turbine of the Flight Demonstrator Contra Rotative Open Rotor (CROR) Engine - JTI-CS2-CPW-LPA-01-05 Rotating Frames of the Flight Demonstrator Contra Rotating Open Rotor (CROR) Engine - JTI-CS2-CPW-LPA-01-06 See IADP_LPA presentation from Cleansky 2 Brussels infoday sept 16th
Open Rotor engine
Snecma proprietary data
Setup and Implementation
WP2 SNECMA Clean Sky 2 activities: Ultra High Propulsive Efficiency for SMR aircraft
Main Technology Objectives from design to ground test of an engine demo to validate LP modules & nacelle technologies Key Technologies Low pressure ratio fan / variable area fan nozzle Low weight / low drag fixed or rotating structures and nacelle. 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, controls and systems components, shafts, bearings 2 topics issued in CS2-CPW1 : Turbine Rear Frame and LP Shaft , Power GearBox
UHBR turbofan for SMR aircraft
Snecma proprietary data
Schedule of WP2 – Snecma UHPE
CS2 ENG Info day, 16th September 2014
Quartile 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4
Studies of best candidates for High
Propulsive Efficiency PPS concepts, ▼
incl. nacelle aspects
Preliminaty studies and choice of demo
concept adequate to mature UHPE concept ▼
(use of existing HP core & incl. nacelle aspects)
▼
Preliminary design
▼
Detailed Design
Manufacturing
▼
Demo instrumentation, assembly & bench update
▼
Ground test
▼
Result analysis
TRL Progresses 3 4 5
ready for ground test
M4: demo 1st run
D3: Report on ground test
2021 20222015 2016 2017 2018 20192014
D1: demo selection
M2: PDR
M3: CDR
D2: Engine & bench
M1: concept selection
2020
Snecma proprietary data
CS2 ENG Info day, 16th September 2014
Snecma Core Partner Calls (JTI-CS2-CPW-ENG-01-01)
Estimated Topic
Value 10 M€
Leading
Company SAFRAN/Snecma
Duration of the
action 9 years
Start
Date
April
1st2015
Strategic Topic Number Title
1
Low Pressure Turbine Rear Frame and Low Pressure Spool Shaft
for Ultra High Propulsive Efficiency (UHPE) Demonstrator for
Short / Medium Range aircraft
Duration 9 years
Start Date April 1st 2015
Low Pressure Turbine Rear Frame (TRF) and Low Pressure Spool (LPS) Shaft for Ground Test UHPE Demo Engine (GTD): Design the TRF and LPS modules/parts Manufacture the TRF and LPS modules/parts Assembly and Instrumentation of the TRF and LPS modules/parts Support the Ground Test of the UHPE Demo Engine for the TRF and LPS modules/parts
Low Pressure Spool Shaft (LPS) for Scale 1 Component Tests: Manufacture the LPS module/parts and rig adaptations Assembly and instrumentation Scale 1 Component Tests: to demonstrate mechanical capacity of the shaft
Snecma proprietary data
CS2 LPA-IADP Info day, 4th September 2014
Snecma Core Partner calls (JTI-CS2-CPW-ENG-01-02)
Estimated Topic
Value 10 M€
Leading Company SAFRAN/Snecma
Duration of the
action 9 years
Start
Date
April 1st
2015
Strategic Topic Number Title
2 Power GearBox (PGB) for Ultra High Propulsive Efficiency
(UHPE) Demonstrator for Short / Medium Range aircraft
Duration 9 years
Start Date April 1st 2015
PGB Module for Ground Test UHPE Demo Engine (GTD) Design of the PGB Module/parts and its equipment ,Manufacturing Assembly and Instrumentation of the PGB module for Ground Test UHPE Demo Engine (GTD) PGB Module for Scale 1 Component Tests Design of rig adaptations for Scale 1 Component Tests Manufacturing of two PGB Modules and of rig adaptations for Scale 1 Component Tests Assembly and instrumentation Scale 1 Component Tests: These tests are rotating, mechanically loaded, back-to-back tests aiming at demonstrating mechanical capacity of PGB parts and Module.
Snecma proprietary data
Setup and Implementation
WP3 Turbomeca Clean Sky 2 activities: Main Technology Objectives From design to ground test of a new turboprop engine demo (1800-2000 thermal shp) for business aviation and short range regional. Improvement of advanced core engine ARDIDEN3
Key Technologies HP core small size (high pressure ratio, low NOx combustor) Advanced propeller / air inlet / gear box Controls, lub & actuation systems
Potential Partner Participation : Propeller Power gear box and accessory gear box Air inlet & Nacelle Innovative accessories (oil, bleed, starter,..)
ARDIDEN 3 Existing turboshaft to be modified for CS2 TP
CS2 ENG Info day, 16th September 2014
Turbomeca Core Partner Call (JTI-CS2-CPW-ENG-01-03)
Estimated Topic
Value 13.5 M€
Leading
Company SAFRAN/Turbomeca
Duration of the
action 4 years
Start
Date
April
1st2015
Strategic Topic Number Title
1 Business Aviation / Short Regional TP demonstrator Front Power
Plant Module
Duration 4 years
Start Date April 1st 2015
Power & accessory Gear Box and Propeller system for Ground Test Ardiden 3TP engine demo: • Design & manufacture the PGB as a whole module
• Design & manufacture the propeller, including the propeller controls
• Assessing global integration optimization, in particular using CFD tools, of the Front Power Plant Module
Turbomeca proprietary data
Setup and Implementation
Rolls-Royce Clean Sky 2 activities are split into two work packages:
Integration
Transmissions
Control & Power Systems
Externals & Structures
Turbines
Composites
WP6: VHBR technologies for the long range airliner market with
Engine Demonstrator
WP5: underlying technologies for VHBR engines with focus on the “Middle-of-
Market” short range aircraft
14 Setup and Implementation Initial areas for participation (Work Package 5):-
Composite/Metallic/Hybrid Outlet guide vanes
Intercase (Integrated IP/HP
compressor)
Low speed composite
fan system
Variable Cold-Nozzle System
Integrated Nacelle
High speed
low-pressure turbine
High speed high
temperature
roller/thrust/journal
bearings
Advanced Engine
Health Monitoring
Oil System Management
System Design and
Integration
More electric engine technology
(including electric pumping and actuation)
Rolls-Royce Core Partner calls, Wave 1
• Rolls-Royce have issued two calls for Core Partners in Wave 1
• Both are aimed at the VHBR demonstrator
– IP Turbine technology
– Structural technology
• Both are important to the success of the RR programme and have been launched first due their criticality VHBR -
ULTRAFAN ™
Rolls-Royce proprietary data
Contacts for Rolls Royce : Keith Nurney : [email protected]
• Technical description, WP5.2, WP6.1:
Rolls-Royce Core Partner calls, Wave 1
IP Turbine Technology – VHBR engine €40M, minimum 5 years
WP5.2: Technologies for IPTs
1. Aerodynamic Design and Testing 2. Aeromechanical Assessment 3. Material evaluation and development 4. Methods development 5. Noise management technologies
WP6.1.1: IPT Demonstrator Modules
1. Sub-System Aspects and Analyses 2. Module Integration 3. Manufacturing of Demonstrator Module parts 4. Instrumentation of Demonstrator Module
hardware 5. Support for Module flight clearance 6. Demonstrator Module delivery 7. Test Data Analyses
Rolls-Royce proprietary data
• Technical description, WP 5.1, 6.1:
Rolls-Royce Core Partner calls, Wave 1
Structural Technology – VHBR engine €10M, minimum 5 years
• Research into and conceptual design / down-selection/ detailed design of an Intermediate compressor case.
• Associated technology/manufacturing demonstration including manufacturing trials, rig testing and modelling
• Manufacture of three sets of hardware; two sets for ground test, one set for use on a flying test bed.
Rolls-Royce proprietary data
Setup and Implementation
WP4 MTU Clean Sky 2 activities:
Main Technology Objectives Rig and Engine Testing and Validation of Compressor and Turbine
Technology to further reduce Emissions
Key Technologies Aerodynamic Integration Material Technologies Manufacturing Technologies
Timeframe: 2015 - 2021 Potential Partner Contribution Design and manufacturing of structural casings in Compression
and Expansion System, test support
Core Partner 2 • LPC design and manufacturing • ICD design and manufacturing
Setup and Implementation
WP4 Core Partner Involvement in Rig and Engine Demo
HPC
ICD LPC Core Partner 1
• Aero method development and design • Test bed adaptation, testing and test
evaluation
MTU Aero Engines • Compression system design lead • HPC design and technology
Compressor Rig
Core Partner 2
• Exhaust system design • Manufacturing of test
hardware • Material and component
validation tests
MTU Aero Engines • Expansion system design lead • MTF and LPT design and technology
Engine Demo
Setup and Implementation
Compression System Development
Development of multidisciplinary Tools
Design of Sub modules using multidisciplinary Tools
Testbed Design or adaptation and Testing
Analysis and evaluation of test results
WP4 Core Partner [1] Involvement “Aerodynamic design and testing of advanced geared fan engine modules“ (WP4.1 / WP4.2 / WP4.6)
HPC
ICD LPC
Compressor Rig
Setup and Implementation
WP4 Core Partner [2] Involvement “LPC, ICD and TEC development for next generation geared fan engines“ (WP4.1 / WP4.5)
Compression System Development
WP4.1 Development of ICD including LPC Backend • Integrated aerodynamic design • Mechanical design and structural optimization • Design and analytical substantiation • Materials and manufacturing technologies • Manufacturing of test hardware • Test instrumentation • Material and component validation tests (TRL 6)
HPC
ICD LPC
Expansion System Development WP4.5 Development of Turbine Exit Casing and Mixer Integrated aerodynamic and acoustic design Mechanical design and Structural optimization Design and analytical substantiation
(aerodynamics, acoustics, structures) Materials and manufacturing technologies Manufacturing of test hardware Test instrumentation Material and component validation tests (TRL 6)
Compressor Rig Engine Demo
Focal Points Engines ITD
Contacts for Safran :
•François Mirville (Snecma) : [email protected]
•Eric Seinturier (Turbomeca) : [email protected]
•Christophe Diette (Turbomeca) : [email protected]
•Jean-Roch Cossa (Safran) : [email protected]
Contacts for Rolls Royce :
•Brett Hands : [email protected]
•Keith Nurney : [email protected]
•Simon Weeks : [email protected]
Contacts for MTU Aero Engines:
•Gerhard Ebenhoch : [email protected]
•Gunnar Klaus : [email protected]
