APU on More Electrical Aircraft : a vision for the future (ppt)

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APU on More Electrical Aircraft : a vision for the future (ppt)


application/pdf APU on More Electrical Aircraft : a vision for the future (ppt) Jean-Francois Rideau, Stéphane Vaillant, Fabien Silet, Bernard Blanc
application/pdf APU on More Electrical Aircraft : a vision for the future Jean-Francois Rideau, Stéphane Vaillant, Fabien Silet, Bernard Blanc


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APU on More Electrical Aircraft : a vision for the future Jean-Francois RIDEAU, Stéphane VAILLANT, Fabien SILET, Bernard BLANC MICROTURBO, Chemin du Pont de Rupé, 31019 Toulouse Cedex, France Jean-francois.rideau@microturbo.fr; Stephane.vaillant@microturbo.fr; Fabien.silet@microturbo.fr; bernard.blanc@microturbo.fr Abstract The recent evolution of aircraft architecture tends to make electricity the main energy driver On-Board. The trade- off associated with, intent to show a sensible increase of the electrical power required by the different system on- board. This has a direct impact on the power off take from the main generators during the flight, on the main engine operability and also on the APU generator for ground operation. In this frame, the Auxiliary Power Unit System architecture needs to evolve. Extention to new functions has to be adressed as some technological limitations show off on the main engine for existing but also future architectures. MICROTURBO has started to adapt to MEA and AEA by certifying its Bleedless APU, the e_APU60 in May 2013 and will continue its move by proposing a new answer to Energy On-Board need. This solution named Power On Demand system intents to propose ”a la carte” power generation solutions that will be customized to match the proper Energy requirement of any type of aircraft architecture. The triple objectives of such system is : optimisation of the balance between the Propulsive and non Propulsive Energy On-Board, optimisation of the energetical efficiency of the aircraft and reduction of the environmental foot print of present and future aircraft program. Introduction The present functions of an APU are to provide pneumatic and electric power for ground operation to start the main engines and supply energy to the ECS, and during flight in case of main engine failures. Fig.1 : APU Location on Aircraft It is an essential link of the energy chain on board an aircraft as it contributes to the overall aircraft Fuel Burn performance and on the noise and pollution level. The APU carries its own specific Type Certificate « CS APU » (US « TSO-C77b) with two categories: Cat 2 : Ground Use Cat 1 : Flight Use (Icing, Ingestion, Starting system, Automatic shutdown) This gives the APU a specific role on-board as there are limited number of system carrying their own Type Certificate (Aricraft CS – 23/25, Engine CS – E, APU CS – APU, Propeller CS – P, Helicopters CS – 27/29). With the recent evolution of the aircraft architecture leading to consider More Electrical System on board, the functions attached to the APU have started to change to match the new functional requirements. e_APU60 : The first bleedless APU for Helicopter and Business Jets Anticipating this More Electrical Architecture evolution on Helicopter and Business Jet, MICROTURBO has launched Mid 2007 a demonstration program around a Bleedless APU, named e_APU. The specificity of the bleedless architecture lies in the compactness of the core engine, since no load compressor is required. This enables either to increase the Overall Pressure Ratio up to 8 for small gas turbine or to avoid adding a load compressor on the shaft for bigger APU’s. The impact is a direct decrease of more than 30% for the Specific Fuel Consumption and more than 10% on the Power to weight Ratio (comparison between competitors and e_APU60). Core EngineGearbox Air (Kg/s) kVA BleedAPU kVA BleedlessAPU Two types of Architectures Fig. 2 : Comparison between bleed / bleedless Architectures In the reduced time of 15months, the e_APU Team has put a brand new engine on a test bench for its first run, based on a bleedless architecture that had never been designed or manufactured before at MICROTURBO. On the 31 st December 2008, the e_APU60 performed its first run. The result of this first run has been the launch of a development contract with the first eAPU60 Customer on the 23 rd April 2009. Fig.3 : First e_APU60 FETT From Contract signature to first engine delivery with flight clearance occurred on the 3 rd July 2011, only 26 months have been necessary, performing successfully : • Performance • Endurance • Overspeed protection • Engine control • Containment module Fig. 4 : First Flight Clearance APU delivered The certification process has started 1 st January 2012 with the Award of the type certificate received in the 31 st May 2013 based on : CS-APU + CRI (overload conditions and hardware/software related) Category 1 “essential” Continuous icing capability validated by test at APU level DAL A (catastrophic event from airframe SSA) Full rotor containment High level of EMC/EMI FAA certification TSO C77b - May 2014 Altitude Test OAT -40°C to +60°C altitude à 20 000 ft (CEPR – Paris) APU containment test compressor & turbine (Microturbo) Attitude tests Pitch -40° à +40° Roll -20° à +20° (Microturbo) Icing test APU (CEPR - Paris) Helicopter installation, (Vienne ECU System test HIRF, lightning, Emissions (Toulouse) Vibration test (Microturbo) Fig.5 : Examples of certification test for APU’s With this certification, MICROTURBO has passed its first step to better answer to More Electrical Architecture requirements. From APU provider to System Provider With the appearance of More Electrical Architecture, the classical ATA Chapter frontiers have been shaken. Optimisation across ATA chapter appears to be the way to find differentiation at Aircraft Level. To capture those changes, MICROTURBO has decided to move from an APU Provider to a System Provider position. This has required the acquisition of competencies outside of the classical Turbine scope: Inlet/Exhaust aerodynamic Noise reduction Piloted Air Inlet Door Mounts/Struts But it has also required to deploy widely the Aerospace Recommended Practice 4754 in MICROTURBO. APU Exhaust (i.e. noise suppressor) Air Inlet / APU Composite APU fixtures (struts, fixations) Inlet Door + Actuator (controlled by the FADEC) Collar Eductor Tail Cone Test Rig Tail Cone Test Rig Test Rig Control Room Fig. 6 : System Integration competencies Results of this movement has been the development of the installation kit of the APS500D for Falcon 5X and APS2[800] for the Global 7000/8000, two major program in the business jet market, with a strong achievement of -6dBA vs ICAO (20m perimeter) in terms of noise reduction on an installation APU. PODS : The next step Ready as a system Provider, MICROTURBO is looking at the next step of APU’s that will align with the evolution of functional perimeter : At Product Level (Inside ATA49), the future aim to a diversification of the thermal source with the appearance of Fuel Cell or Piston Engine in complement or replacement of Gas Turbine At Functional Level (cross ATA 21/24/36/49), the future aim to an over-extended integration, additional functionality such as Main engine Load-Shading, Additional Power Unit, Autonomous Power Unit or Emergency Power Unit such as the IPS on JSF Moving from an APU World ………… ……………to a Power On Demand System Fig. 7 : MICROTURBO Vision on PODS This solution foreseen by MICROTURBO is the Power On Demand system that intents to propose ”a la carte” power generation solution to the Customer for the next generation of Aircraft. It will be customized to match the proper Energy requirement of any type of aircraft architecture. The concept of Power On Demand System looks for solution to the Aircraft Manufacturer and the Airline or final User in the frame of : Creating Value through : ‒ Understanding Energetic Efficiency at Aircraft Level ‒ Cross ATA Multi system Optimization Proposing adaptative Solutions for : ‒ Diversified Aircraft Fleet ‒ Multiple Operating Profile Setting up an « à la carte » approach matching the Airframer Strategy on : ‒ Global Integration ‒ Individual WP Guarantying a Certificability of Energy Solution The global Trade-Off will be driven by : The optimisation of the balance between the Propulsive and non Propulsive Energy On- Board, The optimisation of the energetical efficiency of the aircraft The reduction of the environmental foot print of present and future aircraft program. To achieve its objective, MICROTURBO has identified Technological Gaps that will need to be covered to have this solution ready for the next decade : - Multi System Compatibility and Optimization (ATA21/24/49) - Highly Reliable System with the target of reaching IFSD 10 -5 and MTBF 10.000OH equivalent to Main Engine - Increase of Power to Weight Ratio with the target of reaching -40% in 2030 at System Level - Enhanced Integration to match ACARE 2050 Requirement - Multi-Source energy Management to address Smart Grid solution at Aircraft Level A step-by-step approach based on classical TRL scale has been put forward using Demonstration Program led by SAFRAN Innovation to accelerate the process The first intermediate step is expected to reach TRL6 end of 2015. Conclusions In line with the MEA Architecture and the system trade-off studies, MICROTURBO has started in early 2008 the move to address more electrical architecture requirement by successfully developing the e_APU60 and becoming a Tier 1 System Provider. In the coming future, MICROTURBO will continue its transformation by proposing an evolution of the APU System in a Power On Demand System to its customer with the aim to address further optimization of the Energy Production and Management On Board the Aircraft.