47．为用于多转子发动机，已经研制成功了一种晶体式振动传 感器，它能提供更可靠的振动指示。在通向振动仪表的电路上 装了一个滤波器系统，这就有可能将所得的振动对照已知的频 率范围进行比较，由此能找到振动源的位置。一个多选择位置 的开关使驾驶员可以选出一个特定的区域，以获得该振动水平 的读数。
Controls and instrumentation
shaft failure occur, are but two examples. On some engine types, the fuel system is fitted with a control to enable the engine to be operated by manual throttling should a main fuel system failure occur. 49. In addition to a fire warning system (Part 14), a number of other audible or visual warning systems can be fitted to a gas turbine engine. These may be for low oil or fuel pressure, excessive vibration or overheating. Indication of these may be by warning light, bell or horn. A flashing light is used to attract the pilot's attention to a central warning panel (C.W.P.) where the actual fault is indicated. 50. Other instruments and lights warn the pilot of the selected position of the thrust reverser, the fan reverser or the afterburner variable nozzle, when applicable. Gauges also inform the pilot of such things as hydraulic pressure and flow and generator output, which are vital to the correct operation of the aircraft systems.
警告系统
48.警告系统用来 提供可能出现故障 或存在危险情况的 指示，以便于采取 措旋保护发动机或 飞机。虽然一台飞 机发动机的各种系 统在设计上只要可 能就设计成是“故 障安全”的，但有 时仍然装设附加的 安全装置。现仅举 两个例子，如万一 发生功率损失时的 螺旋桨自动顺桨， 和万一发生涡轮轴 损坏时自动关闭高 压燃油停车开关。 在某些型别发动机 上，在燃油系统中 装有一个控制器， 以便万一在主燃油 系统发生故障时， 保证发动机能够用 手动油门操作。 49.在燃气涡轮发 动机上，除了要装 失火警告系统(第 14章)之外，还可 能安装许多其它的 声响和目视警告系 统。这些系统可以 用于低滑油压力或 低燃油压力、过高 的振动或过热。这 些系统发出的指示 可以是告警灯、警 铃、或喇叭声。有 一个闪光灯用来吸 引驾驶员对中央警 告板的注意，该处 会指出实际的故 障。
图12-11 振动传感器及指示器
Fig. 12-11 Vibration transmitter and indicator.
Aircraft integrated data system 51. The aircraft integrated data system (A.I.D.S.) is an extension of the 'black box' aircraft accident data recorder. By monitoring and recording various engine parameters, either manually or automatically, it is possible to detect an incipient failure and thus prevent a hazardous situation arising.
52. Selected performance parameters may be recorded for trend analysis or fault detection (Part 24). Existing instruments are used, wherever possible, to provide the signals to a magnetic tape. Further instrumentation, recording air pressure from points throughout the engine, oil contamination, tank contents and scavenge oil temperature, may be provided as required for flight recording, 53. After each flight the magnetic tape is processed by computer and the results are analyzed. Any deviation from the normal condition will enable a fault to be identified and the necessary remedial action to be taken.
46. The vibration level recorded on the gauge is the sum total of vibration felt at the pick-up. A more accurate method differentiates between the frequency ranges of each rotating assembly and so enables the source of vibration to be isolated. This is particularly important on multi-spool engines. 47. A crystal-type vibration transmitter, giving a more reliable indication of vibration, has been developed for use on multi-spool engines. A system of filters in the electrical circuit to the gauge makes it possible to compare the vibration obtained against a known frequency range and so locate the vibration source. A multiple-selector switch enables the pilot to select a specific area to obtain a reading of the level of vibration.
Warning systems 48. Warning systems are provided to give an indication of a possible failure or the existence of a dangerous condition, so that action can be taken to safeguard the engine or aircraft. Although the various systems of an aircraft engine are designed wherever possible to 'fail safe1, additional safety devices are sometimes fitted. Automatic propeller feathering should a power loss occur, and automatic closing of the high pressure fuel shut-off cock should a turbine
Electronic indicating systems 54. Electronic indicating systems consolidate engine indications, systems monitoring, and crew alerting functions onto one or more cathode ray tubes (C.R.T.'s) mounted in the instrument panel. The information is displayed on the screen in the form of dials with digital readout and warnings, cautions and advisory messages shown as text. 143
50．其它仪表和灯光在适当的时候向驾驶员提出警告，这些警告有关反推 力，风扇反推力或加力燃烧室的可调喷口的选择位置。有些仪表提示驾驶 员这些情况：液压压力和流量，发电机输出功率等，这些对于飞机系统的 正确工作是极为重要的。
飞行翻译公司 www.aviation.cn 本文链接地址：劳斯莱斯喷气引擎－中英Rolls Royce The JET4
Controls and instrumentation
shaft failure occur, are but two examples. On some engine types, the fuel system is fitted with a control to enable the engine to be operated by manual throttling should a main fuel system failure occur. 49. In addition to a fire warning system (Part 14), a number of other audible or visual warning systems can be fitted to a gas turbine engine. These may be for low oil or fuel pressure, excessive vibration or overheating. Indication of these may be by warning light, bell or horn. A flashing light is used to attract the pilot's attention to a central warning panel (C.W.P.) where the actual fault is indicated. 50. Other instruments and lights warn the pilot of the selected position of the thrust reverser, the fan reverser or the afterburner variable nozzle, when applicable. Gauges also inform the pilot of such things as hydraulic pressure and flow and generator output, which are vital to the correct operation of the aircraft systems.
警告系统
48.警告系统用来 提供可能出现故障 或存在危险情况的 指示，以便于采取 措旋保护发动机或 飞机。虽然一台飞 机发动机的各种系 统在设计上只要可 能就设计成是“故 障安全”的，但有 时仍然装设附加的 安全装置。现仅举 两个例子，如万一 发生功率损失时的 螺旋桨自动顺桨， 和万一发生涡轮轴 损坏时自动关闭高 压燃油停车开关。 在某些型别发动机 上，在燃油系统中 装有一个控制器， 以便万一在主燃油 系统发生故障时， 保证发动机能够用 手动油门操作。 49.在燃气涡轮发 动机上，除了要装 失火警告系统(第 14章)之外，还可 能安装许多其它的 声响和目视警告系 统。这些系统可以 用于低滑油压力或 低燃油压力、过高 的振动或过热。这 些系统发出的指示 可以是告警灯、警 铃、或喇叭声。有 一个闪光灯用来吸 引驾驶员对中央警 告板的注意，该处 会指出实际的故 障。
图12-11 振动传感器及指示器
Fig. 12-11 Vibration transmitter and indicator.
Aircraft integrated data system 51. The aircraft integrated data system (A.I.D.S.) is an extension of the 'black box' aircraft accident data recorder. By monitoring and recording various engine parameters, either manually or automatically, it is possible to detect an incipient failure and thus prevent a hazardous situation arising.
52. Selected performance parameters may be recorded for trend analysis or fault detection (Part 24). Existing instruments are used, wherever possible, to provide the signals to a magnetic tape. Further instrumentation, recording air pressure from points throughout the engine, oil contamination, tank contents and scavenge oil temperature, may be provided as required for flight recording, 53. After each flight the magnetic tape is processed by computer and the results are analyzed. Any deviation from the normal condition will enable a fault to be identified and the necessary remedial action to be taken.
46. The vibration level recorded on the gauge is the sum total of vibration felt at the pick-up. A more accurate method differentiates between the frequency ranges of each rotating assembly and so enables the source of vibration to be isolated. This is particularly important on multi-spool engines. 47. A crystal-type vibration transmitter, giving a more reliable indication of vibration, has been developed for use on multi-spool engines. A system of filters in the electrical circuit to the gauge makes it possible to compare the vibration obtained against a known frequency range and so locate the vibration source. A multiple-selector switch enables the pilot to select a specific area to obtain a reading of the level of vibration.
Warning systems 48. Warning systems are provided to give an indication of a possible failure or the existence of a dangerous condition, so that action can be taken to safeguard the engine or aircraft. Although the various systems of an aircraft engine are designed wherever possible to 'fail safe1, additional safety devices are sometimes fitted. Automatic propeller feathering should a power loss occur, and automatic closing of the high pressure fuel shut-off cock should a turbine
Electronic indicating systems 54. Electronic indicating systems consolidate engine indications, systems monitoring, and crew alerting functions onto one or more cathode ray tubes (C.R.T.'s) mounted in the instrument panel. The information is displayed on the screen in the form of dials with digital readout and warnings, cautions and advisory messages shown as text. 143
50．其它仪表和灯光在适当的时候向驾驶员提出警告，这些警告有关反推 力，风扇反推力或加力燃烧室的可调喷口的选择位置。有些仪表提示驾驶 员这些情况：液压压力和流量，发电机输出功率等，这些对于飞机系统的 正确工作是极为重要的。
飞行翻译公司 www.aviation.cn 本文链接地址：劳斯莱斯喷气引擎－中英Rolls Royce The JET4
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