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101. 发明授权

US4005575A Differentially geared reversible fan for ducted fan gas turbine engines 失效
标题翻译：用于管道式风机燃气涡轮发动机的差速齿轮可逆风扇
公开(公告)号：US4005575A
公开(公告)日：1977-02-01
申请号：US609931
申请日：1975-09-03
申请人： Alexander Scott , Peter Eric Peck
发明人： Alexander Scott , Peter Eric Peck
IPC分类号： F02C9/18 , F02K3/04 , F02C3/06
CPC分类号： F02C9/18 , F02K3/04
摘要： A ducted fan gas turbine engine comprises a pair of turbines in flow series which are contra-rotating and which drive shafts which in turn drive into an epicyclic gear. The output from the epicyclic gear drives a fan which normally provides forward thrust from the engine. The fan can be made to rotate in the opposite direction to provide reverse thrust by varying the relative speeds of rotation of the two turbines by bleeding working fluid from between them.
摘要翻译：管式风机燃气涡轮发动机包括一对涡轮机，它们是反向旋转的，并且驱动轴又被驱动到行星齿轮中。来自行星齿轮的输出驱动通常提供来自发动机的向前推力的风扇。可以使风扇沿相反方向旋转以通过从它们之间流出工作流体来改变两个涡轮机的旋转的相对速度来提供反向推力。

102. 发明授权

US3922852A Variable pitch fan for gas turbine engine 失效
标题翻译：燃气轮机发动机变桨距风机
公开(公告)号：US3922852A
公开(公告)日：1975-12-02
申请号：US40722273
申请日：1973-10-17
申请人： GEN ELECTRIC
发明人： DRABEK STEPHEN
IPC分类号： F02K3/04 , B64C11/32 , F01D7/00 , F02C3/06 , B63H3/04 , F02K3/06
CPC分类号： F01D7/00 , F05D2220/36 , F05D2260/74 , F05D2260/76 , Y02T50/671 , Y02T50/673
摘要： A variable pitch fan together with actuation apparatus are provided for a gas turbine engine of the bypass type. The actuation apparatus includes at least one linear actuator which remains in fixed connection relative to the engine static structure and interconnects to a helical cam means on board the fan rotor through a preloaded thrust bearing. The linear movement of the actuator is converted into angular movement by the helical cam means whereby the angular movement can be applied to all the fan blades to simultaneously vary their pitch.
摘要翻译：为旁路式燃气涡轮发动机提供了可变节距风扇和致动装置。致动装置包括至少一个线性致动器，其相对于发动机静态结构保持固定连接并且通过预加载的推力轴承与在风扇转子上的螺旋形凸轮装置相互连接。致动器的线性运动通过螺旋凸轮装置转换成角运动，由此可以将角运动施加到所有风扇叶片上以同时改变它们的间距。

103. 发明授权

US3898799A Device for bleeding-off compressor air in turbine jet engine 失效
标题翻译：涡轮喷气发动机排出压缩机空气的装置
公开(公告)号：US3898799A
公开(公告)日：1975-08-12
申请号：US40154473
申请日：1973-09-27
申请人： MTU MUENCHEN GMBH
发明人： POLLERT WOLFGANG , KRAFT ECKHARD , PENNIG GREGOR
IPC分类号： F04D27/02 , F02C3/06
CPC分类号： F04D27/0215 , F04D27/023
摘要： Apparatus for bleeding off compressor air in a turbine engine of the type having a plurality of serially arranged compressors. The apparatus includes a first annular chamber communicated directly with compressor air from one of the compressors and a second annular chamber communicated directly with atmosphere or with a bypass duct of the engine. Arranged in between the first and second chambers are internal and external rings slideable with respect to one another with the external ring having openings which are controlled by the position of the internal ring. Actuating means, including a radially extending actuating shaft and a pair of pivotally connected levers interconnecting the internal ring and the actuating shaft are provided for moving the internal ring with respect to the external ring. The internal ring is provided with guide slots and the external ring is provided with guide rollers for guiding relative movement of the internal and external rings such that the internal ring simultaneously moves both circumferentially and axially during adjustments thereof.
摘要翻译：在具有多个连续排列的压缩机的类型的涡轮发动机中排出压缩机空气的装置。该装置包括一个直接与压缩机空气连通的第一环形室和一个直接与大气连通或与发动机旁路管道连通的第二环形室。排列在第一和第二腔室之间的内环和外环可以相对于彼此滑动，外环具有由内环的位置控制的开口。提供包括径向延伸的致动轴和互连内环和致动轴的一对枢转连接的杠杆的致动装置，用于相对于外环移动内圈。内环设置有引导槽，并且外环设置有用于引导内环和外环的相对运动的引导辊，使得内环在其调节期间同时沿周向和轴向移动。

104. 发明授权

US3852958A Stall protector system for a gas turbine engine 失效
标题翻译：用于气体涡轮发动机的保护器系统
公开(公告)号：US3852958A
公开(公告)日：1974-12-10
申请号：US40165073
申请日：1973-09-28
申请人： GEN ELECTRIC
发明人： ADAMS M , DUNCAN V
IPC分类号： F02C9/28 , F02C9/32 , F04D27/02 , F02C3/06 , F02C9/04
CPC分类号： F04D27/0207 , F02C9/32
摘要： A stall protector system is provided for a gas turbine engine wherein the compressor pressure is measured, differentiated, and compared with a reference indicative of the maximum rate at which the compressor pressure decreases during normal operation. When the actual rate of decrease of compressor pressure exceeds the reference rate, then the signal is integrated and compared with a second reference indicative of the minimum change in compressor pressure before a stall occurs. If the second reference is exceeded, the fuel flow to the combustor is automatically restricted.
摘要翻译：提供了一种用于燃气涡轮发动机的失速保护器系统，其中压缩机压力被测量，微分，并且与在正常操作期间压缩机压力降低的最大速率的参考值进行比较。当压缩机压力的实际降低速率超过参考速率时，信号被积分，并与第二个参考值进行比较，表示压缩机压力发生前的最小变化。如果超过第二个参考值，则自动限制燃烧到燃烧器的燃料。

105. 发明授权

US3777489A Combustor casing and concentric air bleed structure 失效
标题翻译： COMBUSTOR铸造和集中空气结构
公开(公告)号：US3777489A
公开(公告)日：1973-12-11
申请号：US3777489D
申请日：1972-06-01
申请人： GEN ELECTRIC
发明人： GEORGE A , JOHNSON K , KEPF P
IPC分类号： F04D29/52 , F01D9/06 , F02C3/06 , F02C6/08 , F02C7/047 , F02C9/18 , F02C3/12 , F02K3/06
CPC分类号： F02C9/18 , F01D9/065 , F02C6/08 , F04D29/545 , Y02T50/671
摘要： Combustor casing and bleed structure provides a concentric flow path for compressor discharge and intermediate stage air from a turbofan engine compressor to an outer cowling defining the fan flow path. Concentric tubes are respectively mounted to a support cone, which includes a plurality of outlet guide vanes, and to an outer casing, which partially defines the fan flow path. External piping is thus limited to the concentric tubes and potential losses due to interference with the fan flow are avoided.
摘要翻译：燃烧器套管和排气结构提供用于压缩机排放的同心流动路径和从涡轮风扇发动机压缩机到限定风扇流动路径的外部整流罩的中间阶段空气。同心管分别安装在支撑锥体上，支撑锥体包括多个出口导向叶片，以及部分地限定风扇流动路径的外壳。因此，外部管道被限制到同心管，并且避免了由于与风扇流动的干扰而引起的潜在损失。

106. 发明授权

US3623317A Gas turbine for low heating value gas 失效
标题翻译：用于低加热气体的气体涡轮机
公开(公告)号：US3623317A
公开(公告)日：1971-11-30
申请号：US3623317D
申请日：1970-06-30
申请人： STRUTHERS ENERGY SYSTEMS INC
发明人： FOSTER-PEGG RICHARD W
IPC分类号： F02C3/22 , F02C3/06
CPC分类号： F02C3/22
摘要： A GAS TURBINE HAS A COMPRESSOR, A COMBUSTION CHAMBER, AND A TURBINE WHICH DRIVES THE COMPRESSOR AND PROVIDES ADDITIONAL SHAFT WORK, AIR AND LOW HEATING VALVE GAS BEING INTRODUCED A GIVEN CIRCUMFERENTIALLY DISPOSED LOCATIONS AT THE COMPRESSOR INTAKE AND BEING WITHDRAWN AT CORRESPONDING CIRCUMFRENTIALLY DISPOSED LOCATIONS AT THE COMPRESSOR EXHAUST, ONE OF SAID LOCATIONS AT THE COMPRESSOR EXHAUST PROVIDING FUEL RICH AIR INTRODUCED INTO AND BURNED IN THE COMBUSTION CHAMBER WITH ADDITIONAL AIR FROM THE COMPRESSOR INTRODUCED THEREAFTER, PRODUCTS OF COMBUSTION FROM THE COMBUSTION CHAMBER DRIVING SAID TURBINE.

107. 发明授权

US3620011A Compressor pressure limiter for gas turbine engine 失效
标题翻译：压缩机气压发动机压力限制
公开(公告)号：US3620011A
公开(公告)日：1971-11-16
申请号：US3620011D
申请日：1970-03-25
申请人： UNITED AIRCRAFT CORP
发明人： URBAN LOUIS A , FORTMANN WILLIAM E
IPC分类号： F02C9/32 , F02C9/08 , F02C3/06 , F02C3/24
CPC分类号： F02C9/32
摘要： COMPRESSOR DISCHARGE PRESSURE OF A GAS TURBINE ENGINE LIMITED BY CLOSING OFF THE FUEL MELTERING VALVE AT A VELOCITY DEPENDENT ON THE MAGNITUDE BY WHICH THE COMPRESSOR DISCHARGE PRESSURE EXCEEDS A DESIRED VALVE. IN THIS MOLE THE FUEL CONTROL BECOMES AN INTEGRATING DEVICE

AND STEADILY STATE IS ACHIEVED BY CLOSING THE LOOP ON COMPRESSOR DISCHARGE PRESSURE THROUGH THE ENGINE. THE LIMIT MAY BE RESET BY THE POWER LEVER AND MAY BE ALITUDE PRESSURE OR TEMPERATURE BIASED.

108. 发明授权

US3603082A Combustor for gas turbine having a compressor and turbine passages in a single rotor element 失效
标题翻译：用于单个转子元件的压缩机和涡轮机通风机的燃气轮机
公开(公告)号：US3603082A
公开(公告)日：1971-09-07
申请号：US3603082D
申请日：1970-02-18
申请人： CURTISS WRIGHT CORP
发明人： SNEEDEN RALPH J , BROOKES NEIL R , WATTS HARGUS
IPC分类号： F02C3/045 , F02K3/068 , F23R3/52 , F02C3/06 , F02K3/06
CPC分类号： F02K3/068 , F02C3/045 , F23R3/52 , Y02T50/671
摘要： In a gas turbine engine having a compressor and turbine passages in a single rotor element, a combustor of annual, toroidal configuration comprises a segmentally constructed liner defining a combustion chamber providing a flow path of at least about 180* and spaced from a housing or shroud to define a diffusing combustion air supply passageway communicating with the annular outlet means of the compressor. The combustion chamber is provided with inlet means to receive air from the diffusing passageway and an outlet in communication with the turbine nozzles formed between next adjacent stator blades. Each of the stator blades has passage means therethrough to communicate the diffusing passageway with the combustion chamber inlet means to pass combustion air from the diffusing passageway to the latter and effect cooling of the stator vanes and heating of the combustion air. The liner has slip joints so constructed and arranged that unrestrained expansion and construction can occur while maintaining a constant diffusing passageway dimensional characteristics.

109. 发明授权

US3546879A Two-shaft turbine with means for controlling relative shaft rotation 失效
标题翻译：双轴涡轮机，用于控制相对轴转动
公开(公告)号：US3546879A
公开(公告)日：1970-12-15
申请号：US3546879D
申请日：1968-08-19
申请人： EATON YALE & TOWNE
发明人： HASS DAVID P
IPC分类号： F02C3/113 , F02C7/36 , F02C3/06
CPC分类号： F02C3/113 , F02C7/36

110. 发明授权

US3524318A Gas turbine power plants having axialflow compressors incorporating contrarotating rotors 失效
标题翻译：具有同轴转子的轴流式压缩机的气体涡轮发电厂
公开(公告)号：US3524318A
公开(公告)日：1970-08-18
申请号：US3524318D
申请日：1968-12-11
申请人： SNECMA
发明人： BAUGER LOUIS JULES , BOUILLER JEAN GEORGES , GARNIER MICHEL ROBERT , LACROIX ARMAND JEAN-BAPTISTE
IPC分类号： F02C3/067 , F04D19/02 , F02C3/06 , F02K3/06
CPC分类号： F04D19/026 , F02C3/067 , F04D19/024

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