1、Energy Learning CenterEnergy Learning Center1/1/20231Energy Learning CenterModel Number DesignationSince April of 1983 all LM2500 engines have been identified by a numbering system consisting of a prefix,engine family designation,type code,and configuration code.Engines manufactured before April 198
2、3 retain the old numbering system and it is not anticipated that they will be updated with the new model numbers.Example:7LM2500-PE-MGW7LM=Prefix2500=Engine family designationPE=Type codeMGW=Configuration codeEnergy Learning Center1/1/20232Energy Learning CenterThe prefix“7LM”is a GE company designa
3、tion for a mechanical,aero derivative(non-aircraft)gas turbine or gas generator.The“7”is the department number for the Marine&Industrial section of the GE Aircraft Engine Company,“L”stands for land and“M”for Marine.The Engine family designation is determined by taking the nominal brake horsepower ra
4、ting and dividing it by 10.The LM2500 had an initial design rating of 25,000 bhp,dividing this by 10 gives an enginefamily designation of 2500.The type code is always comprised of two letters.If the first letter is a“G”it would mean that the engine is a gas generator only,it was not intended to be c
5、oupled to a GE power turbine.The above example indicates that the unit is a gas turbine,by virtue of the“P”.The second letter in the type code indicates the design differences of the unit.Energy Learning Center1/1/20233Energy Learning CenterIn the case of the LM2500+the second letter represents a ma
6、jor design difference of the same product.The letter“K”would indicate a Single Annual Combustor(SAC)engine.The letter”R”would refer to a Dry Low Emission(DLE)engine.For a LM2500+gas generator engine built for a High Speed Power Turbine(HSPT)the type code would be“GV”for a SAC engine and“GY for a DLE
7、 engine.The configuration code identifies major physical characteristics of the engine in terms of utilization.Codes are assigned as follows:HPT Blade CoatingsM=Marinized(CODEP or Platinum Aluminide)N=Non-MarinizedFuel SystemG=Natural GasL=Liquid FuelD=Dual Fuel(both types)Energy Learning Center1/1/
8、20234Energy Learning CenterNOx SuppressionA=Steam NOx with steam power enhancementB=Water NOx with steam power enhancement C=Steam power enhancement onlyD=Dry low EmissionS=Steam NOx onlyW=Water NOx onlyX =NOx Suppressed with water or steam(old convention)Accessories are considered to be bolt on com
9、ponents which could be added or deleted from the engine anytime.Because of this they are not included in the model designation of the engine.Accessories are identified by kit identification numbers given on model lists or purchase documents.The following table illustrates the difference between the
10、various gas turbine model designations and provides a correlation between the old and new numbering systems.1/1/20235Energy Learning Center1/1/20236Energy Learning CenterA Brief HistoryThe LM2500 is an aero-derivative gas turbine.At GE this means that the basic design has proven itself successful in
11、itially as an aircraft engine,with possibly several years and and the experience of in-the-field production engines to draw from.The LM2500 is the most successful aero-derivative in its field.But,it was not the first,or even in the first generation.1959The GE aero-derivative engine makes its debut w
12、hen proven aircraft engine designs are adapted for use in two experimental hydrofoils.A wide variety of applications in marine,industrial,electric utility and other fields soon follow.The following are the pioneering derivatives and their uses.1/1/20237Energy Learning Center LM100Derivation:T58 Heli
13、copter Turboshaft engineApplications:V 169 LocomotiveHS Denison,HydrofoilHS Victoria,HydrofoilUSS President Van BurenHamilton Class USCG Cutter100 ton ore hauling trucksBell SK 5 Air CushionVehicleLM1500Derivation:J79 Airplane Turbojet engineApplications:Portable aircraft catapultUSS Plainview,Hydro
14、foilHS Denison,HydrofoilPG84 Class Gunboat1/1/20238Energy Learning Center1961With the support of the U.S.Navy,a long range program was initiated to solve the specific problems encountered with operating in a marine environment.This marinization program included the laboratory development and testing
15、 of new materials,protective coatings and control devices that would operate properly at sea.Through-out the 1960s this technology was proven at sea and in industry.1965The U.S.Air Force awarded General Electric a contract to develop an engine for their new super sized air transport,the Lockheed C-5
16、 Galaxy.This engine,designated the TF39,proved so successful that a commercial version called the CF6-6 was developed almost immediately.1/1/20239Energy Learning Center1968The basic design of the TF39(now in its second generation)was used in conjunction with the marinization program to create the LM
17、2500.1969The first production LM2500 engine replaced one of two development engines installed aboard the GTS Adm.William W.Callahan,a roll on/roll off(Ro-Ro)cargo ship with a GWT of 24,000 tons,and a cruising speed of 26 knots.1971The first engines were delivered to industrial systems suppliers Dres
18、ser-Rand and Cooper Energy Systems for natural gas compression applications.Dresser-RandColumbia Gulf Transmission Co.,Delhi,Louisiana,USAGreat Lakes Transmission Co.,Wakefield,Michigan,USANova,Airdaire S/S,CanadaNova,Clearwater,CanadaWestcoast Energy,Inc.,McLeod Lake,VBC,Canada 1/1/202310Energy Lea
19、rning CenterCooper Energy SystemsGreat Lakes Transmission Co.,Duluth,Minnesota,USAThe LM2500 has been in production for over 30 years,with a basic design that is now over 35 years old.The engine although originally specified and designed for marine use,has found industrial applications on oil platfo
20、rms,natural gas compression stations,power generation and cogeneration plants,and pipeline pumping stations.Today the engine is available in several different configurations.Either as a gas generator,or gas turbine.Fueled by gaseous or liquid fuels,or both.And may have its power output augmented by
21、the injection of steam that was produced by the heat from its own exhaust gas.This material will be discussed in greater detail later.1/1/202311Energy Learning Center1/1/202312Energy Learning CenterG4 GG tested in Evendale 1/06,GT w/6pack tested 6/06.There will be 24 European Frigates with G4s(1 per
22、 ship)1/1/202313Energy Learning CenterGenealogyDerived from Proven Technology1/1/202314Energy Learning CenterGas Turbine ModulesThe G4 will be easier to exchange with a G3 than to modify a G3 into a G41/1/202315Energy Learning CenterGLOSSARYAABS-Absoluteac-alternating currentACCEL-AccelerationAc-dc-
23、alternating current to direct currentACT-ActuatorAGB-Accessory GearboxALF-Aft Looking forwardamp-amplifier,ampere,or amperageAOA-Angle of AttackAR-As RequiredAssy-AssemblyAve-Avenue-atAlarms-predetermined parametric values at which an automatic warning is executedBButt-Flanges that lie flat against
24、each otherB/E-Base/Enclosurebhp-brake horsepowerBSI-Borescope InspectionBtu-British thermal unitBlade-Rotating airfoil1/1/202316Energy Learning CenterCC-Degrees Centigrade (Celsius)cc-cubic centimeterCCW-CounterclockwiseCDP-Compressor Discharge PressureCFF-Compressor Front FrameChan-ChannelCheck-Ins
25、pectionoffCIP-Compressor Inlet(PT2)Total PressureCIT(T2)-Compressor Inlet Temperature cm-centimeterCMD-CommandCo-CompanyCO2-Carbon DioxideCont-ContinuedCorp-CorporationCRF-Compressor Rear FrameCW-Clockwise1/1/202317Energy Learning CenterDdc-direct currentdistal-viewing lens in linelens with object t
26、o be viewedDOD-Domestic Object DamageDLE-Dry Low EmissionsDVM-Digital Voltmeterdwg-drawingEEEA-Electronic Enclosure AssemblyFF-Degree Fahrenheitfig-figureFIR-Full Indicated Runoutflex-flexibleFMP-Fuel Manifold PressureFOD-Foreign Object Damage.That damage which occurs to gas turbine internal airflow
27、 path surfaces Frame-Establishes the rotational axis(houses bearing sumps)1/1/202318Energy Learning CenterFt-foot(0.3048 meter)or feetFWD-ForwardGgal-gallon(3.785 liters)GE-General Electric CompanyGG-Gas Generatorgpm-gallons per minuteGreen-Repair weld on a weld (previously)fully heat treated part,n
28、ot subjected to heat treatment before welding.(No re-quirement for solutioning,re-solutioning,stress-reliving,or aging of repair weld.)GT-Gas TurbineHHg-MercuryH2O-WaterHPT-High Pressure Turbinehr-hourHSCS-High Speed Coupling ShaftHz-Hertz(cycles per second)HPTN-High Pressure Turbine Nozzle(vanes)1/
29、1/202319Energy Learning CenterIid-inside diameterIGB-inlet GearboxIGV-Inlet Guide Vanein-inchinsp-inspectionI/O-Input/OutputIP-Idle PositionKkg-kilogramkg cm-kilogram centimeterkg m-kilogram meterkg/sq cm-kilogram per square centimeter kPa-kilopascalkw-kilowattLL or l-Literlb-poundLb ft-pound footLb
30、 in-pound inchLH-Left HandLS&CA-Lube Storage and Conditioning AssemblyLSP-Lube Supply Pressure1/1/202320Energy Learning CenterMm-meterma-milliamperemax-maximumMCU-Manual Control UnitMFC-Main Fuel ControlMfg-Manufacturermils-0.001 incmin-minimum or minuteml-millilitermmmillimetermv-millivoltMw,-Mega
31、wattMW or Meg NNGG(N1)-Gas Generator SpeedNo.-NumberNom-NominalNozzle-Turbine StatorsNPT(N2)Power Turbine SpeedOOAT-Outside Air TemperatureOD-Outside DiameterOGV-Outlet Guide VaneOS-OverspeedOT-Overtorque1/1/202321Energy Learning CenterPpara-paragraphPLA-Power Lever AnglePN(s)-Part Number(s)pot-pote
32、ntiometerpph-pounds per hourPPM-Parts per Millionpress-pressurepsi-pounds per square inch pressurepsia-pounds per square inch absolute pressurePsid-pounds per square(P)inch differential pressurepsig-pounds per square inch gage pressurePS3-Compressor Discharge Pressure,StaticPT-Power TurbinePT2-Compr
33、essor Inlet (CIP)Total PressurePT5.4,-Power Turbine Inlet PT4.8 Total Pressure1/1/202322Energy Learning CenterQQAD-Quick Accessory DisconnectQt-quartQty-quantityRRabbet-Overlapping flange or jointRef-ReferenceReq-RequiredRpm-revolutions per minuteReqd-RequiredRTD-Resistance Temperature DetectorRun o
34、n-The torque required to Torque bring a fastener to a sealed positionSSC-Signal ConditionerSCP-Ships Control Panelsec-secondSFC-Specific Fuel Consumption (lbs/bhp-hr)SG-Specific GravitySIG-SignalSN-Serial NumberSST-Signal Shank Turbine BladeStall-A disruption of the normally smooth airflow through t
35、he gas turbine 1/1/202323Energy Learning CenterStd Day-Standard Day 59 deg 29.92”hg,0%hum,Sea levelStator-Casing which Case houses internal located vanesStation-Location of a point on an imaginary line through a turbine engine from front to rear identifying specific parts or sections in Arabic numer
36、alsSys-SystemTTabs-small protrusions (for attachment or alignment)Tach-tachometerTangs-alignment tabs(fit into slots or sockets)TBD-to be determinedT/C-ThermocoupleTemp-TemperatureTGB-Transfer GearboxTM-Torque MotorTMF-Turbine Mid FrameTNH-High Speed Turbine Speed1/1/202324Energy Learning CenterTNL-
37、Low Speed Turbine SpeedTST-Twin Shank Turbine BladeT2-Compressor Inlet(CIT)TemperatureT5.4,4.8-Power Turbine Inlet T54,48 TemperatureUUS-United StatesUSA-United States of AmericaVV-VoltVA-VoltampsVac-volts,alternating currentVane-stationary airfoilsVdc-volts,direct currentVSV-Variable Stator VaneWW-
38、WattWP-Work PackageXX-ByX DCR-Transducer1/1/202325Energy Learning Center1/1/202326Energy Learning CenterAll references to location or position on the LM2500 are based on the assumption that the individual is standing behind the engine and looking forward.This is true in all cases unless stated other
39、wise.Unless otherwise stated,all views in this training manual are from the left side of the engine,with the intake on the observers left and the exhaust on the right.All GE engines rotate CW aft looking forward,(ALF)Generators are viewed forward looking aft.(FLA)1/1/202327Energy Learning Center1/1/
40、202328Energy Learning CenterRubber GasketKeep Clean Room Clean!P=P0 vs.P11”H20=Alarm2”H20=S/DInlet has minimum of 200 lbs/sec airflow1/1/202329Energy Learning CenterInlet ComponentsThe inlet components direct air into the inlet of the gas generator to provide for smooth,non-turbulent airflow into th
41、e compressor.These components consist of:1.Inlet duct2.Centerbody.1/1/202330Energy Learning CenterInlet DuctThe inlet duct is constructed of aluminum(AMS4026)and shaped like a bellmouth.The inlet duct is painted white,and must be maintained in the painted condition.CenterbodyThe centerbody is a flow
42、 divider bolted to the front of the gas generator.The centerbody is sometimes known as the bulletnose,and is made of a graphite reinforced fiberglass composite.unpainted1/1/202331Energy Learning CenterAirflowsIntroduction Primary and secondary airflows are supplied to the gas turbine through the inl
43、et.Primary air is supplied to the enclosure inlet plenum area,and flows through the gas turbine.Secondary air is supplied to the enclosure gas turbine environment,and provides a cooling flow around the gas turbine.Most primary air within the engine is used to support the gas turbine power cycle(inle
44、t,compression,ignition,expansion and exhaust).This airflow is referred to as the“main gas flow”,and its flow path is the Main Gas Path.Some of the primary air is extracted from the main gas path at the 9th and 13th stages of compression,and from the compressor discharge chamber to supply various coo
45、ling and pressurization functions essential to the operation of the engine.This reduces the total amount of air available to the power cycle,and for this reason,these are referred to as“parasitic airflows”.1/1/202332Energy Learning CenterCustomer bleed air requirements for off-engine functions,are a
46、lso supplied by parasitic airflow from the compressor discharge chamber.Main Gas PathBetween the gas turbine inlet and the compressor discharge,the airflow duct formed by the inlet components,CFF,and compressor is continuously convergent.To produce airflow between these two points,work is done on th
47、e air by the rotating compressor blades.From the compressor discharge chamber;through the combustor,HPT,TMF,LPT,TRF,and gas turbine exhaust the airflow duct is almost continuously diffusive.Airflow between these two points is produced by the internal energy stored in the air during its transition th
48、rough the compressor,and by energy added to the air by combustion.During its transition through the compressor,ambient pressure present at the gas turbine inlet is increased by an 23:1 ratio.1/1/202333Energy Learning CenterAt the compressor discharge,the combustor diffuser cowl forms an airflow divi
49、der that routes approximately 20%of the high pressure air into the combustor dome area.The remaining 80%continues to diffuse into the compressor discharge chamber around the combustor.As the 20%flow supplied to the combustor dome area passes through the swirler cups,it is mixed with fuel,and ignites
50、 upon reaching the combustion chamber.The resulting combustion reaction releases tremendous amounts of heat,and causes violent and rapid expansion of the ignited gases.Large masses of high pressure dilution air entering the combustion chamber through holes in the inner and outer liners center the ig
