Bombardier Global Express - Power Plant INTRODUCTION The Global airplane is powered by two BMW-Rolls Royce BR710A2-20 engines, each mounted on a pylon on either side of the rear fuselage. The engine is an axial flow, dual shaft turbofan, with a 4.0:1 bypass ratio, with a rated static thrust of 14,750 pounds at sea level to ISA + 20. The BR710A2-20 engine contains two main rotating assemblies (spools), a single- stage low pressure (LP) fan-driven by a two-stage turbine, and a ten-stage high pressure (HP) compressor, driven by a two-stage turbine. The HP spool provides an external drive for the accessories mounted on the accessory gearbox. The engine is made up of eight modules as follows: • Fan assembly • Fan case • Intermediate case • HP Compressor • HP Turbine and combustion chamber • LP Turbine and shaft • Accessory Gearbox (AGB) • Bypass duct Each engine provides bleed air extraction, from either the 5th stage or the 8th stage of compression, for Air Conditioning/Pressurization, Cowl and Wing anti-icing and engine starts. The engine oil system consists of a lubrication system, a heat management system and an oil replenishment system. The fuel system consists of a low-pressure system and a high-pressure system. Fuel is supplied from the airplane fuel system via AC and/or DC fuel pumps and engine- driven fuel pumps. Thrust management is controlled throughout all phases of operation by the Full Authority Digital Electronic Control (FADEC). An Electronic Engine Controller (EEC) is the major part of the FADEC, interfacing between the airplane and the engine. Primary engine indications are displayed on EICAS and secondary indications on the STATUS page. Autothrottle is controlled by the autothrottle computer, located in the IAC, and sends signals to FADEC via the throttle, for thrust commands. Starting is initiated through the FADEC, to provide normal ground/air starts, alternate ground/air starts, wet and dry motoring and continuous ignition. Starting can also be performed manually. Page 1 Bombardier Global Express - Power Plant The thrust reverser system is operated by the airplane hydraulic system and is controlled by the EEC. Vibration monitoring system provides signals indicating N1 (Fan) and N2 (HP compressor) vibration levels on each engine. Fire detection is provided by dual element sensor assemblies connected in series to provide two independent sensing loops. Two fire bottles are located at the rear of the airplane. DESCRIPTION ENGINE ASSEMBLY AND AIRFLOW The BR710A2-20 engine contains two main rotating assemblies (spools), a single- stage low-pressure (LP), fan-driven by a two-stage turbine, and a ten-stage high pressure (HP) compressor, driven by a two-stage turbine. The HP spool provides an external drive for the accessories mounted on the accessory gearbox. LPCompressor 8 1 (fan) _0 7 1 _ X G Accessory LPTurbine Gearbox HPCompressor HPTurbine All air entering the engine air intake passes through the LP compressor and is divided into two main flows, the bypass and core airflows. The core airflow passes through the HP compressor to the annular combustion chamber, which supplies the engine with its fuel requirements. The core airflow then flows through two stages of HP turbines and two stages of LP turbines into the forced mixer to mix with bypass air. The bypass air passes through the fan outlet guide vanes along the bypass duct to meet with the core airflow. The combined airstream is exhausted to atmosphere. Page 2 Bombardier Global Express - Power Plant Annular HPTurbine LPCompressor HPCompressor Combustion Forced Chamber LPTurbine Mixer COLDSTREAM AIR HOTSTREAM INLET COLDSTREAM 9 1 0 _ 7 1 _ X G Exhaust Exhaust Nozzle Intake Bypass Accessory Cone Cowl Duct Gearbox ENGINE MODULES The engine is made up of eight modules as follows: Intermediate Fan-Case Case HPTurbineand HPCompressor Combustor 0 2 0 _ 7 1 _ X G LPTurbine andShaft BypassDuct FanAssembly AccessoryGearbox Page 3 Bombardier Global Express - Power Plant • Fan assembly - Compresses the air entering the engine inlet cowl and feeds a percentage of it to the core, while the bypass air provides a major portion of the engine’s thrust • Fan case - Provides containment in the event of fan blade failure and noise attenuation • Intermediate case - Provides a fixed structure for rotating systems and houses the drive for the AGB • HP Compressor - Provides a pressurized airflow to the combustion chamber for combustion and cooling purposes and pressurized air for ECS and Wing and Cowl anti-icing • HP Turbine and combustion chamber - The two stage HP turbine drives the HP compressor. The combustion chamber mixes fuel and air, for an optimum mixture, for maximum efficiency • LP Turbine and shaft - Provides the LP turbine shaft which drives a two stage LP turbine that drives the LP compressor (fan) • Accessory Gearbox (AGB) - Transmits the motoring force from the engine to the accessories mounted on the AGB. The AGB also transmits motoring from the air starter to the engine during start/crank procedures. The AGB also houses the integral oil tank • Bypass duct - Provides a streamlined path for the fan bypass airflow and supports the thrust reverser unit FULL AUTHORITY DIGITAL ELECTRONIC CONTROL (FADEC) Thrust management is controlled throughout all phases of operation by the Full Authority Digital Electronic Control (FADEC). An Electronic Engine Controller (EEC) is the major part of the FADEC, interfacing between the airplane systems and the engine. The EEC provides the following control functions: • Fuel metering through the FMU for: • Automatic start and relight • Idle speed control • Acceleration and deceleration • Engine power setting • Limit protection for N1 and N2 speeds • Limit protection for temperature • Independent overspeed protection of N1 and N2 Page 4 Bombardier Global Express - Power Plant • Compressor airflow control via the and HP compressor bleed valves, to ensure: • Surge free acceleration and deceleration • Surge recovery • Stable operation • Control of oil and fuel temperature • Control of the igniters and start air valve • Partial control of the thrust reverser system functions • Control of the engine power in reverse thrust • Control of system electrical supply, either 28 or dedicated generator output to the EEC and through to the FADEC MTAHXRUST DEDICATEDGEN IDLEREV THROTTLE MAXREVLENGRUNR FMU MODULE HPS&BLEEDVALVES 28VDC STATORVANESYSTEM S DAU1 M TE DAU2 EEC S Y DAU3 FUELCOOLEDOILCOOLER S S IAC1 C STARTERAIRVALVE ONI IAC2 IGNITIONSYSTEM AVI IAC3 R THRUSTREVERSER 21 E _0 H 7 OT ADC1 ENGINEINPUTS X_1 G ADC2 ADC3 ELECTRONIC ENGINE CONTROLLER (EEC) The EEC is the controlling unit of the FADEC system and is located on the top of the engine. EngineElectronic Controller(EEC) 2 2 0 _ 7 1 _ X G Page 5 Bombardier Global Express - Power Plant The EEC is an electronic control unit containing two channels A and B. Each channel is comprised of a Central Processor Unit (CPU), Power Supply Unit (PSU) and an Independent Overspeed Protection (IOP) unit. The PSU controls the power supplies to the FADEC system and to the EECs, CPU and IOP. The PSU controls the switch over from the airplane 28 VDC supply to power supplied by the Dedicated Generator (DG). Normally the FADEC is powered by the DG when the engine is operating. If DG power fails, the PSU will revert to the airplane power supply, to continue operation of the engine. The DG is mounted on the front of the accessory gearbox. DedicatedGenerator AirStarter HydraulicPump 3 2 0 _ 7 1 _ X G OilTank FRONTVIEW VariableFrequency GeneratorNo.1 DryDrains Outlet The CPU receives and processes all input signals and calculates the output signals. Control of the engine automatically alternates between channel A and channel B. If channel A is in control, channel B is the backup for the duration of that flight. On the next engine start channel B is in control and channel A is backup. The change command is triggered by the engine shutdown on the ground. An interlock prevents both channels from being in control at the same time. Each CPU’s operation is monitored by a “watchdog timer”. If the watchdog timer senses a CPU malfunction within a set timescale, then it will momentarily pass control to the other channel, while the faulty CPU resets. After four CPU resets the watchdog will impose a freeze and control will pass to the other channel for the remainder of the flight. Page 6 Bombardier Global Express - Power Plant AIRFRAMESIGNALS AIRFRAMESIGNALS ENGINE ENGINE OUTPUTS INPUTS INPUTS INPUTS INPUTS OUTPUTS G CPU CPU W HDOER PVRAOLCIDEASTSIOINNG CROSS PVRAOLCIDEASTSIOINNG TIMATC TCTIM OUTPUTSIGNAL LINKS OUTPUTSIGNAL ERHD WA CALCULATION CALCULATION OG OUTPUTDRIVER OUTPUTDRIVER 4 2 0 _ LANECHANGERELAY LANECHANGERELAY 17 _ X G SYSTEMCONTROLLER SYSTEM POSITION SYSTEMFEEDBACKTOCHANNELA&B ACTUATOR ACTUATOR OFEECAS"ENGINEINPUTS" ENGINEPARAMETERFEEDBACKTOBOTH ENGINE CHANNELSOFTHEEEC(ASABOVE)AND DIRECTTOAIRFRAMESYSTEMS,IE:VIBRATION The IOP will automatically shut off fuel in the event of N1 or N2 reaching the overspeed trigger values. When either N1 or N2 speed signal has exceeded a preset value, one of the IOPs will “vote” to close the HPSOV, located in the FMU and indicate this to the other channel via the cross link. The engine will not shut down unless both IOPs detect an overspeed. The overspeed function is checked during normal engine shutdown by resetting the overspeed trip points to a subidle value. When the speed drops below the reset values, the IOP overspeed detection trip points logic resets. Page 7 Bombardier Global Express - Power Plant ENGINE INDICATIONS Primary engine parameters are displayed on EICAS. Secondary engine parameters are displayed on the STAT page. EnginePressureRatio(EPR) L ENG FLAMEOUT Usedtodisplaythrustandistheprimary FUEL LO QTY thrustsettingindicator. 1.65 1.65 FUEL IMBALANCE 1.54 1.54 YD OFF N1(FAN) <– FUEL XFER ON UsedtodisplaytheLPcompressor(fan) CERPZR GPLADRKM/AENMUEARLBARRAMKE ON speed,andasSecondarythrustsetting indicatorandismeasuredin%. 98.5 98.5 73.3 73.3 InterturbineTemperature(ITT) Usedtodisplayengineoperatingtemperatures T/O N1 andisdisplayedin°C. SYNC GEAR 789 789 DN DN DN N2(HPcompressor) UsedtodisplayHPcompressorspeedand OUT ismeasuredin%. I ITT I G SYNC G N N START START 3O FuelFlow(FF) 93.4 N2 93.4 Usedtodisplaytheamountoffuelbeing 575O FF (PPH) 575O NU –TRIMS– used,inpoundsperhour(pph)orkilograms 115 OIL TEMP 115 AIL perhour(kgph). 81 OIL PRESS 81 7.2 OilTemperature(OILTEMP) Usedtodisplaytheoiltemperatureandis TOTAL FUEL (LBS) 4155O LWD RWD displayedin°C. 146OO 1OOOO 146OO ND 235O STAB NL RUDDER NR OilPressure(OILPRESS) Usedtodisplaytheoilpressureandis displayedinpsi. AftTank NotshownonGlobal5000 CKPT(°C) AFT CABALT 1300 CABIN(°C) CABIN(°C) P 0.00 20 22 22 19 20 20 CABRATE OXYGEN 90% 1 2 OUTFLOWVALVES 1 2 0 0 OPEN OPEN 13% 13% 1 2 EngineOilQuantity(ENG) OILQTY(QTS) Usedtodisplaytheoilquantityinthe 12.3 ENG 12.3 engineandismeasuredinquarts. APU 5.0 RES 5.1 APU RPM100 EGT 650 BRAKETEMP OilReservoirQuantity(RES) 04 05 04 04 Usedtodisplaytheamountofoilinthe replenishmenttankandismeasuredin 5 2 quarts. _0 7 1 _ X G Page 8 Bombardier Global Express - Power Plant INTERTURBINE TEMPERATURE (ITT) ITT measures engine operating temperatures and is used by the EEC during engine start and relight. Seven dual element (dissimilar metals) thermocouples, located in the LP turbine entry area, are connected in parallel and provide an average ITT to each lane of the EEC. A data entry plug ensures that all engines have the same ITT redline. The redline will change value depending on the start configuration, ground or inflight. 789 789 ITT DAU’s AIRFRAME ENGINE DATA CHANNEL CHANNEL ENTRY A B PLUG EEC 6 2 0 _ 7 1 _ X G Page 9 Bombardier Global Express - Power Plant ITT INDICATION ITTSpeedRedline DisplaysthemaximumITT allowedandissetat900°C,for engineoperation(exceptengine 9O6 start).ShouldtheITTlimitsbe exceeded,thesweeparmand ITTreadoutwillberedandwill flash. 789 789 ITTReadout Displaysthecurrent ITTreadout. ITT ITTSweepArm Displaysthecurrent ITTreadout. 25 ITTRedline(groundstart) Theredlineisresetforgroundstart to700°C.Itwillrevertbackto900°C oncetheengineisatidle. ITT ITTRedline(inflightstart) Theredlineisresetforinflightstart 125 to850°C.Itwillrevertbackto 900°Concetheengineisatidle. ITT 7 2 0 _ 7 1 _ X G Page 10