LM2500+ course(燃气透平)

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1、Energy Learning CenterGE Proprietary Information8/18/20211Energy Learning CenterEnergy Learning CenterGE Proprietary Information8/18/20212Model Number DesignationSince April of 1983 all LM2500 engines have been identified by a numbering system consisting of a prefix, engine family designation, type

2、code, and configuration code. Engines manufactured before April 1983 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

3、 CenterEnergy Learning CenterGE Proprietary Information8/18/20213The prefix “7LM” is a GE company designation 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” sta

4、nds for land and “M” for Marine.The Engine family designation is determined by taking the nominal brake horsepower rating 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 t

5、wo 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 coupled 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 differenc

6、es of the unit.Energy Learning CenterEnergy Learning CenterGE Proprietary Information8/18/20214In the case of the LM2500+ the second letter represents a major design difference of the same product. The letter “K” would indicate a Single Annual Combustor (SAC) engine. The letter ”R” would refer to a

7、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 engine.The configuration code identifies major physical characteristics of the engine in terms of utilization. Codes are assign

8、ed as follows:HPT Blade CoatingsM = Marinized(CODEP or Platinum Aluminide)N = Non-MarinizedFuel SystemG = Natural GasL = Liquid FuelD = Dual Fuel (both types)Energy Learning CenterEnergy Learning CenterGE Proprietary Information8/18/20215NOx SuppressionA = Steam NOx with steam power enhancementB = W

9、ater 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 components which could be added or deleted from the engine anytime. Because of

10、 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 various gas turbine model designations and provides a correlation between

11、 the old and new numbering systems.Energy Learning CenterGE Proprietary Information8/18/20216Energy Learning CenterGE Proprietary Information8/18/20217A Brief HistoryThe LM2500 is an aero-derivative gas turbine. At GE this means that the basic design has proven itself successful initially as an airc

12、raft 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 when proven a

13、ircraft 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.Energy Learning CenterGE Proprietary Information8/18/20218 LM100

14、Derivation:T58 Helicopter 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 catapu

15、ltUSS Plainview, HydrofoilHS Denison, HydrofoilPG84 Class GunboatEnergy Learning CenterGE Proprietary Information8/18/202191961With 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 pr

16、ogram included the laboratory development and testing 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

17、for their new super sized air transport, the Lockheed C-5 Galaxy. This engine, designated the TF39, proved so successful that a commercial version called the CF6-6 was developed almost immediately.Energy Learning CenterGE Proprietary Information8/18/2021101968The basic design of the TF39 (now in its

18、 second generation) was used in conjunction with the marinization program to create the LM2500.1969The 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 crui

19、sing speed of 26 knots.1971The first engines were delivered to industrial systems suppliers Dresser-Rand and Cooper Energy Systems for natural gas compression applications.Dresser-RandColumbia Gulf Transmission Co., Delhi, Louisiana, USAGreat Lakes Transmission Co.,Wakefield, Michigan, USANova, Aird

20、aire S/S, CanadaNova, Clearwater, CanadaWestcoast Energy, Inc., McLeod Lake, VBC, Canada Energy Learning CenterGE Proprietary Information8/18/202111Cooper Energy SystemsGreat Lakes Transmission Co., Duluth, Minnesota, USAThe LM2500 has been in production for over 30 years, with a basic design that i

21、s now over 35 years old. The engine although originally specified and designed for marine use, has found industrial applications on oil platforms, natural gas compression stations, power generation and cogeneration plants, and pipeline pumping stations.Today the engine is available in several differ

22、ent 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 the injection of steam that was produced by the heat from its own exhaust gas. This material will be discussed in greater detail later.Energy Learning

23、 CenterGE Proprietary Information8/18/202112Energy Learning CenterGE Proprietary Information8/18/202113G4 GG tested in Evendale 1/06, GT w/6pack tested 6/06. There will be 24 European Frigates with G4s (1 per ship)Energy Learning CenterGE Proprietary Information8/18/202114GenealogyDerived from Prove

24、n TechnologyEnergy Learning CenterGE Proprietary Information8/18/202115Gas Turbine ModulesThe G4 will be easier to exchange with a G3 than to modify a G3 into a G4Energy Learning CenterGE Proprietary Information8/18/202116GLOSSARYAABS- Absoluteac- alternating currentACCEL - AccelerationAc-dc- altern

25、ating 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

26、against each otherB/E- Base/Enclosurebhp- brake horsepowerBSI- Borescope InspectionBtu- British thermal unitBlade- Rotating airfoilEnergy Learning CenterGE Proprietary Information8/18/202117CC- Degrees Centigrade (Celsius)cc- cubic centimeterCCW- CounterclockwiseCDP- Compressor Discharge PressureCFF

27、- Compressor Front FrameChan- ChannelCheck - InspectionoffCIP- Compressor Inlet (PT2) Total PressureCIT (T2) - Compressor Inlet Temperature cm- centimeterCMD- CommandCo- CompanyCO2- Carbon DioxideCont- ContinuedCorp- CorporationCRF- Compressor Rear FrameCW- ClockwiseEnergy Learning CenterGE Propriet

28、ary Information8/18/202118Ddc- direct currentdistal - viewing lens in linelens with object to be viewedDOD- Domestic Object DamageDLE- Dry Low EmissionsDVM- Digital Voltmeterdwg- drawingEEEA- Electronic Enclosure AssemblyFF- Degree Fahrenheitfig- figureFIR- Full Indicated Runoutflex- flexibleFMP- Fu

29、el Manifold PressureFOD- Foreign Object Damage. That damage which occurs to gas turbine internal airflow path surfaces Frame - Establishes the rotational axis (houses bearing sumps)Energy Learning CenterGE Proprietary Information8/18/202119Ft- foot (0.3048 meter) or feetFWD- ForwardGgal- gallon (3.7

30、85 liters)GE- General Electric CompanyGG- Gas Generatorgpm- gallons per minuteGreen - Repair weld on a weld (previously) fully heat treated part, not subjected to heat treatment before welding. (No re- quirement for solutioning, re-solutioning, stress- reliving, or aging of repair weld.)GT- Gas Turb

31、ineHHg- MercuryH2O- WaterHPT- High Pressure Turbinehr- hourHSCS- High Speed Coupling ShaftHz- Hertz (cycles per second)HPTN- High Pressure Turbine Nozzle (vanes)Energy Learning CenterGE Proprietary Information8/18/202120Iid- inside diameterIGB- inlet GearboxIGV- Inlet Guide Vanein- inchinsp- inspect

32、ionI/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 in- pound inchLH- Left HandLS & CA- Lube Storage and Conditioning AssemblyLSP- Lube Supply P

33、ressureEnergy Learning CenterGE Proprietary Information8/18/202121Mm- meterma- milliamperemax- maximumMCU- Manual Control UnitMFC- Main Fuel ControlMfg- Manufacturermils- 0.001 incmin- minimum or minuteml- millilitermmmillimetermv- millivoltMw,- Mega wattMW or Meg NNGG (N1) - Gas Generator SpeedNo.-

34、 NumberNom- NominalNozzle - Turbine StatorsNPT (N2) Power Turbine SpeedOOAT- Outside Air TemperatureOD- Outside DiameterOGV- Outlet Guide VaneOS- OverspeedOT- OvertorqueEnergy Learning CenterGE Proprietary Information8/18/202122Ppara- paragraphPLA- Power Lever AnglePN(s)- Part Number(s)pot- potentio

35、meterpph- 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 TurbineP

36、T2-Compressor Inlet (CIP) Total PressurePT5.4, - Power Turbine Inlet PT4.8 Total PressureEnergy Learning CenterGE Proprietary Information8/18/202123QQAD- Quick Accessory DisconnectQt- quartQty- quantityRRabbet - Overlapping flange or jointRef- ReferenceReq- RequiredRpm- revolutions per minuteReqd- R

37、equiredRTD- Resistance Temperature DetectorRun on - 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 BladeS

38、tall- A disruption of the normally smooth airflow through the gas turbine Energy Learning CenterGE Proprietary Information8/18/202124Std 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

39、 a turbine engine from front to rear identifying specific parts or sections in Arabic numeralsSys- SystemTTabs- small protrusions (for attachment or alignment)Tach- tachometerTangs- alignment tabs (fit into slots or sockets)TBD- to be determinedT/C- ThermocoupleTemp- TemperatureTGB- Transfer Gearbox

40、TM- Torque MotorTMF- Turbine Mid FrameTNH- High Speed Turbine SpeedEnergy Learning CenterGE Proprietary Information8/18/202125TNL- Low Speed Turbine SpeedTST- Twin Shank Turbine BladeT2 - Compressor Inlet (CIT) TemperatureT5.4,4.8- Power Turbine Inlet T54,48 TemperatureUUS- United StatesUSA- United

41、States of AmericaVV- VoltVA- VoltampsVac-volts, alternating currentVane- stationary airfoilsVdc- volts, direct currentVSV- Variable Stator VaneWW- WattWP- Work PackageXX- ByX DCR- TransducerEnergy Learning CenterGE Proprietary Information8/18/202126Energy Learning CenterGE Proprietary Information8/1

42、8/202127All 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 otherwise.Unless otherwise stated, all views in this training manual are from the left side of the e

43、ngine, 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)Energy Learning CenterGE Proprietary Information8/18/202128Energy Learning CenterGE Proprietary Information8/18/202129Rubber G

44、asketKeep Clean Room Clean!P=P0 vs. P11”H20=Alarm2”H20=S/DInlet has minimum of 200 lbs/sec airflowEnergy Learning CenterGE Proprietary Information8/18/202130Inlet ComponentsThe inlet components direct air into the inlet of the gas generator to provide for smooth, non-turbulent airflow into the compr

45、essor.These components consist of:1. Inlet duct2. Centerbody. Energy Learning CenterGE Proprietary Information8/18/202131Inlet 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.Centerb

46、odyThe centerbody is a flow 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.unpaintedEnergy Learning CenterGE Proprietary Information8/18/202132AirflowsIntroduction Primary and secondary

47、airflows are supplied to the gas turbine through the inlet. 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 t

48、he engine is used to support the gas turbine power cycle (inlet, 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 compre

49、ssion, and from the compressor discharge chamber to supply various cooling 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”.Energy Learning Cent

50、erGE Proprietary Information8/18/202133Customer bleed air requirements for off-engine functions, are also 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,

51、 and compressor is continuously convergent.To produce airflow between these two points, work is done on the 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 diffusi

52、ve. Airflow between these two points is produced by the internal energy stored in the air during its transition through 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:

53、1 ratio. Energy Learning CenterGE Proprietary Information8/18/202134At the compressor discharge, the combustor diffuser cowl forms an airflow divider that routes approximately 20% of the high pressure air into the combustor dome area. The remaining 80% continues to diffuse into the compressor discha

54、rge 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 upon reaching the combustion chamber. The resulting combustion reaction releases tremendous amounts of heat, and causes violent and rapid expansion

55、 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 ignition flame within the chamber, and create an instant cooling effect as they are expanded by the super heated combustion gases.Energy Learning C

56、enterGE Proprietary Information8/18/202135 Small film cooling holes drilled in the leading edge of the inner and outer liner rolled ring segments provide a thin layer of cool compressor discharge air between liners and the hot combustion gases (SAC only). The constant inflow of high pressure air thr

57、ough ignition, dilution, and film cooling channels forces the hot combustion gases to expand aft-ward through the turbines. Most of the energy contained in the expanding combustion gases is dissipated against the HPT rotor blades to drive the compressor. The expanding gases discharged from the HPT s

58、till contain considerable amounts of energy, and continue to expand through the LPT. After passing through the LPT all usable energy is consumed, and the depleted gases are expelled from the engine through the exhaust components.Energy Learning CenterGE Proprietary Information8/18/202136MAIN GAS PAT

59、HEnergy Learning CenterGE Proprietary Information8/18/202137Aerodynamic Stations Various instrumentation points along the main gas path are identified with “aerodynamic station numbers” for monitoring temperature and pressure characteristics of the main gas flow. The system used to identify these in

60、strumentation points is mainly intended for use by various engineering functions in the design phase and production testing of the engine. However, some of terminology has spread into the field. Actual aerodynamic station numbers range from 0 to 9, but only military aircraft applications require thi

61、s many numbers to describe the main gas path.LM2500+ applications require only three numbers.Station 2 (Compressor inlet) Station 3 (Compressor Discharge)Station 5.4 (4.8) (Power Turbine Inlet)Combining the monitored parameters with the station numbers produces theEnergy Learning CenterGE Proprietar

62、y Information8/18/202138Following terminology.T2 (Compressor Inlet Temperature or CIT) Pt2 (Compressor Inlet Total Pressure or CDP)Ps3 (Compressor Discharge Static Pressure of CDP)T3 Compressor Discharge TemperatureT5.4 (4.8) (Power Turbine Inlet Temperature)Pt5.4 (4.8) (Power Turbine Inlet Total Pr

63、essure)Energy Learning CenterGE Proprietary Information8/18/202139Component HeritageEnergy Learning CenterGE Proprietary Information8/18/202140ComparisonMaximizes Design Commonality with Technology Advancements=13.8” longerG4 has approx 10% more power than G3 Energy Learning CenterGE Proprietary Inf

64、ormation8/18/202141FramesThe LM2500 has 4 frames:1. Compressor Front Frame (CFF)2. Compressor Rear Frame (CRF)3. Turbine Mid Frame (TMF)4. Turbine Rear Frame (TRF) Frames are rigid, non-moving, engine structural elements. The primary purpose of a frame is to provide support. Energy Learning CenterGE

65、 Proprietary Information8/18/202142 Each of these frames is an assembly consisting of a central hub connected to an outer casing through the use of hollow struts. These struts provide access for cooling, lubrication, and pressurization. Compressor Front Frame The CFF supports the forward stub shaft

66、of the compressor rotor through the use of a roller bearing, which is situated in the hub of the frame, the walls of which form the “A” bearing sump. The CFF also supports the forward portion of the compressor stator, inlet duct, centerbody, and the front of the gas turbine. The outer portion of the frame is supported by 5 equally spaced struts that radiate axially from the hub. The struts are hollow to provide services to and from the engine, and are shaped like airfoils to provide a turbulent