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Commit 381096e3 authored by Kristina Mazur's avatar Kristina Mazur
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Add V2527 engine

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2 merge requests!6Initial open source version,!3Renamed PW1127_JM_mod to PW1127_JM
This commit is part of merge request !3. Comments created here will be created in the context of that merge request.
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V2527-A5/V2527-A5.xml 0 → 100644
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<EngineDataFile>
<EngineDesignCondition Desc="Flight conditions for creating the bucket curve">
<flightAltitude Desc="Flight altitude for bucket curve" Unit="ft">35000</flightAltitude>
<flightMachNumber Desc="Mach number for bucket curve" Unit="-">0.8</flightMachNumber>
<thrust Desc="thrust at design point, ISA (value from source)" Unit="kN">17.01</thrust>
<SLST Desc="Sea level static thrust measured at SL, Mach 0, ISA (value from source)" Unit="kN">110.31</SLST>
<MCT Desc="Maximum continuous thrust measured at SL, Mach 0, ISA (value from source)" Unit="kN">98.92</MCT>
<FlatRatingTemp_MTO Desc="Delta ISA Temperature until the Maximum Takeoff Thrust (MTO) can be reached at sea level" Unit="K">31</FlatRatingTemp_MTO>
<FlatRatingTemp_MCT Desc="Delta ISA Temperature until the Maximum Continuous Thrust (MCT) can be reached at sea level" Unit="K">10</FlatRatingTemp_MCT>
<OPRMax_Climb Desc="Maximum overall pressure ratio in rating TO" Unit="-">32.8</OPRMax_Climb>
</EngineDesignCondition>
<MassProperties>
<Dry_mass Desc="Dry mass of the engine (value from source) excludes starter, exhaust nozzle and power source for ignition system" Unit="kg">2858</Dry_mass>
</MassProperties>
<Geometry Desc="Dimensions of the engine">
<OuterDimensions Desc="External dimensions of the engine">
<w_Engine Desc="Engine width" Unit="m">1.829</w_Engine>
<h_Engine Desc="Height of the engine" Unit="m">2.118</h_Engine>
<l_Engine Desc="Length of the engine" Unit="m">2.508</l_Engine>
</OuterDimensions>
<jetSpecific>
<FanDiameter Desc="Diameter of the fan" Unit="m">1.613</FanDiameter>
<turbineNoise>
<turbineRotorDiameter Desc="Diameter of LP Turbine rotor blades" Unit="m">0</turbineRotorDiameter>
<turbineInletArea Desc="Inlet area of LP turbine" Unit="m2">0</turbineInletArea>
<turbineRotorBladeNo Desc="No of rotor blades of LP turbine" Unit="-">0</turbineRotorBladeNo>
</turbineNoise>
<fanNoise>
<fanInletArea Desc="Inlet area of the fan of the engine" Unit="m2">0</fanInletArea>
<fanExhaustArea Desc="Inlet area of the fan of the engine" Unit="m2">0</fanExhaustArea>
<fanRotorBladeNo Desc="Number of fan rotor blades" Unit="-">0</fanRotorBladeNo>
<fanStatorVaneNo Desc="Number of stator vanes in fan section of engine" Unit="-">0</fanStatorVaneNo>
<fanRotorStatorSpacing Desc="The spacing between rotor blades and stator vanes, actually the ratio spacing/rotorChord (s/C)" Unit="-">0</fanRotorStatorSpacing>
<fanInletRotorDiameter Desc="Diameter of the fan inlet rotor" Unit="m">0</fanInletRotorDiameter>
<fanExhaustRotorDiameter Desc="Diameter of the fan exhaust rotor" Unit="m">0</fanExhaustRotorDiameter>
<fanTipDesignMach Desc="Design Mach number of the fan rotors tip" Unit="-">0</fanTipDesignMach>
<IGV Desc="Whether engine has Inlet Guide Vanes or not: 1:No 2:Yes" Unit="-">0</IGV>
<IFD Desc="Whether Inlet Flow Distortion is present or not: 1:No 2:Yes" Unit="-">0</IFD>
<INBB Desc="Calculate inlet broadband noise or not: 0:No 1:Yes" Unit="-">0</INBB>
<INTON Desc="Calculate inlet tonal noise or not: 0:No 1:Yes" Unit="-">0</INTON>
<DISBB Desc="Calculate exhaust broadband noise or not: 0:No 1:Yes" Unit="-">0</DISBB>
<DISTON Desc="Calculate exhaust tonal noise or not: 0:No 1:Yes" Unit="-">0</DISTON>
</fanNoise>
<combustorNoise>
<combustorEntranceArea Desc="Cross-sectional area of the entrance of combustor" Unit="m2">0</combustorEntranceArea>
</combustorNoise>
<jetNoise>
<flightVectorEngineAxisAngle Desc="Distance from source to observer in dimensionless form" Unit="-">0</flightVectorEngineAxisAngle>
<plugNozzle Desc="Boolean for whether there is a plug at nozzle or not: 1: Yes 0: No" Unit="-">0</plugNozzle>
<plugDiameter Desc="Diameter of plug at nozzle" Unit="m">0</plugDiameter>
<coaxialNozzle Desc="Boolean for whether the nozzles are coaxial or a single nozzle is present: 1: Yes 0: No" Unit="-">0</coaxialNozzle>
<actualPrimaryArea Desc="Geometrical area of the primary jet" Unit="m2">0</actualPrimaryArea>
<actualSecondaryArea Desc="Geometrical area of the secondary jet" Unit="m2">0</actualSecondaryArea>
</jetNoise>
</jetSpecific>
<propSpecific>
<PropDiameter Desc="Diameter of the propeller" Unit="m">0.0</PropDiameter>
<PropBlades Desc="Number of propeller blades" Unit="---">0</PropBlades>
</propSpecific>
</Geometry>
<Deck Desc="Engine performance map (Performance Deck). All values apply to the unscaled deck!">
<UnscaledSLST Desc="Unscaled Flat-Rated static thrust of the deck" Unit="kN" ValueFromSource="110.31">110.3126953</UnscaledSLST>
<UnscaledRatedPower Desc="Unscaled Flat-Rated static power of the deck (Shaft power)" Unit="kW">0</UnscaledRatedPower>
<ThrustDeckName Desc="Name of the engine deck containing the thrust values as a function of N1, Mach, and altitude" Unit="-">V2527-A5_FN.csv</ThrustDeckName>
<FuelDeckName Desc="Name of the engine deck containing the fuel flow values as a function of N1, Mach, and altitude" Unit="-">V2527-A5_WF.csv</FuelDeckName>
<CoreMassFlowDeckName Desc="Name of the engine deck containing the air mass flow values through the engine core as a function of N1, Mach, and altitude" Unit="-">V2527-A5_W25.csv</CoreMassFlowDeckName>
<OPRDeckName Desc="Name of the engine deck containing the OPR values (p3/p2) as a function of N1, Mach, and altitude" Unit="-">V2527-A5_P3q2.csv</OPRDeckName>
<EPRDeckName Desc="Name of the engine deck containing the EPR values (p5/p2) as a function of N1, Mach, and altitude" Unit="-">V2527-A5_P5q2.csv</EPRDeckName>
<TemperatureLimitDeckName Desc="Name of the engine deck containing the temperature limit values (GE uses TIT (turbine inlet temperature) where PW/IAE uses EGT (exhaust gas temperature measured at LP turbine exit) as a function of N1, Mach, and altitude" Unit="-">V2527-A5_St5_T.csv</TemperatureLimitDeckName>
<EGTDeckName Desc="Name of the engine deck containing the EGT values (exhaust gas temperature at LP turbine exit) as a function of N1, Mach, and altitude" Unit="-">V2527-A5_St5_T.csv</EGTDeckName>
<NLimitDeckName Desc="Name of the engine deck containing the rel. N2 values (maximum rel. rotation speed of HP shaft) as a function of N1, Mach, and altitude" Unit="-">V2527-A5_XN_HPC.csv</NLimitDeckName>
<WFToP3LimitDeckName Desc="Name of the engine deck containing the fraction values of fuel flow to p3 as a function of N1, Mach, and altitude" Unit="-">V2527-A5_WFqP3.csv</WFToP3LimitDeckName>
<N1nominal Desc="Maximum rotational speed for low pressure rotor - Limit in TCDS" Unit="1/min">5650</N1nominal>
<N2nominal Desc="Maximum rotational speed for high pressure rotor - Limit in TCDS" Unit="1/min">14950</N2nominal>
<WFToP3min Desc="Minimum fraction of fuel flow and p3 to prevent flame-out" Unit="-">45</WFToP3min>
<WFToP3max_MTO Desc="Maximum ratio of fuel flow to flow pressure after compression in rating TO" Unit="-">101.83</WFToP3max_MTO>
<WFToP3max_MCT Desc="Maximum ratio of fuel flow to flow pressure after compression in rating MCT" Unit="-">98.74</WFToP3max_MCT>
<TempMax_MTO Desc="Temperature limit at turbine exit (T49 or T5). Calculated by returning UnscaledSLST at TO-rating and ambient conditions at FlatRatingTemp_MTO" Unit="K">848.69</TempMax_MTO>
<TempMax_MCT Desc="Temperature limit at turbine exit (T49 or T5). Calculated by returning Maximum Continuous Thrust at MCT-rating and ambient conditions at FlatRatingTemp_MCT" Unit="K">772.35</TempMax_MCT>
<N2max Desc="Maximum relative rotational speed for high pressure rotor - Limit in TCDS" Unit="-">1.034</N2max>
<RelBleedMax Desc="Maximum bleed air extraction of the engine for aircraft onboard systems as a fraction of core mass flow" Unit="-">0.3</RelBleedMax>
<ShaftPowerExtractionMax Desc="Maximum shaft power extraction of the engine for aircraft onboard systems" Unit="kW">150</ShaftPowerExtractionMax>
<NfractionClimbRating Desc="Fraction of N_Climb/N_MCT; calculated such that N_Climb is about 0.9*N1 at SL, Ma=0, and ISA conditions" Unit="-">0.97</NfractionClimbRating>
<NfractionCruiseRating Desc="Fraction of N_Cruise/N_MCT; calculated such that Cruise thrust is met at design point (cf. EngineDesignCondition)" Unit="-">0.875</NfractionCruiseRating>
<St2FuelAirDeckName Unit="-">V2527-A5_St2_fa.csv</St2FuelAirDeckName>
<St2MachDeckName Unit="-">V2527-A5_St2_Mn.csv</St2MachDeckName>
<St2TotalPressureDeckName Unit="-">V2527-A5_St2_P.csv</St2TotalPressureDeckName>
<St2TotalTemperatureDeckName Unit="-">V2527-A5_St2_T.csv</St2TotalTemperatureDeckName>
<St2StaticTemperatureDeckName Unit="-">V2527-A5_St2_Ts.csv</St2StaticTemperatureDeckName>
<St2MassFlowDeckName Unit="-">V2527-A5_St2_W.csv</St2MassFlowDeckName>
<St3FuelAirDeckName Unit="-">V2527-A5_St3_fa.csv</St3FuelAirDeckName>
<St3MachDeckName Unit="-">V2527-A5_St3_Mn.csv</St3MachDeckName>
<St3TotalPressureDeckName Unit="-">V2527-A5_St3_P.csv</St3TotalPressureDeckName>
<St3TotalTemperatureDeckName Unit="-">V2527-A5_St3_T.csv</St3TotalTemperatureDeckName>
<St3StaticTemperatureDeckName Unit="-">V2527-A5_St3_Ts.csv</St3StaticTemperatureDeckName>
<St3MassFlowDeckName Unit="-">V2527-A5_St3_W.csv</St3MassFlowDeckName>
<St4FuelAirDeckName Unit="-">V2527-A5_St4_fa.csv</St4FuelAirDeckName>
<St4MachDeckName Unit="-">V2527-A5_St4_Mn.csv</St4MachDeckName>
<St4TotalPressureDeckName Unit="-">V2527-A5_St4_P.csv</St4TotalPressureDeckName>
<St4TotalTemperatureDeckName Unit="-">V2527-A5_St4_T.csv</St4TotalTemperatureDeckName>
<St4StaticTemperatureDeckName Unit="-">V2527-A5_St4_Ts.csv</St4StaticTemperatureDeckName>
<St4MassFlowDeckName Unit="-">V2527-A5_St4_W.csv</St4MassFlowDeckName>
<St5FuelAirDeckName Unit="-">V2527-A5_St5_fa.csv</St5FuelAirDeckName>
<St5MachDeckName Unit="-">V2527-A5_St5_Mn.csv</St5MachDeckName>
<St5TotalPressureDeckName Unit="-">V2527-A5_St5_P.csv</St5TotalPressureDeckName>
<St5TotalTemperatureDeckName Unit="-">V2527-A5_St5_T.csv</St5TotalTemperatureDeckName>
<St5StaticTemperatureDeckName Unit="-">V2527-A5_St5_Ts.csv</St5StaticTemperatureDeckName>
<St5MassFlowDeckName Unit="-">V2527-A5_St5_W.csv</St5MassFlowDeckName>
<St13FuelAirDeckName Unit="-">V2527-A5_St13_fa.csv</St13FuelAirDeckName>
<St13MachDeckName Unit="-">V2527-A5_St13_Mn.csv</St13MachDeckName>
<St13TotalPressureDeckName Unit="-">V2527-A5_St13_P.csv</St13TotalPressureDeckName>
<St13TotalTemperatureDeckName Unit="-">V2527-A5_St13_T.csv</St13TotalTemperatureDeckName>
<St13StaticTemperatureDeckName Unit="-">V2527-A5_St13_Ts.csv</St13StaticTemperatureDeckName>
<St13MassFlowDeckName Unit="-">V2527-A5_St13_W.csv</St13MassFlowDeckName>
<St22FuelAirDeckName Unit="-">V2527-A5_St22_fa.csv</St22FuelAirDeckName>
<St22MachDeckName Unit="-">V2527-A5_St22_Mn.csv</St22MachDeckName>
<St22TotalPressureDeckName Unit="-">V2527-A5_St22_P.csv</St22TotalPressureDeckName>
<St22TotalTemperatureDeckName Unit="-">V2527-A5_St22_T.csv</St22TotalTemperatureDeckName>
<St22StaticTemperatureDeckName Unit="-">V2527-A5_St22_Ts.csv</St22StaticTemperatureDeckName>
<St22MassFlowDeckName Unit="-">V2527-A5_St22_W.csv</St22MassFlowDeckName>
<St25FuelAirDeckName Unit="-">V2527-A5_St25_fa.csv</St25FuelAirDeckName>
<St25MachDeckName Unit="-">V2527-A5_St25_Mn.csv</St25MachDeckName>
<St25TotalPressureDeckName Unit="-">V2527-A5_St25_P.csv</St25TotalPressureDeckName>
<St25TotalTemperatureDeckName Unit="-">V2527-A5_St25_T.csv</St25TotalTemperatureDeckName>
<St25StaticTemperatureDeckName Unit="-">V2527-A5_St25_Ts.csv</St25StaticTemperatureDeckName>
<St25MassFlowDeckName Unit="-">V2527-A5_St25_W.csv</St25MassFlowDeckName>
<St45FuelAirDeckName Unit="-">V2527-A5_St45_fa.csv</St45FuelAirDeckName>
<St45MachDeckName Unit="-">V2527-A5_St45_Mn.csv</St45MachDeckName>
<St45TotalPressureDeckName Unit="-">V2527-A5_St45_P.csv</St45TotalPressureDeckName>
<St45TotalTemperatureDeckName Unit="-">V2527-A5_St45_T.csv</St45TotalTemperatureDeckName>
<St45StaticTemperatureDeckName Unit="-">V2527-A5_St45_Ts.csv</St45StaticTemperatureDeckName>
<St45MassFlowDeckName Unit="-">V2527-A5_St45_W.csv</St45MassFlowDeckName>
<St18MachDeckName Unit="-">V2527-A5_St8_Mn.csv</St18MachDeckName>
<St18TotalTemperatureDeckName Unit="-">V2527-A5_St8_T.csv</St18TotalTemperatureDeckName>
<St18JetVelocityDeckName Unit="-">V2527-A5_St8_V.csv</St18JetVelocityDeckName>
<St18JetDensityDeckName Unit="-">V2527-A5_St8_Rh.csv</St18JetDensityDeckName>
<St18MassFlowDeckName Unit="-">V2527-A5_St8_W.csv</St18MassFlowDeckName>
<St8MachDeckName Unit="-">V2527-A5_St8_Mn.csv</St8MachDeckName>
<St8TotalTemperatureDeckName Unit="-">V2527-A5_St8_T.csv</St8TotalTemperatureDeckName>
<St8JetVelocityDeckName Unit="-">V2527-A5_St8_V.csv</St8JetVelocityDeckName>
<St8JetDensityDeckName Unit="-">V2527-A5_St8_Rh.csv</St8JetDensityDeckName>
<St8MassFlowDeckName Unit="-">V2527-A5_St8_W.csv</St8MassFlowDeckName>
<SNoxDeckName Unit="-">V2527-A5_sNOx.csv</SNoxDeckName>
</Deck>
<EmissionFactors Desc="Data for the emission calculation">
<NOxFactor Desc="Combustion chamber factor NOx Severity Parameter * x = EI_NOx 23 - 32">32</NOxFactor>
<CO2Factor Desc="Stoichiometric factor for the combustion of the fuel" Unit="kg/kgFuel">3.149</CO2Factor>
<H2OFactor Desc="Stoichiometric factor for the combustion of the fuel" Unit="kg/kgFuel">1.2</H2OFactor>
<SO2Factor Desc="Stoichiometric factor for fuel combustion" Unit="kg/kgFuel">0.84e-3</SO2Factor>
<PM10Factor Desc="Factor for the combustion of the fuel" Unit="kg/kgFuel">0.025e-3</PM10Factor>
</EmissionFactors>
<ICAOEngineData>
<LTOFuelFlow Desc=" Fuel Flow according to ICAO Aircraft Engine Emissions Databank for LTO phases">
<Taxi Desc="Fuel Flow for Taxi Phase according to ICAO (Idle, 7% Thrust Setting)" Unit="kg/s">0.128</Taxi>
<Takeoff Desc="EI Index for Takeoff Phase according to ICAO" Unit="kg/s">1,053</Takeoff>
<ClimbOut Desc="EI Index for ClimbOut phase according to ICAO" Unit="kg/s">0.88</ClimbOut>
<Approach Desc="EI Index for Approach Phase according to ICAO" Unit="kg/s">0.319</Approach>
</LTOFuelFlow>
<LTOEmissions Desc="EI Index according to ICAO Aircraft Engine Emissions Database for LTO phases">
<HCFactor Desc=" EI Index according to ICAO Aircraft Engine Emissions Database for LTO phases">
<Taxi Desc="EI Index for Taxi Phase according to ICAO (Idle, 7% Thrust Setting)" Unit="kg/kgFuel">0.105e-3</Taxi>
<Takeoff Desc="EI Index for Takeoff Phase according to ICAO" Unit="kg/kgFuel">0.041e-3</Takeoff>
<ClimbOut Desc="EI Index for ClimbOut Phase according to ICAO" Unit="kg/kgFuel">0.41-3</ClimbOut>
<Approach Desc="EI Index for Approach Phase according to ICAO" Unit="kg/kgFuel">0.061e-3</Approach>
</HCFactor>
<COFactor Desc=" EI Index according to ICAO Aircraft Engine Emissions Database for LTO phases">
<Taxi Desc="EI Index for Taxi Phase according to ICAO (Idle, 7% Thrust Setting)" Unit="kg/kgFuel">12.43e-3</Taxi>
<Takeoff Desc="EI Index for Takeoff Phase according to ICAO" Unit="kg/kgFuel">0.53e-3</Takeoff>
<ClimbOut Desc="EI Index for ClimbOut Phase according to ICAO" Unit="kg/kgFuel">0.62e-3</ClimbOut>
<Approach Desc="EI Index for Approach Phase according to ICAO" Unit="kg/kgFuel">2.44e-3</Approach>
</COFactor>
<NOxFactor Desc=" EI Index according to ICAO Aircraft Engine Emissions Database for LTO phases">
<Taxi Desc="EI Index for Taxi Phase according to ICAO (Idle, 7% Thrust Setting)" Unit="kg/kgFuel">4.7e-3</Taxi>
<Takeoff Desc="EI Index for Takeoff Phase according to ICAO" Unit="kg/kgFuel">26.5e-3</Takeoff>
<ClimbOut Desc="EI Index for ClimbOut Phase according to ICAO" Unit="kg/kgFuel">22.3e-3</ClimbOut>
<Approach Desc="EI Index for Approach Phase according to ICAO" Unit="kg/kgFuel">8.9e-3</Approach>
</NOxFactor>
<SNFactor Desc=" Smoke Number according to ICAO Aircraft Engine Emissions Database for LTO phases">
<Taxi Desc="Smoke Number for Taxi Phase according to ICAO (Idle, 7% Thrust Setting)" Unit="-">2.6</Taxi>
<Takeoff Desc="Smoke Number for Takeoff Phase according to ICAO" Unit="-">5.2</Takeoff>
<ClimbOut Desc="Smoke Number for ClimbOut Phase according to ICAO" Unit="-">7.2</ClimbOut>
<Approach Desc="Smoke Number for Approach Phase according to ICAO" Unit="-">4.2</Approach>
</SNFactor>
</LTOEmissions>
</ICAOEngineData>
</EngineDataFile>
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