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公开(公告)号：US08506234B2
公开(公告)日：2013-08-13
申请号：US12768041
申请日：2010-04-27
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , F01D5/16 , F01D25/06
摘要： A duct wall of a fan casing of a gas turbine engine comprises an intake section and a containment casing, which are interconnected by bolts at flanges. An acoustic flutter damper is provided between the flanges to reduce or eliminate flutter arising in blades of the fan at certain important operating conditions. The damper provides flexibility at the connection between the intake section and the containment casing so that, in the event of detachment of a blade or a bladed fragment, the resulting deflection wave in the containment casing can be accommodated by displacement and/or deformation of the acoustic flutter damper, reducing the risk that the bolts will shear to allow the intake section and the containment casing to become detached from each other. The acoustic flutter damper may comprise a circumferential array of separate segments.
摘要翻译： 燃气涡轮发动机的风扇壳体的导管壁包括通过螺栓在凸缘处互连的进气部分和容纳壳体。 在凸缘之间提供声波阻尼器以减少或消除在某些重要操作条件下风扇叶片中产生的颤动。 阻尼器在进气部分和收容壳体之间的连接处提供了灵活性，使得在叶片或叶片碎片脱离的情况下，容纳壳体中产生的偏转波可以通过位移和/或变形 声波阻尼器，减少了螺栓剪切的风险，使进气段和密封套彼此脱离。 声波阻尼器可以包括分开的段的圆周阵列。
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公开(公告)号：US06932560B2
公开(公告)日：2005-08-23
申请号：US10277133
申请日：2002-10-22
申请人： Richard V Brooks
发明人： Richard V Brooks
CPC分类号： F01D21/14 , F01D21/04 , Y02T50/671
摘要： A gas turbine engine (10) comprises a fan rotor (26) having a plurality of fan blades (24) and an apparatus (34) for detecting an impact on the fan blades (24). The apparatus (34) comprises speed sensors (48,48B) arranged to measure the speed of rotation of the fan rotor (26) and the turbine rotor (58) and to produce speed signals. A processor unit (40) analyses the speed signals to determine the angle of twist between the ends of the fan rotor (26). The processor unit (40) is arranged to analyse the angle of twist to determine if the angle of twist of the fan rotor (40) oscillates by more than a predetermined level from an average level. The processor unit (40) is arranged to produce a signal indicative of an impact to at least one of the fan blades (24) if the angle of twist oscillates by more than the predetermined level and sends a signal to an indicator device (44,46).
摘要翻译： 燃气涡轮发动机（10）包括具有多个风扇叶片（24）的风扇转子（26）和用于检测对风扇叶片（24）的冲击的装置（34）。 设备（34）包括速度传感器（48,48B），其布置成测量风扇转子（26）和涡轮机转子（58）的旋转速度并产生速度信号。 处理器单元（40）分析速度信号以确定风扇转子（26）的端部之间的扭转角度。 处理器单元（40）被布置成分析扭转角以确定风扇转子（40）的扭转角是否从平均水平振荡超过预定水平。 如果扭转角度振荡超过预定水平，则处理器单元（40）被布置成产生指示对至少一个风扇叶片（24）的冲击的信号，并将信号发送到指示器装置（44， 46）。
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公开(公告)号：US06659712B2
公开(公告)日：2003-12-09
申请号：US10173116
申请日：2002-06-18
IPC分类号： F01D2114
CPC分类号： G01M15/12 , F01D17/04 , F01D17/06 , F01D21/003 , F01D21/04 , F01D21/14 , F05D2270/301 , F05D2270/304 , F05D2270/52 , G01M15/14 , Y02T50/671
摘要： A gas turbine engine (10) comprises a fan rotor (26) having a plurality of fan blades (24) and an apparatus (34) for detecting damage to the fan blades (24). The apparatus (34) comprises a transducer (36) arranged to detect the pressure in the gas flow around the fan blades (34) and to produce a pressure signal. A speed sensor (48) is arranged to measure the speed of rotation of the fan rotor (26) and to produce a speed signal. A processor unit (40) analyses the pressure signal and the speed signal to detect changes in the amplitude of the pressure signal, which occur at multiples of the rotational frequency of the fan rotor (24). The changes indicate differences in pressure between the gas flow around a damaged fan blade (24) and the gas flow around the remainder of the fan blades (24). The processor unit (40) sends a signal indicative of damage to a fan blade (24), if the difference in pressure is above the predetermined level, to an indicator device (44, 46).
摘要翻译： 燃气涡轮发动机（10）包括具有多个风扇叶片（24）的风扇转子（26）和用于检测对风扇叶片（24）的损坏的装置（34）。 设备（34）包括被设置成检测围绕风扇叶片（34）的气流中的压力并产生压力信号的换能器（36）。 速度传感器（48）布置成测量风扇转子（26）的旋转速度并产生速度信号。 处理器单元（40）分析压力信号和速度信号，以检测以风扇转子（24）的转数的倍数发生的压力信号的幅度变化。 这些变化表示损坏的风扇叶片（24）周围的气体流与围绕其余风扇叶片（24）的气流之间的压力差异。 处理器单元（40）向指示器装置（44,46）发送指示对风扇叶片（24）的损坏的信号（如果压力差超过预定水平）。
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