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公开(公告)号：US6067792A
公开(公告)日：2000-05-30
申请号：US953006
申请日：1997-10-16
Applicant: Henry Tubbs
Inventor： Henry Tubbs
CPC classification number: F01D17/105 , F01D9/065 , F02C7/18 , Y02T50/675
Abstract: In a gas turbine engine, compressor delivery air is fed into air inlets in hollow turbine nozzle guide vanes, and then ejected into the gas stream via holes in the vane walls. Valving is provided so as to provide modulation of the cooling airflow over and above the modulation achieved by compressor output when it changes with engine power setting. Excessive cooling of the gas stream is thus prevented.
Abstract translation: 在燃气涡轮发动机中，压缩机输送空气被供给到空心涡轮喷嘴导向叶片中的空气入口中，然后通过叶片壁中的孔喷射到气流中。 提供阀门，以便当发动机功率设定改变时，提供超过由压缩机输出实现的调制的冷却气流的调制。 因此防止了气流的过度冷却。
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公开(公告)号：US4867635A
公开(公告)日：1989-09-19
申请号：US233123
申请日：1988-08-17
Applicant: Henry Tubbs
Inventor： Henry Tubbs
CPC classification number: F04D29/563 , F01D17/162
Abstract: The invention relates to variable guide vane arrangements for axial flow compressors of aircraft gas turbine engines. The variable guide vane arrangement comprises a plurality of stator vanes rotatably mounted in a stator structure of the compressor. A control ring surrounds and is normally coaxially with the compressor axis, and a plurality of operating levers extend from the control ring to their respective stator vane. The control ring is movable laterally with respect to the axis of the compressor so that the stator vanes in a first half of the compressor are rotated in one direction so that the first half of the compressor operates at a higher pressure ratio and the stator vanes in a second half of the compressor are rotated in the opposite direction so that the second half of the compressor operates at a lower pressure ratio. The half of the compressor operating at a higher pressure ratio is arranged to coincide with a zone of the compressor which has a low intake pressure caused by the inlet flow distortions.
Abstract translation: 本发明涉及用于飞机燃气涡轮发动机的轴流式压缩机的可变导叶装置。 可变导向叶片装置包括可旋转地安装在压缩机的定子结构中的多个定子叶片。 控制环围绕并且通常与压缩机轴线同轴，并且多个操作杆从控制环延伸到它们各自的定子叶片。 控制环可相对于压缩机的轴线横向移动，使得压缩机的前半部分中的定子叶片在一个方向上旋转，使得压缩机的前半部分以更高的压力比工作，并且定子叶片 压缩机的后半部分沿相反方向转动，使得压缩机的后半部分以较低的压力比工作。 在较高压力比下操作的压缩机的一半被布置成与由入口流量变形引起的具有低进气压力的压缩机区域重合。
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公开(公告)号：US4199300A
公开(公告)日：1980-04-22
申请号：US883665
申请日：1978-03-06
Applicant: Henry Tubbs
Inventor： Henry Tubbs
CPC classification number: F01D11/18 , F01D21/045 , F05D2260/208
Abstract: A turbine for a gas turbine engine is provided with a rotary stage comprising an annular array of rotor blades surrounded by an annular shroud member. The shroud member is hollow, the hollow interior being provided with a heat transfer medium which, in operation, functions as a condensable vapor and liquid whereby the shroud member is a heat pipe. The shroud member is further provided with a wall adjacent the aerofoil blade which is adapted to be penetrable by a detached blade or blade portion. The wall of the shroud member is dimensioned so that any such detached blade or blade portion which penetrates the wall enters the hollow shroud ring and is retained within it.
Abstract translation: 用于燃气涡轮发动机的涡轮机设置有旋转台，该旋转台包括由环形护罩构件包围的转子叶片的环形阵列。 护罩构件是中空的，中空内部设置有传热介质，其在操作中用作可冷凝的蒸气和液体，由此护罩构件是热管。 护罩构件还设置有邻近机翼叶片的壁，其适于可被分离的刀片或刀片部分穿透。 护罩构件的壁的尺寸设计成使得穿过壁的任何这样的分离的叶片或叶片部分进入中空的护罩环并保持在其中。
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公开(公告)号：US06513971B2
公开(公告)日：2003-02-04
申请号：US09987587
申请日：2001-11-15
Applicant: Henry Tubbs
Inventor： Henry Tubbs
IPC: G01J508
CPC classification number: G01J5/0014 , G01J5/0088 , G01J5/02 , G01J5/029 , G01J5/04 , G01J5/061 , G01J5/08 , G01J5/0821 , G01J5/0887 , G01J5/0893
Abstract: Use of an optical fiber for the direct receipt of heat radiation for transmission to a remote pyrometer is enabled by the provision of an apertured, contaminant free compartment in the component being heated, and aligning the heat receiving end of the optical fiber with the aperture so as to receive radiated heat from within the compartment.
Abstract translation: 使用光纤直接接收热辐射以传输到远程高温计可以通过在被加热的部件中设置有孔，无污染的隔室，并将光纤的热接收端与孔径对准 以接收来自隔室内的辐射热。
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公开(公告)号：US4978280A
公开(公告)日：1990-12-18
申请号：US355022
申请日：1989-05-22
Applicant: Henry Tubbs
Inventor： Henry Tubbs
CPC classification number: F04D29/563 , F01D17/162
Abstract: A variable guide vane arrangement includes a control ring located in a fixed axial position and an operating lever having a first end and a second end which is secured to the control ring with the first end positioned between two flanges and secured thereto by a pin; the second end is connected to a portion which fits into a bore and is slidable with respect thereto to vary the length of the operating lever.
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Patent Agency Ranking6.发明授权
公开(公告)号：US5332357A
公开(公告)日：1994-07-26
申请号：US52550
申请日：1993-04-23
Applicant: Henry Tubbs
Inventor： Henry Tubbs
CPC classification number: F01D17/162 , F01D17/14 , F01D5/147
Abstract: In an annular array of stator aerofoil vanes (25 ) each of the vanes (25 ) has a flank portion (35 ) which is pivotally attached to the remainder of its associated vane (25). Actuation means (60) are provided to pivot each flank portion (35) relative to the remainder of its associated vane (25 ). Such movement of the flank portions (35 ) provides variation in the cross-sectional areas of the throat (61) defined between adjacent stator vanes (25).
Abstract translation: 在定子翼型叶片（25）的环形阵列中，每个叶片（25）具有枢转地附接到其相关叶片（25）的其余部分的侧面部分（35）。 提供致动装置（60）以使每个侧翼部分（35）相对于其相关联的叶片（25）的其余部分枢转。 侧面部分（35）的这种移动提供在相邻的定子叶片（25）之间限定的喉部（61）的横截面积的变化。
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公开(公告)号：US5263820A
公开(公告)日：1993-11-23
申请号：US906252
申请日：1986-09-04
Applicant: Henry Tubbs
Inventor： Henry Tubbs
CPC classification number: B23P15/02 , F01D5/186 , F01D5/187 , F05D2230/23 , F05D2260/201
Abstract: A cooled aerofoil blade for a gas turbine engine has a hollow trailing edge region in which bridging members interconnect the convex and concave flanks of the blade. The bridging members are each provided with angled cooling passages which are in operation exposed to a cooling air flow and direct that flow onto the internal surfaces of the convex and concave flanks so as to provide impingement cooling thereof.
Abstract translation: 用于燃气涡轮发动机的冷却翼型叶片具有中空后缘区域，桥接构件将叶片的凸面和凹面相互连接。 桥接构件各自设置有成角度的冷却通道，其操作暴露于冷却空气流并将其引导到凸形和凹形侧面的内表面上，以便提供冲击冷却。
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公开(公告)号：US4732535A
公开(公告)日：1988-03-22
申请号：US939883
申请日：1986-12-09
Applicant: Henry Tubbs
Inventor： Henry Tubbs
Abstract: In a multi stage ducted fan or ducted propeller gas turbine engine, a fan flow exit path is provided in the cowl between axially adjacent stages of blades. The stage of blades downstream of the exit are each pivotable to attitudes which on continued rotation of the stage, induces a reverse flow of ambient air into the duct via the nozzle. The normal and reversed airflows meet under the exit path and pass therethrough to atmosphere. The need for blocker doors in the duct is obviated and energy is imported to the fan air passing through the exit by both stages of blades.
Abstract translation: 在多级管道风扇或管道螺旋桨式燃气涡轮发动机中，风扇流出口路径在叶片的轴向相邻级之间设置在整流罩中。 出口下游的叶片的阶段各自可转动到台阶继续旋转时的态度，通过喷嘴引起环境空气逆流流入管道。 正常和反向的气流在出口路径下相交，并通过其进入大气。 管道中阻塞门的需要被消除，能量通过叶片的两个阶段进入通过出口的风扇空气。
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公开(公告)号：US06863495B2
公开(公告)日：2005-03-08
申请号：US10412299
申请日：2003-04-14
Applicant: Mark A Halliwell , Henry Tubbs
Inventor： Mark A Halliwell , Henry Tubbs
Abstract: A turbine blade tip clearance control system has a rigid two part outer casing (42) which sandwiches a control ring (48) therebetween, and an air pressurised flexible inner casing (28) which carries shroud segments (22) within it. Struts (40) span the annular space between the casings (42, 28) and prevent flexing of casing (28) until blade tip clearance needs adjusting, whereupon, ring (48) is heated, along with the adjacent portion of outer casing (42) and expands, allowing casing (28) to flex outwards, thus lifting the shroud segments (22) away from the blade tips (24).Closure of the tip clearance is achieved by cooling ring (48), the resulting contraction thereof, via the struts (40), flexing the inner casing (28) and shroud segments (22) inwards, against the air pressure.
Abstract translation: 涡轮叶片顶端间隙控制系统具有刚性两部分外壳（42），其将其间的控制环（48）夹在其间，并且在其内承载有护罩段（22）的空气加压的柔性内壳（28）。 支柱（40）跨越壳体（42,28）之间的环形空间，并防止壳体（28）的弯曲，直到叶片顶端间隙需要调节，于是环（48）与外壳（42）的相邻部分一起被加热 ）并膨胀，允许外壳（28）向外弯曲，从而将护罩段（22）提升离开叶片尖端（24）。顶端间隙的封闭通过冷却环（48）实现，其产生的收缩通过 所述支柱（40）使所述内壳体（28）和所述护罩段（22）向内偏压抵抗所述空气压力。
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公开(公告)号：US6079200A
公开(公告)日：2000-06-27
申请号：US40614
申请日：1998-03-18
Applicant: Henry Tubbs
Inventor： Henry Tubbs
CPC classification number: F04D29/056 , F01D21/045 , F04D29/668 , F16C19/52 , F05B2260/3011 , Y02T50/672
Abstract: A ducted fan gas turbine engine is provided with a fan which is carried by a shaft. Frangible fuse pins maintain the shaft carrying the fan coaxial with the engine longitudinal axis. In the event of severe fan damage, the fuse pins fracture and the fan shaft orbits about the engine longitudinal axis. A spoked resilient member is provided to exert a radially inward restoration force upon the fan shaft following such an event in order to reduce vibration.
Abstract translation: 风管式燃气涡轮发动机配备有由轴承载的风扇。 易碎的保险丝销保持轴承与风扇与发动机纵向轴线同轴的轴。 在严重风扇损坏的情况下，保险丝销断裂，风扇轴围绕发动机纵向轴线运动。 为了减少振动，提供了一种旋转的弹性构件，以在这种事件之后向风扇轴施加径向向内的恢复力。
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