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1、The Application of Turbomachinery to Reciprocating Engines渦輪機(jī)械在往復(fù)式發(fā)動機(jī)上的應(yīng)用Chapter 6第第6章章Matching 4-Stroke Diesels與四沖程柴油機(jī)匹配Volumetric Efficiency容積效率容積效率The volumetric efficiency is defined as; 充氣效率的定義如下充氣效率的定義如下where:D= Displacement per cycle length3/cycle 一個工作循環(huán)的排量一個工作循環(huán)的排量長度長度3/循環(huán)次數(shù)循環(huán)次數(shù)N= Engine spe

2、ed rev/time 發(fā)動機(jī)轉(zhuǎn)速發(fā)動機(jī)轉(zhuǎn)速轉(zhuǎn)轉(zhuǎn)/分分NRPC = Number of revolutions per cycle 2 for a four-stroke engine每循環(huán)活塞往復(fù)運(yùn)動次數(shù)每循環(huán)活塞往復(fù)運(yùn)動次數(shù)二或四沖程二或四沖程where: vol= Volumetric Efficiency dimensionless容積效率容積效率無量綱無量綱min= Net mass flow rate into engine cylinders mass/time進(jìn)入氣缸的凈質(zhì)量流量進(jìn)入氣缸的凈質(zhì)量流量質(zhì)量質(zhì)量/時間時間 ref= Reference density mass/le

3、ngth3參考密度參考密度質(zhì)量質(zhì)量/長度長度3VDR= Volumetric displacement rate length3/time單位時間體積排量單位時間體積排量長度長度3/時間時間The volumetric displacement rate is calculated by;單位時間體積排量按下面的公式計算單位時間體積排量按下面的公式計算.volinref = actual air mass flowideal air mass flow = m*VDR VDR = D*NNRPC Volumetric Efficiency (continued)容積效率容積效率The refe

4、rence density is calculated from the ideal gas law (P*v = m*R*T);參考密度按照理想氣體狀態(tài)方程計算參考密度按照理想氣體狀態(tài)方程計算where:R= Gas constant for air (length*force)/(mass*temperature)空氣氣體常數(shù)空氣氣體常數(shù)Pref= Reference pressure mass/length2 (Ref conditions in the inlet manifold) 參考壓力參考壓力（在進(jìn)氣管狀態(tài)下）（在進(jìn)氣管狀態(tài)下）Tref= Reference temperatu

5、re temperature 參考溫度參考溫度Substituting these relationships into the definition of volumetric efficiency gives;把這些參數(shù)帶入上述充氣效率公式中則有把這些參數(shù)帶入上述充氣效率公式中則有: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 e

6、quation derived from the definition of Volumetric Efficiency;由容積效率定義得出方程式由容積效率定義得出方程式:Make the following assumptions/approximations;做下面的假設(shè)做下面的假設(shè)/近似值近似值 vol= a constant (somewhere between .88 and .95) 常量常量(0.88到到0.95之間之間)Pref= Pamb * (Compressor Pressure Ratio) = Pamb*PRc壓氣機(jī)壓縮比壓氣機(jī)壓縮比Tref= a constant

7、(for an aftercooled engine)常量常量(對中冷發(fā)動機(jī)對中冷發(fā)動機(jī))D= a constant (for a given engine)常量常量(對指定的發(fā)動機(jī)對指定的發(fā)動機(jī))Substituting these relationships into the equation above gives;把這些參數(shù)代如上方程式有把這些參數(shù)代如上方程式有:Converting this to the Mass Flow Parameter used in the compressor map gives:=refrefvolinTNRPCRPNDm.cinPRTNConstan

8、tMFP=()ambinincambinininPPTPRPNConstantPTmMFP=.cambinPRPNConstantm=吸氣線吸氣線(四沖程發(fā)動機(jī)才有四沖程發(fā)動機(jī)才有)轉(zhuǎn)換成壓氣機(jī)特性曲線上的質(zhì)量流量參數(shù)轉(zhuǎn)換成壓氣機(jī)特性曲線上的質(zhì)量流量參數(shù)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 rpm130

9、0 rpm壓氣機(jī)特性曲線坐標(biāo)中的吸氣線壓氣機(jī)特性曲線坐標(biāo)中的吸氣線流量參數(shù)流量參數(shù)壓壓縮縮比比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壓氣機(jī)特性曲線圖上的吸氣線壓氣機(jī)特性曲線圖上的吸氣線壓壓縮縮比比流量參數(shù)流量參數(shù)Compressor map too small壓氣機(jī)特性曲線圖太小壓氣機(jī)特性曲線圖太小0255

10、075100125150175200 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流量參數(shù)流量參數(shù)壓壓縮縮比比Compressor map too large壓氣機(jī)特性曲線圖太大壓氣機(jī)特性曲線圖太大0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.83.03.23.43.63.8Pressure Ratio1

11、900 rpm1300 rpm壓壓縮縮比比流量參數(shù)流量參數(shù)Compressor map too narrow 壓氣機(jī)性能曲線圖太窄壓氣機(jī)性能曲線圖太窄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流量參數(shù)流量參數(shù)壓壓縮縮比比壓壓縮縮比比壓氣機(jī)性能曲線上的工作點(diǎn)壓氣機(jī)性能曲線上的工作點(diǎn)工作點(diǎn)的估算工作點(diǎn)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)空氣流量空氣流

12、量(速速)質(zhì)量流量參數(shù)質(zhì)量流量參數(shù)知道了知道了MFP，和已有的吸氣和已有的吸氣線，就可得出線，就可得出壓縮比壓縮比PRc流量參數(shù)流量參數(shù)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 =

13、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 Casin

14、g Smaller Casing渦殼的選擇對壓氣機(jī)特性曲線上工作點(diǎn)的影響渦殼的選擇對壓氣機(jī)特性曲線上工作點(diǎn)的影響流量參數(shù)流量參數(shù)壓壓縮縮比比大的渦殼大的渦殼小的渦殼小的渦殼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

15、turbine housing the expansion ratio and hence turbine power rises渦殼通流能力曲線流量參數(shù)流量參數(shù)速度參數(shù)速度參數(shù)小的渦殼，小的渦殼，可提高膨脹比和渦輪功率增壓器轉(zhuǎn)速增大的同時，渦輪流量減小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%Operati

16、on within the turbine map速度參數(shù)速度參數(shù)流量參數(shù)流量參數(shù)在渦輪性能曲線圖內(nèi)運(yùn)行在渦輪性能曲線圖內(nèi)運(yùn)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

17、 increaseAt the turbine, expansion ratio will increaseTorque curve characteristics 扭矩曲線特性扭矩曲線特性壓比壓比流量參數(shù)流量參數(shù)發(fā)動機(jī)在發(fā)動機(jī)在壓比不變壓比不變時，轉(zhuǎn)速時，轉(zhuǎn)速從從1300上上升到升到1900壓氣機(jī)質(zhì)壓氣機(jī)質(zhì)量流量和量流量和增壓器轉(zhuǎn)增壓器轉(zhuǎn)速升高速升高渦端膨脹渦端膨脹比增大比增大 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(T

18、im) - (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發(fā)動機(jī)溫度上發(fā)動機(jī)溫度上升升Torque Curve Characteristics 扭矩曲線特性扭矩曲線特性Air-fuel ratio will increase Turbine

19、 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 increase

20、s along the torque curve:空燃比增大渦輪進(jìn)氣溫度降低排氣歧管壓力增大轉(zhuǎn)子轉(zhuǎn)速增大在發(fā)動機(jī)轉(zhuǎn)速沿著扭矩曲線上升時：隨著發(fā)動機(jī)轉(zhuǎn)速的上升，進(jìn)氣歧管與排氣歧管間的壓比減小，泵氣損失相應(yīng)增大Engine System Performance Limits發(fā)動機(jī)性能限制發(fā)動機(jī)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) 渦輪進(jìn)氣溫度(熱負(fù)荷) Co

21、mpressor surge due to the combination of low mass flow and high pressure ratioRated Power:額定功率額定功率Rotor speed 轉(zhuǎn)子轉(zhuǎn)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 泵氣功的

22、增大會使燃油消耗率增加到我們難以接受的程度質(zhì)量流量小，壓比又高的情況下，會引起壓氣機(jī)的喘振壓氣機(jī)或渦輪任何一個發(fā)生阻塞時，都會導(dǎo)致增壓器效率降低和燃油消耗量增大空燃比，以及相應(yīng)的排放問題，(例如煙度)Altitude Performance Criteria高原運(yùn)行指標(biāo)高原運(yùn)行指標(biāo) The compressor outlet temperature must not exceed a set maximum value. The turbocharger rotor physical speed must not exceed a set maximum value. The compress

23、or 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 壓氣機(jī)出口溫度不能超過設(shè)定的最大值增壓器的實(shí)際轉(zhuǎn)速不能超過設(shè)定的最大值壓氣機(jī)不能在喘振狀態(tài)下工作空燃比不能小于設(shè)定的最小值 渦輪進(jìn)氣溫度不能超過設(shè)定的最大值大氣壓

24、力降低,通常情況下溫度也降低HOLW 01.01.10 gives details of turbo speed and temperature limitsHOLW 01.01.10中詳細(xì)給出了增壓器速度和溫度的限制What Happens At Altitude?Absolute Pressure (bar)1 bar barom大氣壓力 1 bar Gauge表壓2 bar abs絕對壓力 0.510Sea Level Conditions2:1 PR0.5 bar barom 1 bar Gauge表壓1.5 bar abs 絕對壓力3:1 PRAltitude Conditions

25、(5000m)1.52高海拔時的情況如何呢？絕對壓力海平面狀態(tài)高原狀態(tài)大氣壓力Altitude Means Pressure Ratio Increase壓縮比隨著海拔高度的上升而增大壓縮比隨著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壓縮比增大，工況點(diǎn)沿發(fā)動機(jī)運(yùn)行線上升，質(zhì)量流量參數(shù)增大MTP因?yàn)镻減小了增大BUT ! Absolute pressure goe

26、s down但是，絕對壓力下降了但是，絕對壓力下降了Absolute Pressure (bar)1 bar barom 1 bar gauge2 bar abs 0.510Sea Level Conditions海平面狀態(tài)2:1 PR0.5 bar barom 1 bar gauge1.5 bar abs3:1 PRAltitude Conditions (5000m)1.52絕對壓力海拔高度為5000m時Engine is a VOLUMETRIC deviceIf absolute pressure drops, then density is lower.如果絕對壓力下降，氣體密度就會

27、減小如果絕對壓力下降，氣體密度就會減小The engine is a volumetric device, so if density is lower, then the mass of air is less. 發(fā)動機(jī)是一個由容積衡量的設(shè)備，如果空氣密度降低，空氣質(zhì)發(fā)動機(jī)是一個由容積衡量的設(shè)備，如果空氣密度降低，空氣質(zhì)量也隨之減小量也隨之減小At altitude, the engine has a lower air/fuel ratio, even though the pressure ratio and Mass Flow Parameter have increased.在高原狀

28、態(tài)下高原狀態(tài)下, 盡管壓比和質(zhì)量流量都有所增加盡管壓比和質(zhì)量流量都有所增加,但發(fā)動機(jī)的空燃但發(fā)動機(jī)的空燃比還是較小比還是較小=refrefrefTRP發(fā)動機(jī)是用容積衡量的設(shè)備發(fā)動機(jī)是用容積衡量的設(shè)備Altitude Means Pressure Ratio Increase壓縮比隨著海拔高度的上升而增大壓縮比隨著海拔高度的上升而增大MTPPR123Increase due to intake pressure dropDecrease due to lower mass flow流量參數(shù)又減小是因?yàn)橘|(zhì)量流量的減小進(jìn)氣管壓力降低，質(zhì)量流量參數(shù)增大Predicting engine - turbo

29、charger performance when operating at increased altitudesFive options:五項原則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) 進(jìn)氣歧管表壓保持不變并繼續(xù)停留在發(fā)動機(jī)吸氣線上，這是基于多年的觀察經(jīng)驗(yàn)，可參考第6到18頁 中的實(shí)例2. Holset

30、Guideline: with no test data, assume compressor rotor speed parameter will increase at a rate of about: Holset 的指導(dǎo)方針：在沒有試驗(yàn)數(shù)據(jù)的情況下，假定壓氣機(jī)轉(zhuǎn)速按下述比例增大 6% per 1000 metres (1.8% per 1000 feet) at rated speed在額定轉(zhuǎn)速時，每升高1000米增加6% 8% per 1000 metres (2.4% per 1000 feet) at torque peak speed 最大扭矩時，每1000米增加8%These

31、 numbers vary slightly, depending upon engine and application. See the calculation procedure in HOLW 01.01.09 這些數(shù)值變化甚微，取決于發(fā)動機(jī)本身及其應(yīng)用，參考Holw 01.01.09中的計算過程 3.Run MINIMATCH - takes account of compressor efficiency changes 應(yīng)用minimatch,分析壓氣機(jī)效率的變化4.Run GT Power - you will need to model the change in appar

32、ent heat release rate as the air/fuel ratio drops with increasing altitude. 在空燃比隨著海拔高度的上升而降低的同時應(yīng)用GT Power來模擬表面放熱率的變化5.Run the engine in the altitude test cell. 在高原試驗(yàn)臺架上運(yùn)行發(fā)動機(jī)預(yù)測在海拔高度增加時發(fā)動機(jī)預(yù)測在海拔高度增加時發(fā)動機(jī)-增壓器工作性增壓器工作性能能Corporate Flow Parameter - kg/sec * sqrt(K)/MPa1000 rpmCompressor Pressure Ratio1600 r

33、pm1800 rpm1300 rpmAltitude - ft- 500- 8500- 12000Altitude operating points on the compressor map壓氣機(jī)壓比壓氣機(jī)壓比總流量參數(shù)總流量參數(shù)海拔高度-英尺壓氣機(jī)特性圖上的高原運(yùn)行工況點(diǎn)壓氣機(jī)特性圖上的高原運(yùn)行工況點(diǎn)Compressor Exit Gauge Pressures壓氣機(jī)出口表壓壓氣機(jī)出口表壓 01020304050607004000800012000Altitude - ftComp Exit Gauge PressureHg1800 rpm1600 rpm1300 rpm1000 rpm壓

34、氣機(jī)出口表壓海拔高度Example of actual “% per 1000ft” factor variation1.41.51.61.71.86009001200150018002100Engine Speed rpmRotor Speed % per 1000 ft發(fā)動機(jī)轉(zhuǎn)速每1000英尺轉(zhuǎn)子轉(zhuǎn)速變化實(shí)際海拔高度每上升1000英尺時的參數(shù)變化Altitude “box” for compressor map sizing0255075100125150175200Flow Parameter kg/s * sqrt(K)/MPa1.01.21.41.61.82.02.22.42.62.

35、83.03.23.43.63.8Pressure Ratio1900 rpm1300 rpm12000 ft500 ft高原運(yùn)行圖高原運(yùn)行圖流量參數(shù)流量參數(shù)壓比壓比Turbine types (section 6.5 in the text)渦殼類型渦殼類型Single Entry單流道Twin Flow雙流道AAExhaust Manifold排氣歧管排氣歧管Twin-entry Turbine Housing 雙流道渦殼雙流道渦殼Single Entry vs Twin Flow Turbines: Guidelines for Decisions單流道單流道VS雙流道渦殼雙流道渦殼 Si

36、ngle 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 suitabl

37、e when wastegate flows become large.額定轉(zhuǎn)速時，單流道渦殼在燃油消耗率方面有1%的優(yōu)勢（渦輪效率要高出3到4 個百分點(diǎn)）最大扭矩時，雙流道渦殼在燃油消耗率方面有1%的優(yōu)勢雙流道渦殼不適于旁通流量大的時候雙流道渦殼對瞬時負(fù)載增大有更好的響應(yīng)能力Cyl 1Intake ManifoldExhaust ManifoldCyl 2Cyl 3Cyl 4Cyl 5Cyl 6Comp.Turb.STACKAMBWastegated TurbochargerCoolerAfter-Wastegate旁通閥增壓器旁通閥增壓器旁通閥進(jìn)氣歧管中冷排氣歧管排氣管(堆棧)渦輪 壓氣機(jī)

38、Typically may need more boost here e.g. To reduce smoke at low engine speeds通常是通過提高增壓壓力來降低發(fā)動機(jī)低速運(yùn)轉(zhuǎn)時的煙塵Use smaller turbine casing to give more work to the compressor hence more boost!小的渦殼,提供更多的功給壓氣機(jī)從而提高增壓壓力Now, because housing is smaller, boost will also increase across the speed range of the engine現(xiàn)在

39、，由于渦殼小了,在發(fā)動機(jī)轉(zhuǎn)速由最低上升到最大的過程中增壓壓力不斷升高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小的渦殼適宜于發(fā)動機(jī)低速、小流量的狀態(tài),但當(dāng)發(fā)動機(jī)轉(zhuǎn)速高、流量大時，由于壓力上升過大, 會導(dǎo)致發(fā)動機(jī)超速.BANG!Small casing also means that engine will have too much boost at even less than

40、max engine speed too much boost can exceed peak cylinder pressure limits!小的渦殼使發(fā)動機(jī)在尚未達(dá)到最大轉(zhuǎn)速時，增壓壓力就已經(jīng)很大了，甚至?xí)鰵飧卓沙惺艿膲毫O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設(shè)定旁通閥

41、在壓比達(dá)到一定程度時打開,以防止對發(fā)動機(jī)增壓過度旁通閥一旦打開,壓比就近似的保持不變,直到旁通閥孔阻塞為止.Change in slope of boost vs flow curve indicates wastegate opening point由二維坐標(biāo)壓比和流量參數(shù)構(gòu)成的斜線的轉(zhuǎn)折點(diǎn)就是旁通閥的開啟點(diǎn)Flap Valve:CheapNot Much Controlof Intermediate AreasPoppet Valve:More CostlyGood Control ofIntermediate AreasExh. Mfld orTurbine HousingExh. Mf

42、ld orTurbine Housing片轉(zhuǎn)閥，便宜，中間位置控制不夠提升閥，貴，中間位置控制較好排氣歧管或渦殼LINKAGE WEAR POINTS聯(lián)結(jié)磨損點(diǎn)聯(lián)結(jié)磨損點(diǎn)Air Pressure in空氣壓力空氣壓力MovementLoad ForceSpring Force 彈簧力彈簧力Gas ForceCapsule or MotorOperation氣體壓力氣體壓力負(fù)載力負(fù)載力運(yùn)動運(yùn)動調(diào)節(jié)器活塞部件運(yùn)動示意圖調(diào)節(jié)器活塞部件運(yùn)動示意圖Waste Gate Controls旁通閥控制旁通閥控制Air Pressure Sources 空氣壓力來源 Compressor Cover 壓殼 In

43、take Manifold (temperature) 進(jìn)氣歧管（溫度） Brake Tank 制動箱 Exhaust Manifold 排氣歧管Air Pressure Controls 空氣壓力控制 None (use varying pressure of source) 沒有（采用變化的壓力資源） Electronic Valves 電子閥 4 Step 4步 PWM valve (tank air) 脈寬調(diào)制閥（儲存空氣） Command valve (boost air) 命令閥（增壓空氣）VentBoost Air SignalValveActuator調(diào)節(jié)器OrificeCom

44、mand VaIve Integral modulating WG - System Concept命令閥命令閥- -整體調(diào)節(jié)旁通閥整體調(diào)節(jié)旁通閥- -系統(tǒng)概念系統(tǒng)概念增壓信號孔閥出口50010001500200025003000350700Torque (Nm)Speed (rpm)0Area of modulated wastegate control (with lower rate spring) No control possibleConventional WastegateCommand Valve Integral Modulating WG - operating range

45、命令閥命令閥- -整體調(diào)節(jié)旁通閥整體調(diào)節(jié)旁通閥- -運(yùn)行范圍運(yùn)行范圍不可控區(qū)域傳統(tǒng)的旁通閥可調(diào)節(jié)旁通閥控制區(qū)域（低壓縮率的彈簧）轉(zhuǎn)速扭矩Command VaIve Integral Modulating WG命令閥-整體調(diào)節(jié)旁通閥Command Valve Integral Modulating WG命令閥命令閥-整體調(diào)節(jié)旁通閥整體調(diào)節(jié)旁通閥Waste Gate Field Problems and Fixes (continued) Waste Gate Hardware/Mechanism: 旁通閥硬件/機(jī)械裝置1. Air supply hose breaks, burns, or is

46、 removed by user. 空氣傳送管破裂，灼燒，或被人為的移動2. Actuator diaphragm leaks/ruptures 調(diào)節(jié)器振動模漏氣/破裂3. Set point changes due to spring taking a set 由于彈簧殘余變形而改變設(shè)置點(diǎn)Solution: heat treat the spring and change spring material 解決辦法:熱處理彈簧及改變彈簧材料4. Mechanism durability/fretting wear of shaft, bushing, pin, and rod - (much

47、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，軸、襯套、銷和連桿的腐蝕磨損，這些運(yùn)動件在 調(diào)節(jié)增壓壓力和控制氣缸最大壓力時所做的運(yùn)動要比單純的控制 最大轉(zhuǎn)子轉(zhuǎn)速所做的運(yùn)動多的多Solutions: Stellite 6 shaft, 420V bushing, triballoy T400 pin and bushing in rod旁通閥的使用問題與修理解決辦法，軸采用材料Stelli

48、te6，420V襯套，連桿的銷和襯套采用T400spring forceforce due toactuator airpressureforce due toexhaust gaspressureexhaust manifoldor turbine housinggas passage彈力調(diào)節(jié)器空氣壓力調(diào)節(jié)器空氣壓力廢氣壓力廢氣壓力排氣歧管或渦殼進(jìn)氣通道WASTEGATE CLOSEDWASTEGATE OPENINGWASTEGATE CHOKED通流能力壓比旁通閥阻塞旁通閥阻塞旁通閥關(guān)閉旁通閥關(guān)閉旁通閥開啟旁通閥開啟Affect of turbine control on compres

49、sor operation1.01.52.02.53.03.54.04.55.05.50102030405060708090100Mass Flow (kg/sec. K/MPa)Pressure Ratio (T-T)FGFGWGWGVGVGEGR, high torque 不同渦輪控制方式在壓氣機(jī)特性圖上的體現(xiàn)大扭矩時Cyl 1Intake ManifoldExhaust ManifoldCyl 2Cyl 3Cyl 4Cyl 5Cyl 6Comp.Turb.STACKAMBVariable Geometry Turbine可變截面渦輪可變截面渦輪CoolerAfter-進(jìn)氣歧管進(jìn)氣歧管排氣

50、歧管排氣歧管中冷中冷壓氣機(jī)壓氣機(jī)渦輪渦輪可移動噴嘴環(huán)可移動噴嘴環(huán)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 %對可變截面開啟的定義關(guān)閉，位置關(guān)閉，位置= Y * 100 / X %噴嘴面與槽的背面齊平，噴嘴面與槽的背面齊平，位置位置100%最大流量，位置最大流量，位置= Y * 100 / X %11.2

51、1.41.61.822.22.42.62.83010203040506070Flow Parameter - (kg/sec)*(K*.5)/MPaPressure RatioClosed14%13Q1136%71%22Q11107%143%VGT HX50 - 40-31-12流量參數(shù)流量參數(shù)壓比壓比流量參數(shù)流量參數(shù)效率效率恒壓比Creating efficiency vs flow characteristics效率與流量的關(guān)系A(chǔ)ctual Dynamometer maps 56% to 218% nozzle gap (expressed as % of turbine wheel ti

52、p width)實(shí)際的測功圖-噴嘴間隙由56%到218%，這個百分比是噴嘴間隙與渦輪頂部寬度的比值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 ,

53、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 , 1.61.61.81.82.22.22.62.63.03.010152

54、025303540455055020406080100120N/ 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

55、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.

56、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%1.81.82.22.22.62.63.03.0303438424650545862667074020406080100120Effi

57、ciency , Index 846941665Proj 02/0233-17 , Test 38272 , Closing逐漸關(guān)閉Fully open全開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 847123489Pr

58、oj 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 , 1.61.6

59、1.81.82.22.22.62.63.03.010152025303540455055020406080100120N/ 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 , 1.61.61.81.82.22.22.62.63.03.01015202530354045505502040

60、6080100120N/ 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

61、)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%1.81.82.22.22.62.63.03.030343842465054

62、5862667074020406080100120Efficiency , Index 846941665Proj 02/0233-17 , Test 38272 , Creating peak efficiency vs flow data for a given expansion ratio:針對給定的膨脹比，做最大效率VS流量圖For each expansion ration, select the peak efficiency value and the speed/flow value at which it occurs對于每一個膨脹比，找出最高效率值，以及對應(yīng)的速度/流量值

63、0102030405060708005101520253035404550CORPORATE MASS FLOW PARAMETEREFFICIENCYExpansion Ratio = 2.2Sliding Nozzle - HX40 Low Flow VGTSwing Vane - MHI/HY35AP36 VGT膨脹比膨脹比總質(zhì)量流量參數(shù)總質(zhì)量流量參數(shù)效率效率擺動葉片擺動葉片移動噴嘴移動噴嘴-HX40 低流量低流量VGTTransient or Load-Shedding Compressor Surge瞬時負(fù)載減小時壓氣機(jī)的喘振瞬時負(fù)載減小時壓氣機(jī)的喘振This is a SYSTEM

64、 PROBLEM - NOT a compressor problem這是系統(tǒng)問題-不是壓氣機(jī)的問題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發(fā)動機(jī)在高工況運(yùn)行時，突然關(guān)閉油門，就會導(dǎo)致壓氣機(jī)發(fā)生喘振ENGINEdisp. = VdAftercooler+pipingvolume=Vac=2-4xVdtime const.Vac/Veng.Veng=rpm*Vd

65、/2.CompressorTurbineTurbo shaft - time constant I* Transient Surge - First Order Model瞬時喘振瞬時喘振-第一種命令模式第一種命令模式Turbo shaft inertia keeps speed (and boostsupply pressure) from changing.Aftercooler and piping volumeskeep intake system pressure from changing.軸慣量維持增壓器的轉(zhuǎn)速（增壓比）不發(fā)生變化軸慣量維持增壓器的轉(zhuǎn)速（增壓比）不發(fā)生變化軸軸時間

66、常量時間常量壓氣機(jī)壓氣機(jī)渦輪渦輪發(fā)動機(jī)發(fā)動機(jī)排量排量中冷器中冷器+管道容積管道容積中冷器和空氣輸送管道維持進(jìn)氣系統(tǒng)中冷器和空氣輸送管道維持進(jìn)氣系統(tǒng)壓力不變壓力不變轉(zhuǎn)速轉(zhuǎn)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穩(wěn)定狀態(tài)運(yùn)行穩(wěn)定狀態(tài)運(yùn)行油門由全開狀態(tài)突然關(guān)閉的瞬時現(xiàn)象油門由全開狀態(tài)突然關(guān)閉的瞬時現(xiàn)象流量參數(shù)流量參數(shù)壓氣機(jī)壓比壓氣機(jī)壓比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