B737点火系统维修手册英文翻译.doc

B737 Ignition1. IGNITION INTRODUCTION2. IGNITION - GENERAL DESCRIPTION3. IGNITION - ENGINE COMPONENT LOCATION4. IGNITION - FLIGHT COMPARTMENT COMPONENT LOCATIONS5. IGNITION - IGNITION EXCITER6. IGNITION - DISTRIBUTION - IGNITION LEADS AND SPARK IGNITERS7. IGNITION - FUNCTIONAL DESCRIPTION8. IGNITION OPERATION9. IGNITION - TRAINING INFORMATION POINTIGNITION - INTRODUCTIONGeneralThe ignition systems supply electrical sparks in the combustion chamber for combustion. Each engine has two ignition systems that operate independently. The ignition system usually operates manually. However, the ignition systems operate automatically when the electronic engine control (EEC) sees a possible engine flameout condition.You use ignition during these times:1. Ground start2. Takeoff and landings3. In-flight (during heavy turbulence or bad weather)4. In-flight start.Abbreviations and Acronyms1. CDS - common display system2. CDU - control display unit3. CONT - continuous4. DEU - display electronics unit5. EEC - electronic engine control6. FLT - flight7. FMC - flight management computer8. GRD - ground9. IGN - ignition10. L - left11. R rightIGNITION - INTRODUCTIONIGNITION - GENERAL DESCRIPTIONGeneralThese components control ignition:1. Start levers2. Start switches3. Ignition selector switch4. Electronic engine control (EEC).The start lever controls ignition system power to the EEC. The start switch and the ignition selector switch supply inputs to the EEC. The EEC uses these inputs to supply power to the ignition exciters. The ignition exciters supply power to the spark igniters.The engine starting system also uses the switch positions for control.See the engine starting chapter for more informationElectrical PowerThe engine 1 ignition systems receive 115v ac from ac transfer bus 1 and the ac standby bus. The EEC has internal switches that control the 115v ac to the ignition exciters. The ignition exciters change the 115v ac input to a dc voltage of approximately 15,000 to 20,000v for the spark igniters. The spark igniters give a spark for combustion. The ignition systems of engine 2 receive ac power from ac transfer bus 2 and the ac standby bus.IGNITION - GENERAL DESCRIPTIONIGNITION - ENGINE COMPONENT LOCATIONGeneralEach engine has a right and a left ignition system. These are the components of each ignition system:1. Ignition exciter2. Ignition lead3. Air manifold4. Spark igniter.Component LocationsThe ignition exciters are on the right side, lower portion, of the fan case.The ignition leads go from the ignition exciters to the spark igniters on the right and left sides of the engine.The air manifold goes around the ignition leads. The air manifold starts in the 6:00 strut and goes to the igniters.The spark igniters are just forward of the fuel manifold, at the 4:00 position and the 8:00 position.IGNITION - ENGINE COMPONENT LOCATIONIGNITION - FLIGHT COMPARTMENT COMPONENT LOCATIONSGeneralThese components which control the ignition system are in the flight compartment:1. Engine start switches2. Ignition selector switch3. Start levers.Component LocationsThe ignition selector switch and engine start switches are on the forward overhead panel (P5).The start levers are on the control stand.IGNITION - FLIGHT COMPARTMENT COMPONENT LOCATIONSIGNITION - IGNITION EXCITERPurposeThe ignition exciters supply power to spark igniters.GeneralThe ignition exciters change 115v ac to 20,000v dc. The output of the ignition exciter is 14.5 to 16 joules. The spark igniter uses this power to ignite the fuel/air mixture in the combustion chamber. Usually, only one ignition exciter per engine operates at a time.Physical DescriptionA 115v ac electrical connector attaches to the forward face of the ignition exciter. The ignition lead attaches to the aft face of the ignition exciter.The ignition exciters attach to the fan case with four shockmounts.Each ignition exciter has a bond jumper that attaches to the engine.Training Information PointWARNING: MAKE SURE THAT THE IGNITION EXCITERS ARE DE-ENERGIZED FOR A MINIMUM OF FIVE MINUTES BEFORE YOU START WORK ON THE IGNITION SYSTEM. THE IGNITION SYSTEM VOLTAGE IS DANGEROUSLY HIGH. DO NOT TOUCH THE ELECTRICAL CONTACTS. THE IGNITION EXCITERS CAN HAVE AN ELECTRICAL CHARGE EVEN WHEN NOT ENERGIZED. IF YOU DO NOT OBEY THIS STEP, INJURY TO PERSONS CAN OCCUR.IGNITION - IGNITION EXCITERIGNITION - DISTRIBUTION - IGNITION LEADS AND SPARK IGNITERSPurposeThe spark igniters supply an electrical spark to ignite the fuel/air mixture in the combustion chamber.The ignition leads transmit power from the ignition exciters to the spark igniters.General DescriptionEach spark igniter has its own ignition lead. Air goes around each ignition lead to decrease the temperature of the lead.Ignition Lead CoolingEach ignition lead goes into an air manifold at the 6:00 position at the aft end of the fan case. Booster air (low pressure compressor exhaust air), makes each ignition lead cool. The booster air goes into the air manifold and moves around the inner part of the ignition lead shroud. Booster air comes out of the spark igniter end of the ignition lead to cool the spark igniter.Spark IgnitersEach spark igniter installs into an adapter at the 4:00 and 8:00 positions on the engine. The spark igniter electrode is inside the combustion chamber.IGNITION - DISTRIBUTION - IGNITION LEADS AND SPARK IGNITERSIGNITION - FUNCTIONAL DESCRIPTIONGeneralThese are the components that operate the ignition system:1. Start levers2. Engine start switches3. Ignition selector switch4. EEC.The ac transfer bus 1 supplies 115v ac electrical power to the EEC for the left ignition exciter. The ac standby bus supplies 115v ac electrical power to the EEC for right ignition exciter. The left ignition exciter for engine 2 uses power from ac transfer bus 2. The right ignition exciter uses the ac standby bus.The EEC controls power to the ignition exciters. Input from the flight compartment components give manual control. The EEC has internal logic for automatic ignition system control.Manual ControlThe EEC and the CDS/DEUs monitor the position of these flight compartment components:1. Ignition selector switch2. Engine start switches3. Start levers.Each CDS/DEU sends a digital data signals to the EEC with switch position information.The EEC looks at the CDS/DEU digital data signal and the analog signal. The EEC compares the two signals. If the CDS/DEU 1 or CDS/DEU 2 digital data signal to the EEC logic stops, the EEC uses the analog signal as the flight compartment input.The EEC uses switch position data to control four internal EEC ignition on/off switches. These switches control the 115v ac power to the ignition exciters. Each EEC channel (A and B) controls one ignition on/off switch to each ignition exciter. Only one EEC channel is active at a time. Therefore, only one ignition on/off switch, for an ignition exciter, works at a time. The other EEC channel is in the standby mode. 115v ac power goes to the EEC when you move the start lever to the idle position. The 115v ac power goes through the start lever switches that are in the closed position.The ignition exciters receive power and supply 15,000 to 20,000v dc of electrical power to the spark igniters. The voltage goes across the electrodes of the spark igniter to make sparks.Flameout ProtectionThe EEC turns on both ignition systems of an engine automatically if one of these conditions are true:1. The engine start lever is in the IDLE position, the start switch is in the FLT position2. The engine start lever is in the IDLE position, start switches in GRD or CONT position, N2 less than idle and the airplane is in flight3. The engine start lever is in the IDLE position, engine speed decreases uncommanded or N2 is less than 57% and N2 is more than 50%. For this condition only, both ignition systems are energized for 30 secondsGUN 001-099, 101-122, 155-157The engine start lever is in the IDLE position, the airplane is in flight, start switch is in the OFF position, N2 speed is less than idle, and N2 speed is more than 5%.GUN 201-999The engine start lever is in the IDLE position, the airplane is in flight, start switch is in the AUTO position, N2 speed is less than idle, and N2 speed is more than 5%.GUN ALLThe EEC turns ignition off when these conditions are true:1. Engine start switches are not in a position that command ignition operation2. Hot start on the ground3. Wet start on the ground4. The engine start lever is in the IDLE position, airplane is on the ground, the engine completed a start, N2 speed goes less than 50% and EGT is more than the start limit5. Ignition system energized because of N2 less than idle or uncommanded decrease in N2 and engine speed goes back to normal.GUN 201-999Automatic IgnitionThe EEC turns on the selected igniter(s) when the flaps are not up or the engine anti-ice is selected on. To keep ignitors off when they are not needed or have no effect, more EEC logic is used to turn ignitors on when all of these conditions are true:1. Automatic ignition feature is enabled in the CDS software2. N2 is more than 20% (engine running)3. Burner pressure is less than the igniter firing limit pressure(175 psia)4. Thrust lever resolver angle is more than 50 degrees or the airplane is in-flight5. Engine anti-ice is selected on or wing flaps are not up and airplane altitude is less than 18,000 feet.GUN ALLIGNITION - FUNCTIONAL DESCRIPTIONIGNITION - OPERATIONGeneralThese are the flight compartment controls you use to operate the engine ignition:1. Start lever2. Ignition selector switch3. Engine start switch.Start LeverThe start lever controls ignition electrical power to the EEC. The EEC receives 115v ac power for ignition when the start lever is in the idle position.Ignition Selector SwitchThere are three ignition selector switch positions:1. IGN L (Left spark igniter)2. IGN R (right spark igniter)3. BOTH (both spark igniters).Engine Start SwitchThere are four engine start switch selection positions:1. GRD (ground start)2. OFF3. CONT (continuous ignition)4. FLT (flight).Engine Start Switch Position (GRD)The engine starter engages and turns the engine when you put the engine start switch to the GRD position. You supply ignition and fuel to the engine combustor when you move the start lever to the idle position.You use the GRD position to start the engine on the ground.See the engine starting chapter for more information.Engine Start Switch Position (OFF)Usually the igniters do not operate when the start switch is in the OFF position. However, the EEC turns on the ignition system automatically if the EEC sees a possible engine flameout condition. See the functional description page in this section for more information about this function.IGNITION - OPERATIONEngine Start Switch Position (AUTO)Usually the igniters do not operate when the start switch is in the AUTO position. However, the EEC turns on the ignition system automatically if the engine cowl anti-ice system is turned on or flaps are down. The EEC will turn on igniters if itsees a possible engine flameout condition. See the functional description page in this section for more information about this function.Engine Start Switch Position (CONT)The flight crew may turn the engine start switch to the CONT position at these times:1. Takeoff2. Approach3. Landing4. Bad WeatherThe spark igniters, as selected by the ignition selector switch, turn on and operate continuously when the switch is in this position.Engine Start Switch Position (FLT)Both spark igniters operate continuously when you turn the engine start switch to FLT position. The EEC does not use the ignition selector switch position information.IGNITION - OPERATIONIGNITION - TRAINING INFORMATION POINTGeneralThe control display unit (CDU) helps you do troubleshooting of the ignition system.You can also use the CDU to do a ground test of the ignition system.See the engine indicating chapter for more information.IGNITION - TRAINING INFORMATION POINT波音737点火系统1 （1）点火系统简介。2 点火系统总体描述。3 航空发动机点火系统的位置。4 点火励磁机。5 火花点火引线和点火器。6 点火系统功能描述。7 点火系统操作。8 训练信息要点。点火系统简介1综述1.（1）点火系统供应的电子火花燃烧在燃烧室中，每个发动机有两个点火系统且能独立工作。点火系统通常设有手动操作，当发动机电控设备观察到一个可能导致发动机熄火情况时点火系统会自动操作。2.在这些时候你会用到点火系统：（1）地面启动。（2）起飞和降落。（3）在飞行中（剧烈的震荡或坏天气）。（4）在飞行中启动。3.首字母的缩写：（1）CDS-共同显示系统。（2）CDU-控制显示器。（3）CONT-持续飞行状态。（4）DEU-单位显示电子。（5）EEC-发动机电控。（6）FLT-飞行中。 （7）FMC-飞行管理计算机。 （8）GRD-地面。 （9） IGN-点火系统。 (10) L-左边。 (11) R-右边。 机上和机上启动机 起飞和降落 地面启动点火介绍 4.点火系统介绍 有效性 点火系统总体描述 5.这些部件控制点火系统 (1)启动杠杆 (2)启动开关 (3)点火选择开关 (4)发动机电控启动杠杆控制点火系统功率到发动机电控，启动开关和点火选择开关提供输入到发动机电控。发动机电控用这些输入去提供能量到点火励磁机。点火励磁机提供能量去火花点火器。发动机启动系统也使用开关位置控制。 看发动机章节以获取更多信息。 6.电能1号发电机点火系统接受115V交流电压转移到1号母线和交流电压备用母线。发电机电控有内部开关控制115V交流电压到点火励磁机。点火励磁机改变115V交流电压输入到直流电压提供大约15000V到20000V电压给火花点火器。火花点火器提供火花到燃烧室。2号发电机点火系统接受的交流电压能量来自2号交流电压转换母线和交流电压备用母线。点火系统总体描述发电机点火部件的位置1.概述每一个发动机都有一个右点火系统和一个左点火系统，每个点火系统由这些部件组成：（1） 点火励磁机（2） 点火导线（3） 空气通道（4） 火花点火器2.部件的位置（1）点火励磁机在右边，较低的部位，风机箱的下面。（2）点火导线是从点火励磁机出发到火花点火器，在右边和左边的发动机。（3）空气通道绕着点火导线，开始于6:00钟方向然后通往点火器。（4）火花点火仅仅前往燃料通道，在4:00钟位置和8:00钟位置。发动机点火系统位置一综述：这些部件在飞行区域中控制点火系统。1. 发动机启动开关2. 点火选择开关3. 启动杠杆二组件的位置：点火开关和发动机启动开关都在机头前面的面板上（P5）。启动杠杆在控制站上。飞行中点火部件的位置目的：点火励磁机提供能量到火花点火器。综述：点火励磁机把115V交流电压转变成20000V直流电压。点火励磁机输出的能量在14.5到16焦耳之间。火花点火器利用这些能量在燃烧室中点燃燃料/汽液混合物。通常，一段时间只有一个点火励磁机引擎运作。物理描述：一个115V交流电压电接头连接到前面的点火励磁机。点火系统前端连接到尾部点火励磁机。点火励磁机附在风扇箱和四个防震架上。每个点火励磁机都有一个跳泵连接到发动机上的。警告：在你启动点火系统前至少五分钟确保点火励磁机是断电状态的。点火系统电压是高度危险的。不要接触电触头。点火励磁机可以具备电荷即使它不在通电状态。如果你不遵守这一步，可能出现人员受伤的情况。点火系统的点火励磁点火系统分布点火引线和火花点火器目的：火花点火器提供一种电火花在燃烧室中点燃燃料/汽液混合物。点火引线传输能量通过点火励磁到火花点火器。总体描述：每个火花点火器都有它自己的点火引线。空气沿着每个点火引线去降低导线的温度。点火导线冷却：每个点火导线进入一条空气管道在尾部风扇箱六点点钟位置。增压空气（低压压缩排气），使每根点火导线冷却。增压空气进入空气导管和围绕覆盖中心部分点火导线。增压空气流出火花点火器末端点火引线来冷却火花点火器。火花点火器：每个火花点火器安装在发动机一个适配器上4：00到8：00钟位置。火花点火器电极在燃烧室的内部。点火系统分布点火引线和火花点火器一综述：操作点火系统的部件：1. 启动杠杆2. 发动机启动开关3. 点火选择开关4. 发动机电控1号交流电压转换器提供115V交流电压到发动机电控器左边的点火励磁机。交流电压备用电机提供115V交流电压到发动机电控器右边的点火励磁机。2号发动机左边的点火励磁机用的能量来自于2号交流电压转换器。右边的点火励磁机用的能力来自于备用交流电压电机。发动机电控控制能量到点火励磁机，从飞行室部件输入给手动控制。发动机电控系统具有内部逻辑控制自动点火系统。二手动控制：发动机电控和共同显示系统/单位显示电子监控定位这些飞行区域部件：1. 点火选择开关2. 发动机启动开关3. 启动杠杆每个同显示系统/单位显示电子发送一个数字数据信息和开关位置信息到发动机电控。发动机电控接收到共同显示系统/单位显示电子的数字数据信号和模拟信号。发动机电控比较两种信号。如果共同显示系统/单位显示电子显示数字数据1或2的信号，发动机电控边停止，发动机电控采用模拟信号输入到飞行区域。发动机电控使用开关的位置数据来四个内部发动机电控点火系统开