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1.发明授权公开(公告)号：US06652235B1
公开(公告)日：2003-11-25
申请号：US10160527
申请日：2002-05-31
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/141 , F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676 , Y10T29/49341
摘要： A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.
摘要翻译： 一种用于制造用于燃气涡轮发动机的转子叶片的方法有助于降低转子叶片的尖端部分的操作温度。 该方法包括形成包括第一侧壁和第二侧壁的翼型件，第一侧壁和第二侧壁连接在前缘和后缘以在其中限定空腔，其中第一和第二侧壁在转子叶片根部和转子叶片顶板之间径向延伸，以及 形成从所述转子叶片尖端板沿着所述第一侧壁延伸的第一末端壁，使得所述第一末端壁的至少一部分相对于所述转子叶片第一侧壁至少部分地凹入以限定从所述第一侧壁延伸的尖端架 机翼后缘朝向翼型前缘。 第二顶端壁形成为沿着第二侧壁从转子叶片顶板延伸。
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公开(公告)号：US06382908B1
公开(公告)日：2002-05-07
申请号：US09764637
申请日：2001-01-18
IPC分类号： F01D906
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A nozzle vane includes a row of trailing edge apertures and cooperating inboard slots joined in flow communication with a mid-chord cavity. An outboard slot is spaced outwardly from a respective last one of the inboard slots, and outboard of a respective last one of the trailing edge apertures. The outboard slot extends behind a fillet between the vane and a supporting band and is effective for backside cooling thereof.
摘要翻译： 喷嘴叶片包括一排后缘孔和协作的内槽，其与中和弦腔流动连通。 外侧狭槽从相应的最后一个内侧槽中向外间隔开，并且在相应的最后一个后缘孔中外侧隔开。 外侧插槽延伸在叶片和支撑带之间的圆角之后，对其后侧冷却是有效的。
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公开(公告)号：US06715988B2
公开(公告)日：2004-04-06
申请号：US10273506
申请日：2002-10-18
申请人： Leslie Eugene Leeke , Sean Robert Keith , Ronald Eugene Mc Rae, Jr. , Richard William Albrecht, Jr. , David Alan Frey
发明人： Leslie Eugene Leeke , Sean Robert Keith , Ronald Eugene Mc Rae, Jr. , Richard William Albrecht, Jr. , David Alan Frey
IPC分类号： F01D518
CPC分类号： F01D5/186 , F05D2250/71 , F05D2260/202 , F05D2260/94 , F05D2260/941 , Y02T50/67 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The suction side wall has a selectively reduced thickness, which allows shortened trailing edge slots, improving trailing edge cooling.
摘要翻译： 中空的冷却涡轮机翼片设置有压力和吸力侧壁以及多个后缘冷却通道，其在后缘进给冷却空气排放槽。 吸力侧壁具有选择性地减小的厚度，这允许缩短的后缘槽，改善后缘冷却。
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公开(公告)号：US06672832B2
公开(公告)日：2004-01-06
申请号：US10040660
申请日：2002-01-07
IPC分类号： F01D530
CPC分类号： F01D5/143 , Y02T50/673 , Y10S415/914
摘要： A turbine includes a row of blades each having an integral airfoil, platform, and dovetail. Each platform has opposite first and second side edges corresponding with the opposite pressure and suction sides of the airfoil. The platform first side edge is radially higher than the platform second side edge continuously between opposite forward and aft edges of the platform. In this way, adjacent platforms define a down step therebetween for preventing obstruction of combustion gases flowable downstream thereover.
摘要翻译： 涡轮机包括一排叶片，每排叶片具有整体的翼型，平台和燕尾榫。 每个平台具有相对的第一和第二侧边缘对应于翼型的相对的压力和抽吸侧。 平台第一侧边缘在平台的相对的前后边缘之间连续地径向地高于平台第二侧边缘。 以这种方式，相邻的平台在其间限定了一个向下的步骤，用于防止在其下游流动的燃烧气体的阻塞。
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公开(公告)号：US07607885B2
公开(公告)日：2009-10-27
申请号：US11461042
申请日：2006-07-31
IPC分类号： F01D25/12
CPC分类号： F01D11/08 , F01D25/14 , F01D25/24 , F01D25/246 , F05D2260/201 , Y02T50/676
摘要： A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.
摘要翻译： 提供了一种操作燃气涡轮发动机的方法。 该方法包括将冷却空气引导到护罩悬挂器组件，使得冷却空气流过限定在护罩悬挂器组件中的空腔，引导冷却空气通过从空腔延伸的多个冷却通道，并从多个 冷却通道朝向冲击挡板，以便于冷却从护罩悬挂器悬挂的护罩。
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公开(公告)号：US06428273B1
公开(公告)日：2002-08-06
申请号：US09755352
申请日：2001-01-05
IPC分类号： F04D2958
CPC分类号： F01D5/189 , F01D9/04 , F05D2240/126 , F05D2240/128 , F05D2260/201 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes vanes joined to outer and inner bands. Each vane includes opposite sidewalls extending between leading and trailing edges, with an internal bridge extending between the sidewalls to effect forward and aft cavities. Side ribs extend along the sidewalls and project inwardly into the cavities. Each of the side ribs is truncated adjacent the bridge to uncouple the ribs therefrom and increase nozzle life.
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公开(公告)号：US20090202337A1
公开(公告)日：2009-08-13
申请号：US11461042
申请日：2006-07-31
CPC分类号： F01D11/08 , F01D25/14 , F01D25/24 , F01D25/246 , F05D2260/201 , Y02T50/676
摘要： A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.
摘要翻译： 提供了一种操作燃气涡轮发动机的方法。 该方法包括将冷却空气引导到护罩悬挂器组件，使得冷却空气流过限定在护罩悬挂器组件中的空腔，引导冷却空气通过从空腔延伸的多个冷却通道，并从多个 冷却通道朝向冲击挡板，以便于冷却从护罩悬挂器悬挂的护罩。
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8.发明授权公开(公告)号：US06923616B2
公开(公告)日：2005-08-02
申请号：US10653519
申请日：2003-09-02
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/676
摘要： A method facilitates fabricating a rotor assembly for a gas turbine engine. The method comprises providing a plurality of rotor blades that each include an airfoil, a dovetail, a shank, and a platform, wherein the platform extends between the shank and the airfoil, and wherein the dovetail extends outwardly from the shank, and forming a cooling circuit within a portion of the shank to supply cooling air to the rotor blade for supplying cooling air to the rotor blade for impingement cooling a portion of the rotor blade and for supplying cooling air to the rotor blade for purging a cavity defined downstream from the rotor blade.
摘要翻译： 一种方法有助于制造用于燃气涡轮发动机的转子组件。 该方法包括提供多个转子叶片，每个转子叶片包括翼型件，燕尾榫，柄和平台，其中平台在柄和翼型之间延伸，并且其中燕尾榫从柄部向外延伸，并形成冷却 在所述柄部的一部分内设置电路，以向所述转子叶片供应冷却空气，以向所述转子叶片供应冷却空气，用于冲击冷却所述转子叶片的一部分并用于向所述转子叶片供应冷却空气，用于向所述转子叶片 刀。
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公开(公告)号：US06609891B2
公开(公告)日：2003-08-26
申请号：US09943527
申请日：2001-08-30
申请人： Leslie Eugene Leeke , Sean Robert Keith , Ronald Eugene Mc Rae, Jr. , Lawrence Paul Timko , David Alan Frey
发明人： Leslie Eugene Leeke , Sean Robert Keith , Ronald Eugene Mc Rae, Jr. , Lawrence Paul Timko , David Alan Frey
IPC分类号： F01D518
CPC分类号： F01D5/186 , F05D2260/202 , F05D2260/94 , F05D2260/941 , Y02T50/673 , Y02T50/676
摘要： A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The airfoil trailing edge is selectively thickened in the root portion so as to allow shortened trailing edge slots, thereby improving trailing edge cooling and reducing mechanical and thermal stresses.
摘要翻译： 中空的冷却涡轮机翼片设置有压力和吸力侧壁以及多个后缘冷却通道，其在后缘进给冷却空气排放槽。 叶片后缘在根部部分中选择性地加厚，以便允许缩短的后缘槽，从而改善后缘冷却并降低机械和热应力。
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公开(公告)号：US06551062B2
公开(公告)日：2003-04-22
申请号：US09943526
申请日：2001-08-30
申请人： Leslie Eugene Leeke , Sean Robert Keith , Ronald Eugene McRae, Jr. , Richard William Albrecht, Jr. , David Alan Frey
发明人： Leslie Eugene Leeke , Sean Robert Keith , Ronald Eugene McRae, Jr. , Richard William Albrecht, Jr. , David Alan Frey
IPC分类号： F01D518
CPC分类号： F01D5/186 , F05D2250/71 , F05D2260/202 , F05D2260/94 , F05D2260/941 , Y02T50/67 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The suction side wall has a selectively reduced thickness, which allows shortened trailing edge slots, improving trailing edge cooling.
摘要翻译： 中空的冷却涡轮机翼片设置有压力和吸力侧壁以及多个后缘冷却通道，其在后缘进给冷却空气排放槽。 吸力侧壁具有选择性地减小的厚度，这允许缩短的后缘槽，改善后缘冷却。
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