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1. 发明授权

US06353790B1 Gas turbine aeroengine control system 有权
标题翻译：燃气轮机航空发动机控制系统
公开(公告)号：US06353790B1
公开(公告)日：2002-03-05
申请号：US09636751
申请日：2000-08-11
申请人： Sadachika Tsuzuki
发明人： Sadachika Tsuzuki
IPC分类号： F02K306
CPC分类号： F02C9/263 , F05D2260/84 , F05D2270/54 , G05B9/02
摘要： In a control system for a gas turbine aero engine, the control system (ECU) is configured as a dual control system comprising two channels, Ch-A and Ch-B. Ch-A has two CPUs which conduct calculations separately based on the sensor outputs and one of the CPUs compares the results and if they coincide, the CPU sends the result of the other CPU to the FCU. If not, one of the CPUs determines that an abnormality arises in Ch-A and sends a result to Ch-B. Ch-B is constituted as a standby channel having only one CPU whose operation is monitored by a simple watchdog timer circuit. This enhances CPU failure detection with a relatively simple configuration, and eliminates the need for provision of an overspeed protector.
摘要翻译：在用于燃气轮机航空发动机的控制系统中，控制系统（ECU）被配置为包括两个通道Ch-A和Ch-B的双重控制系统。 Ch-A有两个CPU根据传感器输出分别执行计算，其中一个CPU比较结果，如果它们相符，CPU将其他CPU的结果发送到FCU。如果不是，其中一个CPU确定Ch-A中出现异常，并将结果发送给Ch-B。 Ch-B构成为仅具有一个CPU的备用信道，其操作由简单的看门狗定时器电路监视。这可以通过相对简单的配置来增强CPU故障检测，并且不需要提供超速保护器。

2. 发明授权

US06666018B2 Combined cycle pulse detonation turbine engine 有权
标题翻译：联合循环脉冲爆震涡轮发动机
公开(公告)号：US06666018B2
公开(公告)日：2003-12-23
申请号：US10328679
申请日：2002-12-23
申请人： Lawrence Butler , James Edward Johnson , Lawrence Wayne Dunbar
发明人： Lawrence Butler , James Edward Johnson , Lawrence Wayne Dunbar
IPC分类号： F02K306
CPC分类号： F02K3/075 , F02K7/02 , F02K7/06 , F02K7/075
摘要： A pulse detonation system for a turbofan engine including a fan assembly and a turbine sub-system, which includes at least one turbine, is configured to create a temperature rise and a pressure rise within the turbofan engine and to generate thrust for the turbofan engine. The pulse detonation system includes a pulse detonation core assembly comprising at least one detonation chamber configured to detonate a fuel mixture. The pulse detonation core assembly is positioned between the fan assembly and the turbine sub-system.
摘要翻译：包括风扇组件和包括至少一个涡轮机的涡轮机子系统的涡轮风扇发动机的脉冲爆震系统构造成在涡轮风扇发动机内产生温度升高和压力上升，并产生用于涡轮风扇发动机的推力。脉冲爆震系统包括脉冲爆震核心组件，其包括至少一个被配置为引爆燃料混合物的爆震室。脉冲爆震芯组件位于风扇组件和涡轮机子系统之间。

3. 发明授权

US06742324B2 Methods and apparatus for supporting variable bypass valve systems 有权
标题翻译：支持可变旁通阀系统的方法和装置
公开(公告)号：US06742324B2
公开(公告)日：2004-06-01
申请号：US10243232
申请日：2002-09-13
申请人： Kenneth Alan Bachelder , Donald James Welty
发明人： Kenneth Alan Bachelder , Donald James Welty
IPC分类号： F02K306
CPC分类号： F01D17/162 , F01D17/105 , F04D27/0215 , F04D27/023 , F05D2260/50 , Y02T50/671
摘要： A method enables a gas turbine engine variable bypass valve system to be assembled. The method comprises positioning a unison ring circumferentially within the gas turbine engine such that the unison ring is radially outward from a structural frame, coupling at least one bellcrank to the unison ring, such that the unison ring is radially supported only by said at least one bellcrank, and coupling the at least one bellcrank to a bellcrank support that is coupled to the structural frame.
摘要翻译：一种方法能够组装燃气涡轮发动机可变旁通阀系统。该方法包括在燃气涡轮发动机内圆周地定位协调环，使得协调环从结构框架径向向外，将至少一个曲拐联接到协调环上，使得协调环仅由所述至少一个曲拐，并且将至少一个曲拐联接到耦合到结构框架的曲拐支撑件。

4. 发明授权

US06378293B1 Gas turbine engine bearing arrangement 有权
标题翻译：燃气轮机发动机轴承布置
公开(公告)号：US06378293B1
公开(公告)日：2002-04-30
申请号：US09506570
申请日：2000-02-18
申请人： Ian C D Care , Arnold C Newton
发明人： Ian C D Care , Arnold C Newton
IPC分类号： F02K306
CPC分类号： F01D15/10 , F01D25/16 , F02C7/06 , F05D2220/50 , F05D2240/515 , F16C32/0474 , F16C37/005 , F16C2360/23 , Y02T50/671
摘要： A gas turbine engine (10) is provided with a plurality of shafts (18, 19, 20) interconnecting its compressor portions (11, 12, 13) with its turbine portions (15, 16, 17). Each shaft (18, 19, 20) is supported in the hotter part of the engine by electromagnetic bearings (26, 28, 32) and by rolling element bearings (24, 27, 29, 31, 33) in the remainder of the engine (10). The arrangement provides a simplified liquid lubrication system for the rolling element bearings (24, 27, 29, 31, 33) which reduces the likelihood of lubricant thermal degradation of the lubricant.
摘要翻译：燃气涡轮发动机（10）设置有多个将其压缩机部分（11,12,13）与其涡轮部分（15,16,17）互连的轴（18,19,20）。每个轴（18,19,20）通过电磁轴承（26,28,32）和发动机的其余部分中的滚动元件轴承（24,27,29,31,33）支撑在发动机的较热部分中（10）。该装置为滚动元件轴承（24,27,29,31,33）提供了简化的液体润滑系统，其减少润滑剂的润滑剂热降解的可能性。

5. 发明授权

US06799416B2 Device for supporting and recentering the shaft of a turbojet fan after uncoupling 有权
标题翻译：拆卸后支撑和重新安装涡轮喷气风扇的轴的装置
公开(公告)号：US06799416B2
公开(公告)日：2004-10-05
申请号：US10387392
申请日：2003-03-14
申请人： Daniel Plona , Patrick Morel
发明人： Daniel Plona , Patrick Morel
IPC分类号： F02K306
CPC分类号： F01D21/045 , F01D25/16 , F05B2260/3011 , F05D2260/30 , F16C19/52 , F16C2360/23
摘要： The invention provides a device for supporting and recentering a shaft (2) after decoupling. The device comprises an annular support (4) surrounding the shaft (2), a bearing (5) secured to the annular support (4) and having an inner ring (9) which is spaced apart from the shaft by clearance J. The inner ring (9) has two webs or tenons (14a, 14b) that are normally held to the periphery of two troughs (16a, 16b) carried by the shaft (2). Two sets of balls (28a, 28b) normally bear against the bottoms of indentations (25, 26) formed facing one another in the adjacent radial walls of the troughs (16a, 16b) and of the inner ring (9). Resilient means (26) tend to urge the troughs (16a and 16b) towards each other. In the event of the webs or tenons (14a, 14b) breaking due to a large unbalance, the balls (28a, 28b) roll on the walls of the indentations (25, 26) and move the troughs (16a, 16b) apart from each other. The resilient mans (20) tend to bring the balls (28a, 28b) back towards the bottoms of the indentations and to recenter the shaft (2) relative to the inner ring (9).
摘要翻译：本发明提供一种用于在解耦之后支撑和重新调节轴（2）的装置。该装置包括围绕轴（2）的环形支撑件（4），固定到环形支撑件（4）并具有内部环（9）的轴承（5），该内圈与轴间隔开。环（9）具有通常保持在由轴（2）承载的两个槽（16a，16b）的周边的两个腹板或榫头（14a，14b）。两组球（28a，28b）通常抵靠在槽（16a，16b）和内圈（9）的相邻径向壁中彼此面对形成的凹陷（25,26）的底部。弹性装置（26）趋向于朝向彼此推动槽（16a和16b）。在由于大的不平衡导致腹板或榫头（14a，14b）断裂的情况下，滚珠（28a，28b）在压痕（25,26）的壁上滚动并使槽（16a，16b）从彼此。弹性杆（20）倾向于将球（28a，28b）返回到凹陷的底部并且相对于内圈（9）更换轴（2）。

6. 发明授权

US06681559B2 Thrust reverser position determination system and method 有权
标题翻译：推力反向器位置确定系统及方法
公开(公告)号：US06681559B2
公开(公告)日：2004-01-27
申请号：US10199020
申请日：2002-07-19
申请人： Andrew T. Johnson
发明人： Andrew T. Johnson
IPC分类号： F02K306
CPC分类号： F02K1/72 , F02K1/763 , F05D2200/11 , F05D2270/051 , F05D2270/62 , F05D2270/66
摘要： An improved jet engine thrust reverser that includes a sensor to determined the rotational position of a motor. The system includes an actuator, a motor, motor position sensor, and an electronic control unit. The electronic control unit converts the rotational position of the motor to thrust reverser system using, for example, a summation algorithm and reset logic. The summation algorithm incrementally calculates absolute position of the thrust reverser from the sensed motor rotational position.
摘要翻译：一种改进的喷气发动机推力反向器，其包括用于确定电动机的旋转位置的传感器。该系统包括致动器，马达，马达位置传感器和电子控制单元。电子控制单元使用例如求和算法和复位逻辑将电动机的旋转位置转换成推力反向器系统。求和算法从感测到的电动机旋转位置递增地计算推力反向器的绝对位置。

7. 发明授权

US06508055B2 Variable mode jet engine—suitable for STOVL 失效
标题翻译：可变模式喷气发动机 - 适用于STOVL
公开(公告)号：US06508055B2
公开(公告)日：2003-01-21
申请号：US09765700
申请日：2001-01-22
申请人： Adrian Alexander Hubbard
发明人： Adrian Alexander Hubbard
IPC分类号： F02K306
CPC分类号： B64C29/0066 , F02K1/566 , F02K1/64 , F02K3/075
摘要： This jet engine comprises a complete low bypass turbofan unit 1 including secondary fan unit 2 and engine core, ahead of which sits a larger diameter main fan unit 3 driven from the front of the secondary fan via a long drive shaft 4. A center portion of the main fan feeds the secondary fan via long central duct 5. The outer portion of the main fan is ducted into a split exhaust plenum chamber 6. This chamber has thrust vectoring exhaust mechanisms 7 immediately attached to each side, and then each side then feeds a thrust splitter 10, and then feeds to variable area outer ducting 8, using double-hinged inner and outer doors 9. Both outer ducts rejoin the central duct downstream in a second plenum chamber 11 just ahead of the secondary fan. Between this chamber and secondary fan is an intercooler 12.
摘要翻译：该喷气发动机包括一个完整的低旁路涡扇风扇单元1，其包括二次风扇单元2和发动机机芯，其前面设有一个较大直径的主风扇单元3，该主风扇单元3经由长驱动轴4从次风扇的前部驱动。主风扇通过长的中心管道5供给二次风扇。主风扇的外部部分被引导到分流排气增压室6中。该室具有立即附接到每一侧的推力向量排气机构7，然后每侧进料推力分配器10，然后使用双铰链的内门9和外门9进给可变区外管8.两个外管在第二增压室11的下游重新连接在次风扇前面的第二增压室11中。在该室和二次风扇之间是中间冷却器12。

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