涡轮增压器设计培训资料

The Application of Turbomachinery to Reciprocating Engines涡轮机械在往复式发动机上的应用Chapter 6第第6章章Matching 4-Stroke Diesels与四冲程柴油机匹配Volumetric Efficiency容积效率容积效率The volumetric efficiency is defined as; 充气效率的定义如下充气效率的定义如下where:D= Displacement per cycle length3/cycle 一个工作循环的排量一个工作循环的排量长度长度3/循环次数循环次数N= Engine speed rev/time 发动机转速发动机转速转转/分分NRPC = Number of revolutions per cycle 2 for a four-stroke engine每循环活塞往复运动次数每循环活塞往复运动次数二或四冲程二或四冲程where: vol= Volumetric Efficiency dimensionless容积效率容积效率无量纲无量纲min= Net mass flow rate into engine cylinders mass/time进入气缸的净质量流量进入气缸的净质量流量质量质量/时间时间 ref= Reference density mass/length3参考密度参考密度质量质量/长度长度3VDR= Volumetric displacement rate length3/time单位时间体积排量单位时间体积排量长度长度3/时间时间The volumetric displacement rate is calculated by;单位时间体积排量按下面的公式计算单位时间体积排量按下面的公式计算.volinref = actual air mass flowideal air mass flow = m*VDR VDR = D*NNRPC Volumetric Efficiency (continued)容积效率容积效率The reference density is calculated from the ideal gas law (P*v = m*R*T);参考密度按照理想气体状态方程计算参考密度按照理想气体状态方程计算where:R= Gas constant for air (length*force)/(mass*temperature)空气气体常数空气气体常数Pref= Reference pressure mass/length2 (Ref conditions in the inlet manifold) 参考压力参考压力（在进气管状态下）（在进气管状态下）Tref= Reference temperature temperature 参考温度参考温度Substituting these relationships into the definition of volumetric efficiency gives;把这些参数带入上述充气效率公式中则有把这些参数带入上述充气效率公式中则有:or, solving for min gives:或者，求解或者，求解min.=refrefinvolPNDTmNRPCR=refrefvolinTNRPCRPNDm=refrefrefTRPBreathing Lines (Four-Stroke Diesel Engine Only)Given the equation derived from the definition of Volumetric Efficiency;由容积效率定义得出方程式由容积效率定义得出方程式:Make the following assumptions/approximations;做下面的假设做下面的假设/近似值近似值 vol= a constant (somewhere between .88 and .95) 常量常量(0.88到到0.95之间之间)Pref= Pamb * (Compressor Pressure Ratio) = Pamb*PRc压气机压缩比压气机压缩比Tref= a constant (for an aftercooled engine)常量常量(对中冷发动机对中冷发动机)D= a constant (for a given engine)常量常量(对指定的发动机对指定的发动机)Substituting these relationships into the equation above gives;把这些参数代如上方程式有把这些参数代如上方程式有:Converting this to the Mass Flow Parameter used in the compressor map gives:=refrefvolinTNRPCRPNDm.cinPRTNConstantMFP=()ambinincambinininPPTPRPNConstantPTmMFP=.cambinPRPNConstantm=吸气线吸气线(四冲程发动机才有四冲程发动机才有)转换成压气机特性曲线上的质量流量参数转换成压气机特性曲线上的质量流量参数MFPBreathing lines in compressor map coordinates0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1900 rpm1300 rpm压气机特性曲线坐标中的吸气线压气机特性曲线坐标中的吸气线流量参数流量参数压压缩缩比比Breathing Lines on a Compressor Map0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1900 rpm1300 rpm压气机特性曲线图上的吸气线压气机特性曲线图上的吸气线压压缩缩比比流量参数流量参数Compressor map too small压气机特性曲线图太小压气机特性曲线图太小0255075100125150175200 Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1900 rpm1300 rpm流量参数流量参数压压缩缩比比Compressor map too large压气机特性曲线图太大压气机特性曲线图太大0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1900 rpm1300 rpm压压缩缩比比流量参数流量参数Compressor map too narrow 压气机性能曲线图太窄压气机性能曲线图太窄0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio2100 rpm1100 rpm流量参数流量参数压压缩缩比比压压缩缩比比压气机性能曲线上的工作点压气机性能曲线上的工作点工作点的估算工作点的估算功率功率燃油消耗率燃油消耗率空燃比空燃比燃油流量燃油流量(速速)空气流量空气流量(速速)质量流量参数质量流量参数知道了知道了MFP，和已有的吸气和已有的吸气线，就可得出线，就可得出压缩比压缩比PRc流量参数流量参数Operating Point on a Compressor Map0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1900 rpmEstimation of Operating Point Power = x kW BSFC = y g/kWh Air/Fuel ratio = z Fuel flow rate = x * y Air flow rate = Fuel * z MFP = Fuel*z * Hence PRc from MFP and breathing linesqrt(Tin)/PinEffect of Turbine Selection on Compressor Operation0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1900 rpmLarger Casing Smaller Casing涡壳的选择对压气机特性曲线上工作点的影响涡壳的选择对压气机特性曲线上工作点的影响流量参数流量参数压压缩缩比比大的涡壳大的涡壳小的涡壳小的涡壳02550751001.01.41.82.22.63.03.43.8Flow Parameter kg/s * sqrt(K)/MPa494136Speed ParameterAs the turbo speed increases the flow size of the turbine decreases slightly Turbine swallowing capacity curvesWith a smaller turbine housing the expansion ratio and hence turbine power rises涡壳通流能力曲线流量参数流量参数速度参数速度参数小的涡壳，小的涡壳，可提高膨胀比和涡轮功率增压器转速增大的同时，涡轮流量减小Flow Parameter kg/s - sqrt(K)/MPa01020304050Speed Parameter rev/s * 1/sqrt(K)0.010.020.030.040.050.060.070.080.01.301.501.802.202.803.5074%72%70%64%56%74%72%70%64%56%Operation within the turbine map速度参数速度参数流量参数流量参数在涡轮性能曲线图内运行在涡轮性能曲线图内运行0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1900 rpm1300 rpmABConsider the engine moving from 1300 to 1900 rpm at constant boost pressureComp mass flow and turbo speed increaseAt the turbine, expansion ratio will increaseTorque curve characteristics 扭矩曲线特性扭矩曲线特性压比压比流量参数流量参数发动机在发动机在压比不变压比不变时，转速时，转速从从1300上上升到升到1900压气机质压气机质量流量和量流量和增压器转增压器转速升高速升高涡端膨胀涡端膨胀比增大比增大 00.40.81.21.62.02.400.010.020.030.040.050.06Fuel-air ratio燃空比燃空比Engine Temp. rise(Tem-Tim) over inlet temp(Tim) - (absolute)Lines are Diamond Engine: AJEPATL Points 4692-4906Motoring data from NT engine in brake test cellSymbols are N14 A95NE3_P5 at 1800,1200, & 800 rpm2100 rpm1800 rpm1200 rpm800 rpm20335025Air/Fuel发动机温度上发动机温度上升升Torque Curve Characteristics 扭矩曲线特性扭矩曲线特性Air-fuel ratio will increase Turbine inlet temperature will decreaseThe exhaust manifold pressure will increase The rotor speed will increaseThe pressure ratio across the engine (ratio of intake to exhaust manifold pressure) willdecrease. This means that pumping losseswill increase with increasing engine speed.As engine speed increases along the torque curve:空燃比增大涡轮进气温度降低排气歧管压力增大转子转速增大在发动机转速沿着扭矩曲线上升时：随着发动机转速的上升，进气歧管与排气歧管间的压比减小，泵气损失相应增大Engine System Performance Limits发动机性能限制发动机性能限制Torque Peak:最大扭矩最大扭矩 Air-fuel ratio, and the corresponding problems of emissions (eg: smoke) Turbine inlet temperature (thermal loading) 涡轮进气温度(热负荷) Compressor surge due to the combination of low mass flow and high pressure ratioRated Power:额定功率额定功率Rotor speed 转子转速Choke in either the compressor or turbine, resulting inlower turbo efficiencies and higher fuel consumptionUnacceptable specific fuel consumption (BSFC) due to pumping work increase 泵气功的增大会使燃油消耗率增加到我们难以接受的程度质量流量小，压比又高的情况下，会引起压气机的喘振压气机或涡轮任何一个发生阻塞时，都会导致增压器效率降低和燃油消耗量增大空燃比，以及相应的排放问题，(例如烟度)Altitude Performance Criteria高原运行指标高原运行指标 The compressor outlet temperature must not exceed a set maximum value. The turbocharger rotor physical speed must not exceed a set maximum value. The compressor must not operate in surge. The air-fuel ratio must not fall below a set minimum value. The turbine inlet temperature must not exceeda set maximum value.Air pressure decreases and also generally temperature decreases 压气机出口温度不能超过设定的最大值增压器的实际转速不能超过设定的最大值压气机不能在喘振状态下工作空燃比不能小于设定的最小值 涡轮进气温度不能超过设定的最大值大气压力降低,通常情况下温度也降低HOLW 01.01.10 gives details of turbo speed and temperature limitsHOLW 01.01.10中详细给出了增压器速度和温度的限制What Happens At Altitude?Absolute Pressure (bar)1 bar barom大气压力 1 bar Gauge表压2 bar abs绝对压力 0.510Sea Level Conditions2:1 PR0.5 bar barom 1 bar Gauge表压1.5 bar abs 绝对压力3:1 PRAltitude Conditions (5000m)1.52高海拔时的情况如何呢？绝对压力海平面状态高原状态大气压力Altitude Means Pressure Ratio Increase压缩比随着海拔高度的上升而增大压缩比随着海拔高度的上升而增大MTPPR123Moving up the engine running line therefore means the Mass Flow Parameter also increases!goes up because P goes down.MTP压缩比增大，工况点沿发动机运行线上升，质量流量参数增大MTP因为P减小了增大BUT ! Absolute pressure goes down但是，绝对压力下降了但是，绝对压力下降了Absolute Pressure (bar)1 bar barom 1 bar gauge2 bar abs 0.510Sea Level Conditions海平面状态2:1 PR0.5 bar barom 1 bar gauge1.5 bar abs3:1 PRAltitude Conditions (5000m)1.52绝对压力海拔高度为5000m时Engine is a VOLUMETRIC deviceIf absolute pressure drops, then density is lower.如果绝对压力下降，气体密度就会减小如果绝对压力下降，气体密度就会减小The engine is a volumetric device, so if density is lower, then the mass of air is less. 发动机是一个由容积衡量的设备，如果空气密度降低，空气质发动机是一个由容积衡量的设备，如果空气密度降低，空气质量也随之减小量也随之减小At altitude, the engine has a lower air/fuel ratio, even though the pressure ratio and Mass Flow Parameter have increased.在高原状态下高原状态下, 尽管压比和质量流量都有所增加尽管压比和质量流量都有所增加,但发动机的空燃但发动机的空燃比还是较小比还是较小=refrefrefTRP发动机是用容积衡量的设备发动机是用容积衡量的设备Altitude Means Pressure Ratio Increase压缩比随着海拔高度的上升而增大压缩比随着海拔高度的上升而增大MTPPR123Increase due to intake pressure dropDecrease due to lower mass flow流量参数又减小是因为质量流量的减小进气管压力降低，质量流量参数增大Predicting engine - turbocharger performance when operating at increased altitudesFive options:五项原则1.Intake manifold gauge pressure stays constant and stays on engine breathing line. (This is based upon years of observations and an example is given in text p 6-18) 进气歧管表压保持不变并继续停留在发动机吸气线上，这是基于多年的观察经验，可参考第6到18页 中的实例2. Holset Guideline: with no test data, assume compressor rotor speed parameter will increase at a rate of about: Holset 的指导方针：在没有试验数据的情况下，假定压气机转速按下述比例增大 6% per 1000 metres (1.8% per 1000 feet) at rated speed在额定转速时，每升高1000米增加6% 8% per 1000 metres (2.4% per 1000 feet) at torque peak speed 最大扭矩时，每1000米增加8%These numbers vary slightly, depending upon engine and application. See the calculation procedure in HOLW 01.01.09 这些数值变化甚微，取决于发动机本身及其应用，参考Holw 01.01.09中的计算过程 3.Run MINIMATCH - takes account of compressor efficiency changes 应用minimatch,分析压气机效率的变化4.Run GT Power - you will need to model the change in apparent heat release rate as the air/fuel ratio drops with increasing altitude. 在空燃比随着海拔高度的上升而降低的同时应用GT Power来模拟表面放热率的变化5.Run the engine in the altitude test cell. 在高原试验台架上运行发动机预测在海拔高度增加时发动机预测在海拔高度增加时发动机-增压器工作性增压器工作性能能Corporate Flow Parameter - kg/sec * sqrt(K)/MPa1000 rpmCompressor Pressure Ratio1600 rpm1800 rpm1300 rpmAltitude - ft- 500- 8500- 12000Altitude operating points on the compressor map压气机压比压气机压比总流量参数总流量参数海拔高度-英尺压气机特性图上的高原运行工况点压气机特性图上的高原运行工况点Compressor Exit Gauge Pressures压气机出口表压压气机出口表压 01020304050607004000800012000Altitude - ftComp Exit Gauge PressureHg1800 rpm1600 rpm1300 rpm1000 rpm压气机出口表压海拔高度Example of actual “% per 1000ft” factor variation1.41.51.61.71.86009001200150018002100Engine Speed rpmRotor Speed % per 1000 ft发动机转速每1000英尺转子转速变化实际海拔高度每上升1000英尺时的参数变化Altitude “box” for compressor map sizing0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1900 rpm1300 rpm12000 ft500 ft高原运行图高原运行图流量参数流量参数压比压比Turbine types (section 6.5 in the text)涡壳类型涡壳类型Single Entry单流道Twin Flow双流道AAExhaust Manifold排气歧管排气歧管Twin-entry Turbine Housing 双流道涡壳双流道涡壳Single Entry vs Twin Flow Turbines: Guidelines for Decisions单流道单流道VS双流道涡壳双流道涡壳 Single entry turbine gives about 1 percent bsfc advantage at rated speed conditions. (About 3 4 % points turbine efficiency increase) Twin entry turbine gives about 1 percent bsfc advantage at peak torque conditions. Twin entry turbine gives better transient load pickup. Twin entry turbine not suitable when wastegate flows become large.额定转速时，单流道涡壳在燃油消耗率方面有1%的优势（涡轮效率要高出3到4 个百分点）最大扭矩时，双流道涡壳在燃油消耗率方面有1%的优势双流道涡壳不适于旁通流量大的时候双流道涡壳对瞬时负载增大有更好的响应能力Cyl 1Intake ManifoldExhaust ManifoldCyl 2Cyl 3Cyl 4Cyl 5Cyl 6Comp.Turb.STACKAMBWastegated TurbochargerCoolerAfter-Wastegate旁通阀增压器旁通阀增压器旁通阀进气歧管中冷排气歧管排气管(堆栈)涡轮 压气机Typically may need more boost here e.g. To reduce smoke at low engine speeds通常是通过提高增压压力来降低发动机低速运转时的烟尘Use smaller turbine casing to give more work to the compressor hence more boost!小的涡壳,提供更多的功给压气机从而提高增压压力Now, because housing is smaller, boost will also increase across the speed range of the engine现在，由于涡壳小了,在发动机转速由最低上升到最大的过程中增压压力不断升高Small casing to suit low flow at low engine speeds give too much boost at high flow high engine speed, thus leading to over speed小的涡壳适宜于发动机低速、小流量的状态,但当发动机转速高、流量大时，由于压力上升过大, 会导致发动机超速.BANG!Small casing also means that engine will have too much boost at even less than max engine speed too much boost can exceed peak cylinder pressure limits!小的涡壳使发动机在尚未达到最大转速时，增压压力就已经很大了，甚至会超出气缸可承受的压力极限Wastegate is set to open at a specific boost pressure to prevent over-boosting the engine.Once open, boost remains approximately constant until the wastegate port becomes choked设定旁通阀在压比达到一定程度时打开,以防止对发动机增压过度旁通阀一旦打开,压比就近似的保持不变,直到旁通阀孔阻塞为止.Change in slope of boost vs flow curve indicates wastegate opening point由二维坐标压比和流量参数构成的斜线的转折点就是旁通阀的开启点Flap Valve:CheapNot Much Controlof Intermediate AreasPoppet Valve:More CostlyGood Control ofIntermediate AreasExh. Mfld orTurbine HousingExh. Mfld orTurbine Housing片转阀，便宜，中间位置控制不够提升阀，贵，中间位置控制较好排气歧管或涡壳LINKAGE WEAR POINTS联结磨损点联结磨损点Air Pressure in空气压力空气压力MovementLoad ForceSpring Force 弹簧力弹簧力Gas ForceCapsule or MotorOperation气体压力气体压力负载力负载力运动运动调节器活塞部件运动示意图调节器活塞部件运动示意图Waste Gate Controls旁通阀控制旁通阀控制Air Pressure Sources 空气压力来源 Compressor Cover 压壳 Intake Manifold (temperature) 进气歧管（温度） Brake Tank 制动箱 Exhaust Manifold 排气歧管Air Pressure Controls 空气压力控制 None (use varying pressure of source) 没有（采用变化的压力资源） Electronic Valves 电子阀 4 Step 4步 PWM valve (tank air) 脉宽调制阀（储存空气） Command valve (boost air) 命令阀（增压空气）VentBoost Air SignalValveActuator调节器OrificeCommand VaIve Integral modulating WG - System Concept命令阀命令阀- -整体调节旁通阀整体调节旁通阀- -系统概念系统概念增压信号孔阀出口50010001500200025003000350700Torque (Nm)Speed (rpm)0Area of modulated wastegate control (with lower rate spring) No control possibleConventional WastegateCommand Valve Integral Modulating WG - operating range命令阀命令阀- -整体调节旁通阀整体调节旁通阀- -运行范围运行范围不可控区域传统的旁通阀可调节旁通阀控制区域（低压缩率的弹簧）转速扭矩Command VaIve Integral Modulating WG命令阀-整体调节旁通阀Command Valve Integral Modulating WG命令阀命令阀-整体调节旁通阀整体调节旁通阀Waste Gate Field Problems and Fixes (continued) Waste Gate Hardware/Mechanism: 旁通阀硬件/机械装置1. Air supply hose breaks, burns, or is removed by user. 空气传送管破裂，灼烧，或被人为的移动2. Actuator diaphragm leaks/ruptures 调节器振动模漏气/破裂3. Set point changes due to spring taking a set 由于弹簧残余变形而改变设置点Solution: heat treat the spring and change spring material 解决办法:热处理弹簧及改变弹簧材料4. Mechanism durability/fretting wear of shaft, bushing, pin, and rod - (much more movement when used to modulate boost and peak cylinder pressure than when simply used for max. rotor speed control) 材料的耐久力，轴、衬套、销和连杆的腐蚀磨损，这些运动件在 调节增压压力和控制气缸最大压力时所做的运动要比单纯的控制 最大转子转速所做的运动多的多Solutions: Stellite 6 shaft, 420V bushing, triballoy T400 pin and bushing in rod旁通阀的使用问题与修理解决办法，轴采用材料Stellite6，420V衬套，连杆的销和衬套采用T400spring forceforce due toactuator airpressureforce due toexhaust gaspressureexhaust manifoldor turbine housinggas passage弹力调节器空气压力调节器空气压力废气压力废气压力排气歧管或涡壳进气通道WASTEGATE CLOSEDWASTEGATE OPENINGWASTEGATE CHOKED通流能力压比旁通阀阻塞旁通阀阻塞旁通阀关闭旁通阀关闭旁通阀开启旁通阀开启Affect of turbine control on compressor operation1.01.52.02.53.03.54.04.55.05.50102030405060708090100Mass Flow (kg/sec. K/MPa)Pressure Ratio (T-T)FGFGWGWGVGVGEGR, high torque 不同涡轮控制方式在压气机特性图上的体现大扭矩时Cyl 1Intake ManifoldExhaust ManifoldCyl 2Cyl 3Cyl 4Cyl 5Cyl 6Comp.Turb.STACKAMBVariable Geometry Turbine可变截面涡轮可变截面涡轮CoolerAfter-进气歧管进气歧管排气歧管排气歧管中冷中冷压气机压气机涡轮涡轮可移动喷嘴环可移动喷嘴环固定限流板固定限流板DEFINITION OF V.G. OPENINGClosed Position = Y * 100 / X %Nozzle face flush with channel back facePosition is 100% (X=Y)Max. flow (100+%)Position = Y * 100 / X %对可变截面开启的定义关闭，位置关闭，位置= Y * 100 / X %喷嘴面与槽的背面齐平，喷嘴面与槽的背面齐平，位置位置100%最大流量，位置最大流量，位置= Y * 100 / X %11.21.41.61.822.22.42.62.83010203040506070Flow Parameter - (kg/sec)*(K*.5)/MPaPressure RatioClosed14%13Q1136%71%22Q11107%143%VGT HX50 - 40-31-12流量参数流量参数压比压比流量参数流量参数效率效率恒压比Creating efficiency vs flow characteristics效率与流量的关系Actual Dynamometer maps 56% to 218% nozzle gap (expressed as % of turbine wheel tip width)实际的测功图-喷嘴间隙由56%到218%，这个百分比是喷嘴间隙与涡轮顶部宽度的比值1.61.61.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 218%1.61.61.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 847123489Proj 02/0223-21 , Test 38298 , 1.61.61.81.82.22.22.62.63.03.0101520253035404550550102030405060708090100N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 157%1.61.61.81.82.22.22.62.63.03.03034384246505458626670740102030405060708090100Efficiency , Index 847027052Proj 02/0223-20 , Test 38287 , 1.61.61.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 124%1.61.61.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 847014156Proj 02/0223-19 , Test 38282 , 1.61.61.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 101%1.61.61.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 846844162Proj 02/0233-16 , Test 38258 , 1.61.61.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 79%1.61.61.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 846948455Proj 02/0223-18 , Test 38274 , 1.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 56%1.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 846941665Proj 02/0233-17 , Test 38272 , Closing逐渐关闭Fully open全开1.61.61.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 218%1.61.61.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 847123489Proj 02/0223-21 , Test 38298 , 1.61.61.81.82.22.22.62.63.03.0101520253035404550550102030405060708090100N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 157%1.61.61.81.82.22.22.62.63.03.03034384246505458626670740102030405060708090100Efficiency , Index 847027052Proj 02/0223-20 , Test 38287 , 1.61.61.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 124%1.61.61.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 847014156Proj 02/0223-19 , Test 38282 , 1.61.61.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 101%1.61.61.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 846844162Proj 02/0233-16 , Test 38258 , 1.61.61.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 79%1.61.61.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 846948455Proj 02/0223-18 , Test 38274 , 1.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ T (rps/ K)m T/p Corp. (kg/sec. K/MPa)HY40V A29CX23 56%1.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Efficiency , Index 846941665Proj 02/0233-17 , Test 38272 , Creating peak efficiency vs flow data for a given expansion ratio:针对给定的膨胀比，做最大效率VS流量图For each expansion ration, select the peak efficiency value and the speed/flow value at which it occurs对于每一个膨胀比，找出最高效率值，以及对应的速度/流量值0102030405060708005101520253035404550CORPORATE MASS FLOW PARAMETEREFFICIENCYExpansion Ratio = 2.2Sliding Nozzle - HX40 Low Flow VGTSwing Vane - MHI/HY35AP36 VGT膨胀比膨胀比总质量流量参数总质量流量参数效率效率摆动叶片摆动叶片移动喷嘴移动喷嘴-HX40 低流量低流量VGTTransient or Load-Shedding Compressor Surge瞬时负载减小时压气机的喘振瞬时负载减小时压气机的喘振This is a SYSTEM PROBLEM - NOT a compressor problem这是系统问题-不是压气机的问题The compressor can be driven into surge by the engine system if the throttle is snapped shutwhile the engine is running at high bmep levels发动机在高工况运行时，突然关闭油门，就会导致压气机发生喘振ENGINEdisp. = VdAftercooler+pipingvolume=Vac=2-4xVdtime const.Vac/Veng.Veng=rpm*Vd/2.CompressorTurbineTurbo shaft - time constant I* Transient Surge - First Order Model瞬时喘振瞬时喘振-第一种命令模式第一种命令模式Turbo shaft inertia keeps speed (and boostsupply pressure) from changing.Aftercooler and piping volumeskeep intake system pressure from changing.轴惯量维持增压器的转速（增压比）不发生变化轴惯量维持增压器的转速（增压比）不发生变化轴轴时间常量时间常量压气机压气机涡轮涡轮发动机发动机排量排量中冷器中冷器+管道容积管道容积中冷器和空气输送管道维持进气系统中冷器和空气输送管道维持进气系统压力不变压力不变转速转速Transient withthrottle snapped shutfrom full fuelingFlow Parameter kg/s * sqrt(K)/MPa 0 25 50 75 100 125 150 1.0 1.4 1.8 2.2 2.6 3.0 3.4 3.8 4.2 46 54 60 64 68 72 75 78 82 85 90 80% 72% 68% 64% 78% 76% Compressor Pressure RatioSteady StateOperation稳定状态运行稳定状态运行油门由全开状态突然关闭的瞬时现象油门由全开状态突然关闭的瞬时现象流量参数流量参数压气机压比压气机压比Flow Parameter kg/s * sqrt(K)/MPa 0 25 50 75 100 125 150 1.0 1.4 1.8 2.2 2.6 3.0 3.4 3.8 4.2 Compressor P