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公开(公告)号：US5123813A
公开(公告)日：1992-06-23
申请号：US662693
申请日：1991-03-01
CPC分类号： F01D5/323 , F01D5/26 , F01D5/3007 , Y10S416/50 , Y10T403/7061
摘要： Apparatus for preloading an airfoil blade attached to a rotor disk in a gas turbine engine. The dovetail root of a composite fan blade is preloaded to prevent rubbing and wear against the dovetail slot of a metal rotor disk during fan windmilling, with the aircraft engine off, due to wind and breezes at the airport. A resilient material is inserted into the lower portion of the slot below the engaged blade root. The disk has a radius which intersects the slot. The material is acted upon by a device which adjustably compresses the inserted material perpendicular to the radius of the disk. This causes the compressed material to exert a radially outward force against the bottom of the engaged root of the blade.
摘要翻译： 用于预装载在燃气涡轮发动机中的转子盘上的翼型叶片的装置。 复合风扇叶片的燕尾根预先加载，以防止在风扇风车期间摩擦和磨损金属转子盘的燕尾槽，飞机发动机由于机场的风和微风而关闭。 将弹性材料插入在所接合的叶片根部下方的狭槽的下部。 磁盘具有与槽相交的半径。 该材料被可调节地压缩垂直于盘半径的插入材料的装置作用。 这使得压缩的材料向刀片的接合根部的底部施加径向向外的力。
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公开(公告)号：US5573377A
公开(公告)日：1996-11-12
申请号：US426205
申请日：1995-04-21
申请人： Nigel M. Bond , Martin C. Hemsworth
发明人： Nigel M. Bond , Martin C. Hemsworth
CPC分类号： F01D5/3007 , F01D5/147 , F01D5/282 , F01D5/3092 , F05D2250/00 , F05D2250/711 , F05D2300/603
摘要： An assembly of a plurality of composite blades including blade roots carried by blade root receiving slots in the rotor wherein the slot has a slot wall with a radially outward portion which, when assembled, diverges from a spaced apart juxtaposed blade root pressure face radially outer surface in an amount which is a function of a predetermined amount of centrifugal loading on the blade during operation of the assembly, to allow at least a portion of the radially outer surface of the root pressure face to be in contact with the slot wall radially outward surface during operation.
摘要翻译： 多个复合叶片的组件，包括由转子中的叶片根部接收槽支承的叶片根部，其中所述狭槽具有带有径向向外部分的槽壁，所述槽壁当组装时从间隔开的并置叶片根部压力面径向外表面 其量是在组件操作期间在叶片上的预定量的离心负载的函数的量，以允许根部压力面的径向外表面的至少一部分与槽壁径向向外的表面接触 在运行期间。
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公开(公告)号：US4289447A
公开(公告)日：1981-09-15
申请号：US84244
申请日：1979-10-12
申请人： Albert P. Sterman , Charles H. Gay, Jr. , Frederick W. Tegarden , Dean T. Lenahan , Martin C. Hemsworth
发明人： Albert P. Sterman , Charles H. Gay, Jr. , Frederick W. Tegarden , Dean T. Lenahan , Martin C. Hemsworth
CPC分类号： F01D11/125 , Y10T29/49316 , Y10T428/1234 , Y10T428/12375 , Y10T428/24149
摘要： A turbine shroud includes a ceramic sealing layer secured to a metal substrate. In one form, the metal substrate includes a plurality of pegs extending therefrom. Intermediate bonding layers are disposed on the peg-metal substrate structure. A ceramic sealing layer of zirconium oxide with about 20 weight percentage magnesium oxide is disposed, e.g., plasma sprayed, on the intermediate bonding layers. The ceramic sealing layer includes an ordered pattern of very fine cracks therein which reduce the thermal stress in the ceramic sealing layer. A method of constructing a turbine shroud structure is also disclosed.
摘要翻译： 涡轮罩包括固定到金属基底的陶瓷密封层。 在一种形式中，金属基底包括从其延伸的多个钉。 中间粘合层设置在钉金属基底结构上。 将具有约20重量％的氧化镁的氧化锆陶瓷密封层例如等离子体喷涂在中间粘合层上。 陶瓷密封层包括其中非常细的裂缝的有序图案，其降低了陶瓷密封层中的热应力。 还公开了一种构造涡轮机罩结构的方法。
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公开(公告)号：US4087199A
公开(公告)日：1978-05-02
申请号：US743616
申请日：1976-11-22
CPC分类号： F01D11/08 , Y02T50/671
摘要： A high temperature turbine shroud assembly for an aircraft gas turbine engine comprising a plurality of arcuate ceramic blocks arranged in a ring. The blocks are supported by a pair of annular support members which retain the blocks in the assembly. Spring-like fingers associated with the support members apply a preloaded force against a pair of slanted dovetail surfaces on the blocks to force the blocks against rigid stops formed upon the annular support members, thereby establishing their proper radial position within the assembly. The preload applied by the fingers accommodates the thermal expansion differences between the ceramic blocks and the metallic support members. In an alternative embodiment, the blocks are retained between cooperating rigid legs extending from the annular support members and wedged radially inwardly into position by a preloaded spring contacting the back side of the blocks. Heat transfer between the blocks and metallic support members is minimized by providing point or line contact between components, thus reducing the contact area available for heat conduction.
摘要翻译： 一种用于飞机燃气涡轮发动机的高温涡轮机护罩组件，其包括布置成环的多个弧形陶瓷块。 这些块由一对将块固定在组件中的环形支撑构件支撑。 与支撑构件相关联的弹簧状指状物对块上的一对倾斜的燕尾表面施加预加载力，以迫使块抵抗形成在环形支撑构件上的刚性挡块，从而在组件内建立其适当的径向位置。 由手指施加的预载荷容纳陶瓷块和金属支撑构件之间的热膨胀差异。 在替代实施例中，块被保持在从环形支撑构件延伸的配合的刚性支柱之间并且通过接触块的后侧的预加载的弹簧径向向内楔入到位。 通过在部件之间提供点或线接触来最小化块和金属支撑构件之间的热传递，从而减少可用于热传导的接触面积。
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公开(公告)号：US5853285A
公开(公告)日：1998-12-29
申请号：US872840
申请日：1997-06-11
申请人： Frederick Martin Miller , Roger Clayton Walker , Christopher Charles Glynn , Martin C. Hemsworth
发明人： Frederick Martin Miller , Roger Clayton Walker , Christopher Charles Glynn , Martin C. Hemsworth
CPC分类号： F01D5/08 , F01D25/04 , F01D5/10 , Y02T50/676 , Y10S416/50
摘要： In a compressor rotor assembly including a plurality of rotor disks affixed to a rotor body, and wherein at least one radially directed cooling tube is supported from a radially outer end within a rotor shaft, with an opposite, radially inner free end extending toward a longitudinal axis of the rotor, an improvement comprising a ring member loosely secured to the tube at the free end.
摘要翻译： 在包括固定在转子体上的多个转子盘的压缩机转子组件中，并且其中至少一个径向冷却管从转子轴内的径向外端支撑，相对的径向内自由端朝向纵向 转子的轴线，其改进包括在自由端松散地固定到管的环件。
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公开(公告)号：US5593274A
公开(公告)日：1997-01-14
申请号：US414695
申请日：1995-03-31
申请人： Diether E. Carreno , Albert Myers , Gene D. Palmer , Philip M. Caruso , Ian D. Wilson , Martin C. Hemsworth
发明人： Diether E. Carreno , Albert Myers , Gene D. Palmer , Philip M. Caruso , Ian D. Wilson , Martin C. Hemsworth
CPC分类号： F01D5/085 , F01D5/081 , F01D9/06 , F02C7/16 , F02C7/18 , F05D2230/61 , F05D2260/232 , F05D2260/2322
摘要： A rotor cooling circuit includes a cooling medium supply reservoir for supplying cooling medium to a plurality of axial passages through the turbine wheel and spacer disc rims. A passageway communicates cooling medium from the reservoir for flow in series and in a serpentine manner in and about the cavities between the wheels and discs. The flows are reunited at a plenum for flowing the cooling medium into first and second stage buckets. Return passages through the rims of the wheels and spacer discs return spent cooling medium from the buckets to a return location external of the rotor. Transition elements between the buckets and spacer plates in the rotor rim accommodate any thermal mismatch between the adjoining buckets and spacer plates to prevent cooling medium leakage at the joints.
摘要翻译： 转子冷却回路包括用于将冷却介质供给到通过涡轮机叶轮和隔离盘轮缘的多个轴向通道的冷却介质供应储存器。 通道将来自储存器的冷却介质与冷却介质连通并以蛇形方式连接在车轮和盘之间的空腔内和周围。 流动在用于将冷却介质流入第一和第二级桶的增压室处重新聚合。 通过车轮和间隔盘的轮缘返回通道将废冷却介质从铲斗返回到转子外部的返回位置。 转子轮辋中的铲斗和间隔板之间的过渡元件适应相邻的铲斗和间隔板之间的任何热失配，以防止接头处的冷却介质泄漏。
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公开(公告)号：US4971641A
公开(公告)日：1990-11-20
申请号：US490506
申请日：1990-03-01
IPC分类号： B64C11/26
CPC分类号： B64C11/26 , B64D2027/026
摘要： An aircraft propeller blade is constructed by forming two shells of composite material laminates and bonding the two shells to a metallic spar with foam filler pieces interposed between the shells at desired locations. The blade is then balanced radially and chordwise.
摘要翻译： 飞机螺旋桨叶片通过形成复合材料层压体的两个壳体并且将两个壳体结合到金属翼梁构造，其中泡沫填充片插入在所需位置的壳体之间。 然后将叶片径向和弦并入。
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公开(公告)号：US4784575A
公开(公告)日：1988-11-15
申请号：US157179
申请日：1988-02-12
CPC分类号： B64C11/18 , B64C11/20 , B64D2027/026 , Y10S416/02
摘要： A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.
摘要翻译： 用于飞行器发动机的推进器叶片包括形成为弯曲形状的翼型部分。 金属叶片翼片插入在叶片的相对表面之间并且结合到表面以建立叶片的结构完整性。 金属叶片翼梁包括允许叶片附接到发动机的根部端部。
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公开(公告)号：US06464461B2
公开(公告)日：2002-10-15
申请号：US09731982
申请日：2000-12-08
申请人： Ian David Wilson , Kevin Joseph Barb , Ming Cheng Li , Susan Marie Hyde , Thomas Charles Mashey , Ronald Richard Wesorick , Christopher Charles Glynn , Martin C. Hemsworth
发明人： Ian David Wilson , Kevin Joseph Barb , Ming Cheng Li , Susan Marie Hyde , Thomas Charles Mashey , Ronald Richard Wesorick , Christopher Charles Glynn , Martin C. Hemsworth
IPC分类号： F01D508
CPC分类号： F01D5/085 , F02C7/16 , F05D2260/2322 , Y02T50/676
摘要： The steam cooling circuit for a gas turbine includes a bore tube assembly supplying steam to circumferentially spaced radial tubes coupled to supply elbows for transitioning the radial steam flow in an axial direction along steam supply tubes adjacent the rim of the rotor. The supply tubes supply steam to circumferentially spaced manifold segments located on the aft side of the 1-2 spacer for supplying steam to the buckets of the first and second stages. Spent return steam from these buckets flows to a plurality of circumferentially spaced return manifold segments disposed on the forward face of the 1-2 spacer. Crossover tubes couple the steam supply from the steam supply manifold segments through the 1-2 spacer to the buckets of the first stage. Crossover tubes through the 1-2 spacer also return steam from the buckets of the second stage to the return manifold segments. Axially extending return tubes convey spent cooling steam from the return manifold segments to radial tubes via return elbows.
摘要翻译： 用于燃气涡轮机的蒸汽冷却回路包括孔管组件，其将周向间隔开的径向管供给蒸汽，所述径向管连接到供应弯头，以沿着与沿转子边缘的蒸汽供应管沿轴向方向转换径向蒸汽流。 供应管将位于1-2间隔物的后侧的周向隔开的歧管段供应蒸汽，以将蒸汽供应到第一和第二级的桶。 来自这些铲斗的废水返回蒸汽流向设置在1-2间隔物的前表面上的多个周向间隔开的返回歧管段。 交叉管将来自蒸汽供应歧管段的蒸汽供应通过1-2间隔件连接到第一级的桶。 通过1-2间隔物的交叉管还将蒸汽从第二级的桶返回到回流歧管段。 轴向延伸的回流管通过返回弯头将废冷却蒸汽从返回歧管段传送到径向管。
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公开(公告)号：USRE34207E
公开(公告)日：1993-03-30
申请号：US660459
申请日：1991-02-26
摘要： A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.
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