Green rotorcraft - GRC1 - Innovative Rotor Blades - IPAS2011
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Green rotorcraft - GRC1 - Innovative Rotor Blades - IPAS2011






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Green rotorcraft - GRC1 - Innovative Rotor Blades - IPAS2011 Green rotorcraft - GRC1 - Innovative Rotor Blades - IPAS2011 Presentation Transcript

  • Green RotorCraft ITD Sub-project GRC1© 2011 – CSJU/GRC-ITD Members Innovative Rotor Blades 1 1
  • GRC1 – Innovative Rotor Blades : Objectives Objective “the development of active and passive technologies to provide the greatest possible reduction in rotor noise and fuel consumption” The main rotor of a helicopter is both the main user of power (and hence© 2011 – CSJU/GRC-ITD Members fuel), and the main source of intrusive noise. Working directly to improve the efficiency and reduce the noise of the main rotor is a highly effective way of reducing fuel usage, CO2 and NOX emissions, and rotorcraft generated noise levels. Current reduction targets are -8% hover power, -3% cruise power 2 and -6dB in noise on approach 2
  • GRC1 – Innovative Rotor Blades : Plan and Schedule 2008 2009 2010 2011 2012 2013 2014 2015 WP1 ‐ Technology Evaluation, Selection  and Development WP2 ‐ Model Rotor Design and Testing WP3 ‐ Full Scale Blade Design© 2011 – CSJU/GRC-ITD Members WP4 ‐ Whirl Tower Testing 3 3 View slide
  • GRC1 – Innovative Rotor Blades : Planned Results Following initial selection of technologies, the anticipated outcomes are - • ACTIVE TWIST – full scale demonstration of active twist system, with analysis to assess future exploitation challenges, benefits in line with GRC1 objectives and airworthiness / safety evaluation • ACTIVE GURNEY FLAP – full scale demonstration and testing of a full main rotor with a built-in, actively controlled Gurney flap system • PASSIVE ROTOR OPTIMISATION – full scale demonstration and testing of© 2011 – CSJU/GRC-ITD Members an optimised passive rotor on a whirl tower, with further analysis of other passive technology concepts • LAMINAR FLOW AEROFOILS – testing of laminar flow aerofoils installed on top of conventional main rotor blades • SUPPORTING TECHNOLOGIES – development of all necessary manufacturing techniques, control and power supply systems, and data 4 gathering capabilities necessary to support the physical demonstration activities 4 View slide
  • GRC1 – Innovative Rotor Blades : Participants • The GRC1 team includes rotorcraft OEMs, Research Institutions, Academia and independent SMEs Academia University of Twente Technical University of Delft© 2011 – CSJU/GRC-ITD Members SMEs Rotorcraft OEMs Airborne AgustaWestland Micromega Eurocopter LMS PZL Swidnik Eurocarbon Research Institutions CIRA DLR NLR 5 ONERA 5
  • GRC1 – Innovative Rotor Blades : Active Twist Concept Development of a full scale, active twist blade segment based on integrated piezoelectric actuators. Active twist will allow the blade shape to be changed in flight to improve performance and/or reduce rotor generated noise. - GRC1 partners are working to develop, build and test a full-scale representative rotor blade section with piezoelectric actuators built into the blade structure - Prototype actuators have been produced for testing, and evaluation work is© 2011 – CSJU/GRC-ITD Members underway - Detailed consideration has also been given to airworthiness requirements for this type of active blade system 6 6
  • GRC1 – Innovative Rotor Blades : Passive Blade Optimisation Development of an optimised integrated, 3D blade geometry aiming to maximise performance and minimise noise from a passive main rotor blade. An optimised full-scale blade will be tested on a whirl tower. The optimisation studies are using state of© 2011 – CSJU/GRC-ITD Members the art, multi-objective, genetic algorithms to assess all possible combinations of – - Blade chord distribution - Blade twist distribution - Additional blade features (e.g. anhedral) 7 7
  • GRC1 – Innovative Rotor Blades : Active Gurney Flaps An active Gurney flap system is being developed for a full scale main rotor blade. This technology will be thoroughly tested in 2D wind tunnel tests, in wind tunnel model rotor tests, and at full scale on a whirl tower. The active use of the Gurney flap is intended to modify the aerodynamic properties of the blade to improve efficiency and/or reduce noise. - New modelling and CFD techniques have been developed to study the operation and performance of active gurney flap systems© 2011 – CSJU/GRC-ITD Members - Additional partners have been recruited to design, manufacture and supply the actuation systems required for testing - Ongoing concept development work also includes control algorithms, analysis of potential failure modes and full aircraft 8 integration 8
  • GRC1 – Innovative Rotor Blades : Active Gurney Flaps The active Gurney flap system poses some difficult challenges for the design of a suitable actuation system due to the limited space available close to the trailing edge of a rotor blade - • preliminary studies have already been carried out by several GRC1 partners • additional partners will eventually be recruited through the Clean Sky CfP process to complete the design and manufacturing activities for the actuation systems© 2011 – CSJU/GRC-ITD Members 9 Possible Gurney flap deployment concepts 9
  • GRC1 – Innovative Rotor Blades : Active Gurney Flaps The development of suitable control algorithms is also a challenging area. All components of the active system must be accurately modelled to obtain truly representative results in Coupled analysing - • Force Simulation© 2011 – CSJU/GRC-ITD Members • system dynamic stability • Displacement • component forces • Velocity • aerodynamic loads • inertial loads in environment with high accelerations • power consumption 10 10
  • GRC1 – Innovative Rotor Blades : Active Gurney Flaps V Performance assessments so far have indicated that an active Gurney flap system could be capable of producing useful reductions in main rotor power requirements and noise – broadly in line with the original project objectives Ongoing studies are continuing to© 2011 – CSJU/GRC-ITD Members optimise the characteristics of the Gurney flap system in terms of – • radial position • chordwise position • azimuthal deployment • flap size 11 11
  • Clean Sky JU / Green RotorCraft ITD © 2011 by the CleanSky JU / Green Rotorcraft ITD (GRC) Members: AgustaWestland, Eurocopter, Liebherr-Aerospace, Hispano-Suiza, Thales Avionics Electrical Systems, Wytwornia Sprzetu Komunikacyjnego PZL Swidnik, Office National dEtudes et de Recherches Aérospatiales, Deutsches Zentrum für Luft- und Raumfahrt, Centro Italiano Ricerche Aerospaziali, SELEX Sistemi Integrati, Airborne Composites, Alphei Pueschel Roesler - Akustik Technologie Goettingen, Eurocarbon, Fibre Optic Sensors and Sensing Systems, LMS International, Microflown Technologies, Micromega Dynamics, Stichting Nationaal Lucht- en Ruimtevaartlaboratorium, Technische Universiteit Delft, Universiteit Twente,© 2011 – CSJU/GRC-ITD Members All rights reserved. This presentation material is provided for information of parties/persons invited to the meeting as indicated herewith. No information contained in this material may be disclosed to any other party/person, nor reproduced in whole or in part, nor used without the prior written consent of the specific GRC member(s) to which the information belong(s). 12 12