Gr\uf6nstedt, Tomas

Xisto, Carlos

Chalmers Research

The ULTIMATE project is funded by the European Union H2020 programme under GA no. 633436.LEMCOTEC Workshop for the Aeronautics IndustryPotsdam, Germany, December 6th, 2016A Search for the “ULTIMATE” Aero- EngineCarlos Xisto, Tomas Grönstedt Ultra Low emission Technology Innovations for Mid-century Aircraft Turbine Engines2LEMCOTEC Workshop06/12/2016Exploring synergistic combinations of radical core technologiesCall: MG-1.5-2014 - Breakthrough innovation for European AviationBudget: EUR 3,138,121.88 (100% financed by the EU)Duration: 36 months, September 2015 – August 2018Consortium: 10 partners (4 Universities, 4 Industries, 1 research institute and 1 technology management company)Coordination: Chalmers University of Technology Tomas Grönstedt Chalmers University of TechnologyDepartment Applied Mechanics412 96 Gothenburg, Swedene-mail: tomas.gronstedt@chalmers.seTel: +46 704 92 33 39Project Goals3LEMCOTEC Workshop06/12/2016Losses in a 2015 state-of-the-art TurbofanULTIMATE will attack the major loss sources “the Big Three”Combustor irreversibilities (1)Core exhaust heat losses (2)Excess of kinetic energy in the bypass flow (3) Grönstedt, T., Irannezhad, M., Lei, X., Thulin, O., Lundbladh, A., “First and second law analysis of future aircraft engines”.Journal of Engineering for Gas Turbines and Power”,136 (3), 2014The red cross-hatched areas may be captured –HOW?“Exergy, denoted ε, of a steady stream of matter is equal to the maximum amount of work obtainable when the stream is brought from its initial state to a state of thermal and mechanical equilibrium with its environment”4LEMCOTEC Workshop06/12/2016Project GoalsIntercooling & RecuperationExploring synergistic combinations of radical core technologies….together with advanced tube and wing configurationBottoming cyclesAdvanced low pressure system technologyConstant volume type combustionConcept and Approach 5LEMCOTEC Workshop06/12/2016• Combine and exploit synergies between radical technologies• Attack all three major sources simultaneously• Incorporate the new powerplants into an Advanced Tube and wing aircraft (TRL1)• Create and exploit multidisciplinary evaluation platform (TERA 2050) for powerplant development and optimization  Exploring synergistic combinations of radical core technologies• Technology assumptions for 2050o Turbomachinery efficiency;o High Pressure Turbine Temperature Capabilities;o Characterization of Heat exchangers;o Weight estimation and structural considerationso Reference cycles Concept and Approach 6LEMCOTEC Workshop06/12/2016Starting point!Powerplant for intercontinental configuration (architecture illustrated by Rolls-Royce UltraFan for 2025)Intra-European configurationCombustor Irreversebility7LEMCOTEC Workshop06/12/2016LEMCOTEC: Diferent composite cycle concepts Source: S. Kaiser et al., 2016Piston based composite cyclesAttack loss source #1Nutating disc composite cyclesPulse detonation combustionS. Kaiser et al “Composite Cycle Engine Concept with Hectopressure Ratio”. Accepted for publication in AIAA Jounal of Propulsion and PowerCore exhaust heat losses8LEMCOTEC Workshop06/12/2016LEMCOTEC: Involute spiral arrangement of IC for space optimizationSource: Zhao et al., 2015Attack loss source #2Bottoming cycleIntercoolingIC/Recuperation, with inter turbine burningLEMCOTEC: MTU concept for IRA engineX. Zhao and T. Grönstedt, "Conceptual design of a two-pass cross-flow aeroengine intercooler," Proc IMechE Part G: J Aerospace Engineering, vol. 229, no. 11, pp. 2006-2023, 2015Goulas, A., Donnerhack, S., Flouros, M., Missirlis, D., Vlahostergios, Z. and Yakinthos, K. “Thermodynamics cycle analysis, pressure loss and heat transfer assessment of a recuperative system for aero engines”, Journal of Engineering for Gas Turbines and Power, Vol. 137, 041205-1, (2015).Excess of Kinetic Energy9LEMCOTEC Workshop06/12/2016Attack loss source #3Variable pitch fan & area nozzleUltra-slim nacelle enabling tech.Boxprop Retractable nacelle Powerplant for intercontinental configuration (architecture illustrated by Rolls-Royce UltraFan for 2025)Intra-European configurationCombinations!Combinations11LEMCOTEC Workshop06/12/2016Intercooled Pulse Detonation Core+OpportunitiesPressure rise combustionReduction of  combustor irreversibility Reduced risk of auto-ignition at higher OPRHigher combustion pressure ratio with ICChallengesCompatibility between HPT and PDC flowNOx emissions Design of cooling systemNoise IC-PDC vs 2050 Turbofan-11.0% SFCCombinations12LEMCOTEC Workshop06/12/2016Intercooled cycle with Inter-turbine burning and a supercritical CO2 (S-CO2) bottoming cycleOpportunitiesWill allow considerably smaller and simultaneously more efficient cores Lowered NOx and CO2 emissions due to smaller fuel mass flows.The main heat exchanger behind the LPT may reduce noise emissions of the core jet.ChallengesAccurate simulation of thermal behavior of S-CO2heat exchangersRealistic prediction of S-CO2turbomachinery Off-Design Weight estimation of several componentsEngine will include intercoolingEngine will include inter-turbine reheatTurbine exhaust heat exchangerBottoming cycle turbomachinery can be geared to LP turbine shaftCombinations13LEMCOTEC Workshop06/12/2016Open-Rotor with nutating disc topping Nutating disc machines are located hereThe intercooler could be placed here, or in the pylonThe LPC may be an axi-centrifugal designOpportunitiesThe relatively higher power density leads to a reduced weight penalty as opposed to Piston combined cycles. Supposed reduced NOx emissions due to low residence times in the combustion chamber.Reduced combustion irreversibility and pressure rise combustionChallengesAccurate simulation of boosted nutating disk engine design point and off-design point performanceAccurate estimation of the overall weight.Accurate prediction of the heat release in the combustion chamber at design and off-design conditionsCombinations14LEMCOTEC Workshop06/12/2016Intercooled Piston Composite Cycle (with inter-turbine recuperation)Intercooled CCE vs baseline 2050 Turbofan +3.7% weight | -12.6% TSFC | -17.5% fuel burnOpportunitiesPressure rise combustionReduction of  combustor irreversibility Improves volumetric efficiencyReduces piston system weight considerably Challenges Demanding operating conditions for the piston systemConceptual design of intercoolers (limited space)Incorporation of recuperation in the design spacePotential synergistic combination of the CCE with recuperationScientific Approach15LEMCOTEC Workshop06/12/2016Developmentpartially qualitative selectionOptimization towards the SRIA 2050 targetsExploitationTERA 205016LEMCOTEC Workshop06/12/2016Techno-Economic Risk Assessment platform for ULTIMATEThe race is on - Ultimating17LEMCOTEC Workshop06/12/2016123Mission fuel burn NOx and noise?Mission fuel burn NOx and noise?Mission fuel burn NOx and noise?M36M12IC + PDC + BPIC + PT + ORIC + ND + ORFly longer (!) with the best score.Industry input will support our “scoring” of concepts.Technical feasibilityo How likely is a concept to fly?o NOx, CO2, Noiseo Methods for assessment  Support on technology roadmappingThe Champ (s)!18LEMCOTEC Workshop06/12/2016Fly longer and better!The Consortium19LEMCOTEC Workshop06/12/20164 Universities, 4 Industries, 1 Research Institute and 1 SMERRCUARTSFISAEMTUBHLCHALMERSGKNAUTHThank you!

A Search for the “ULTIMATE” Aero-Engine

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A Search for the “ULTIMATE” Aero-Engine

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