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公开(公告)号：US5369954A
公开(公告)日：1994-12-06
申请号：US65307
申请日：1993-05-24
申请人： Alan R. Stuart
发明人： Alan R. Stuart
摘要： A turbofan engine bypass and exhaust system has a double-hoop configuration in which a fan exhaust passageway comprises shells of a constant circular contour to resolve air pressure induced stresses and increase in bypass passageway area asymmetrically in the horizontal direction without substantially increasing the overall engine height.
摘要翻译： 涡轮风扇发动机旁通和排气系统具有双箍结构，其中风扇排气通道包括恒定圆形轮廓的壳体以分解空气压力引起的应力并且在水平方向上不对称地增加旁路通道面积，而基本上不增加总体发动机高度 。
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公开(公告)号：US5317877A
公开(公告)日：1994-06-07
申请号：US923676
申请日：1992-08-03
申请人： Alan R. Stuart
发明人： Alan R. Stuart
CPC分类号： F02C7/224 , F02C7/185 , Y02T50/675
摘要： A gas turbine engine having a compressor and an air-cooled turbine is provided with a cooling system for decreasing the temperature of the turbine cooling air. A heat exchanger, mounted on the compressor casing, receives a portion of the pressurized air which is bled from the compressor. A heat sink medium is pumped through the heat exchanger into heat exchange relationship with the pressurized air, thereby cooling the air. The cooled air is then further pressurized and routed to and circulated through the turbine rotor blades to provide improved cooling thereof. The intercooling of the compressor bleed air permits a reduction in the quantity of compressor air required for turbine rotor blade cooling or allows an increase in turbine entry temperature and thus provides an improvement in engine power and performance. In the case where the heat sink medium is engine fuel, the heat extracted from the compressor bleed air is returned to the engine operating cycle in the form of heated engine fuel.
摘要翻译： 具有压缩机和空气冷却涡轮机的燃气涡轮发动机设置有用于降低涡轮机冷却空气的温度的冷却系统。 安装在压缩机壳体上的热交换器接收从压缩机排出的一部分加压空气。 散热介质通过热交换器被泵送到与加压空气的热交换关系，从而冷却空气。 然后冷却的空气被进一步加压并且被引导并通过涡轮机转子叶片循环，以提供改进的冷却。 压缩机排放空气的中间冷却允许减少涡轮转子叶片冷却所需的压缩机空气量，或允许增加涡轮进入温度，从而提高发动机功率和性能。 在散热介质是发动机燃料的情况下，从压缩机排放的空气中抽取的热量以加热的发动机燃料的形式返回到发动机运转循环。
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公开(公告)号：US4790133A
公开(公告)日：1988-12-13
申请号：US166749
申请日：1988-03-10
申请人： Alan R. Stuart
发明人： Alan R. Stuart
摘要： A gas turbine engine comprising a core gas generator engine for generating combustion gases, an additional power turbine, an additional fan section, and a booster compressor is disclosed. The power turbine includes first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively. The fan section includes a first fan blade row connected to the first drive shaft and a second fan blade row connected to the second drive shaft. The booster compressor includes a first compressor blade row connected to the first drive shaft and a second compressor blade row connected to the second drive shaft.
摘要翻译： 公开了一种燃气涡轮发动机，其包括用于产生燃烧气体的核心气体发生器发动机，附加动力涡轮机，附加风扇部分和增压压缩机。 动力涡轮机包括分别有效地旋转第一和第二驱动轴的第一和第二反向旋转涡轮叶片排。 风扇部分包括连接到第一驱动轴的第一风扇叶片排和连接到第二驱动轴的第二风扇叶片排。 增压压缩机包括连接到第一驱动轴的第一压缩机叶片排和连接到第二驱动轴的第二压缩机叶片排。
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公开(公告)号：US5927644A
公开(公告)日：1999-07-27
申请号：US947143
申请日：1997-10-08
申请人： Joe E. Ellis , Alan R. Stuart
发明人： Joe E. Ellis , Alan R. Stuart
CPC分类号： F02C7/20 , B64D27/26 , B64D2027/266 , Y02T50/44
摘要： An aircraft engine mount includes a mounting platform fixedly joinable to an aircraft pylon, and a cooperating mounting ring fixedly joinable to an aircraft engine. The platform includes a pair of spaced apart lugs defining therebetween a failsafe slot. The mounting ring includes an inner flange fixedly joinable to the engine, and an outer flange extending from the inner flange into the failsafe slot. A pair of side links are pivotally joined to the outer flange and at least one of the lugs to carry loads therebetween. A failsafe pin extends across the failsafe slot and is fixedly joined to the lugs. A clearance hole is provided in the outer flange for receiving the failsafe pin and providing a failsafe alternate loadpath between the mounting ring and platform upon failure of the links to carry loads.
摘要翻译： 飞机发动机支架包括固定地连接到飞机塔架的安装平台和可固定地连接到飞行器发动机的协作安装环。 平台包括一对在其间限定故障安全槽的间隔开的凸耳。 安装环包括固定地连接到发动机的内凸缘和从内凸缘延伸到故障安全槽中的外凸缘。 一对侧连杆枢转地连接到外凸缘和至少一个凸耳以在其间承载载荷。 故障安全销延伸穿过故障安全槽，并牢固地连接到凸耳。 在外部法兰中设置有一个间隙孔，用于接收故障保护销，并且在连杆承载负载故障时，在安装环和平台之间提供故障安全的交替负载路径。
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公开(公告)号：US5190441A
公开(公告)日：1993-03-02
申请号：US566203
申请日：1990-08-13
CPC分类号： F02K3/072 , B64C11/008 , B64C11/48 , B64C23/06 , B64D2027/005 , B64D2027/026 , Y02T50/162 , Y02T50/66
摘要： The invention concerns reduction of tip vortices in aircraft propellers, wherein a fence having anhedral or dihedral is attached to the blades of the propeller. Another form of the invention is applicable to counterrotating propeller systems, wherein a fence is attached to the blades of the forward propeller of the system, and no fences are attached to the aft propeller.
摘要翻译： 本发明涉及飞机螺旋桨中的尖端旋涡的减少，其中具有单面或双面的篱笆附接到螺旋桨的叶片上。 本发明的另一种形式可应用于逆向旋转螺旋桨系统，其中挡板连接到系统的前进螺旋桨的叶片上，并且没有栅栏连接到后部螺旋桨。
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公开(公告)号：US4621978A
公开(公告)日：1986-11-11
申请号：US677631
申请日：1984-12-03
申请人： Alan R. Stuart
发明人： Alan R. Stuart
CPC分类号： F01D7/00 , B64C11/308 , F01D9/065 , F02K3/072 , B64D2027/005 , F05D2260/74 , F05D2260/76 , Y02T50/66 , Y02T50/671
摘要： An improved counterrotating power turbine is disclosed. The power turbine includes a support having an annular axial cross-section and forward and aft portions. The forward portion of the support has a diameter greater than the diameter of the aft portion. Also included are a first rotor and a second rotor. The first rotor is supported on the first portion of the support by first bearing means and extends to the aft portion forming a first interface therewith. The second rotor is supported on the first rotor by second bearing means and extends to the aft portion of the support forming a second interface therewith. In this manner, it is possible to have low diameter slip rings at the first and second interfaces while maintaining relative high diameters for the rotor bearing means.
摘要翻译： 公开了一种改进的逆转动力涡轮机。 动力涡轮机包括具有环形轴向横截面和前后部分的支撑件。 支撑件的前部具有大于后部直径的直径。 还包括第一转子和第二转子。 第一转子通过第一轴承装置支撑在支撑件的第一部分上，并延伸到与其形成第一界面的后部。 第二转子通过第二轴承装置支撑在第一转子上，并且延伸到支撑件的后部形成与其的第二界面。 以这种方式，可以在第一和第二界面处具有低直径的滑环，同时保持用于转子轴承装置的相对高的直径。
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公开(公告)号：US5921500A
公开(公告)日：1999-07-13
申请号：US947274
申请日：1997-10-08
申请人： Joe E. Ellis , Alan R. Stuart
发明人： Joe E. Ellis , Alan R. Stuart
CPC分类号： B64D27/20
摘要： An aircraft engine mount includes a mounting platform fixedly joinable to an aircraft pylon, and a cooperating mounting ring fixedly joinable to an aircraft engine. The platform includes four lugs arranged in forward and aft pairs. Four links are arranged in forward and aft pairs pivotally joined at opposite ends thereof to respective ones of the four lugs and to the mounting ring. The four links are symmetrically arranged both circumferentially and axially to carry both thrust loads and in-plane vertical and side loads between the mounting ring and mounting platform with failsafe redundancy.
摘要翻译： 飞机发动机支架包括固定地连接到飞机塔架的安装平台和可固定地连接到飞行器发动机的协作安装环。 该平台包括四个前后排列的凸耳。 四个连杆被布置在其两端枢转地连接到其中的四个凸耳中的相应一个和安装环上的前部和后部对。 四个连杆在圆周和轴向对称布置，以承载安装环和安装平台之间的两个推力负载和面内垂直和侧向负载，并具有故障安全冗余。
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公开(公告)号：USD286880S
公开(公告)日：1986-11-25
申请号：US586372
申请日：1984-03-05
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公开(公告)号：US4161318A
公开(公告)日：1979-07-17
申请号：US886605
申请日：1978-03-14
申请人： Alan R. Stuart , Brian S. Stratford
发明人： Alan R. Stuart , Brian S. Stratford
摘要： Turbine blade shrouds are sealed by injecting air on to the shroud immediately upstream of a shroud seal. This air serves two purposes: it creates a turbulent flow immediately upstream of the shroud seal, thus spoiling and reducing the leakage flow over the seal, and the hot gases which would otherwise leak over the seal are replaced by the cooler air, thus reducing energy wastage and improving S.F.C. (specific fuel consumption).
摘要翻译： 涡轮叶片护罩通过在护罩密封件的紧邻上游将空气喷射到护罩上而被密封。 这种空气有两个目的：它会在护罩密封件的上游立即产生湍流，从而破坏和减少密封件上的泄漏流量，否则将会泄漏在密封件上的热气体被较冷的空气所替代，从而减少能量 浪费和改善证监会 （比燃料消耗）。
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