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1. 发明授权

US07431561B2 Method and apparatus for cooling gas turbine rotor blades 有权
标题翻译：用于冷却燃气轮机转子叶片的方法和装置
公开(公告)号：US07431561B2
公开(公告)日：2008-10-07
申请号：US11356388
申请日：2006-02-16
申请人： Tyler F. Hooper , Bhanu Reddy , Gaoqiu Zhu , Richard William Albrecht, Jr.
发明人： Tyler F. Hooper , Bhanu Reddy , Gaoqiu Zhu , Richard William Albrecht, Jr.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/21 , F05D2240/126 , F05D2250/185
摘要： Methods and apparatus for cooling gas turbine rotor blades is provided. The blade includes an airfoil having an internal three pass serpentine cooling circuit having radially extending first, second, and third serpentine cooling cavities partially separated by, in axially aft succession, a first radially extending internal rib and a second radially extending internal rib. The serpentine cooling circuit includes a first inlet in flow communication with the first cavity and a second inlet in flow communication with at least one of the second and third cavities wherein the first and second inlets are formed during casting of the airfoil.
摘要翻译：提供了用于冷却燃气轮机转子叶片的方法和装置。叶片包括具有内部三通蛇形冷却回路的翼型件，其具有径向延伸的第一，第二和第三蛇形冷却空腔，所述径向延伸的第一，第二和第三蛇形冷却腔沿轴向向后连续地分开第一径向延伸的内肋和第二径向延伸的内肋。蛇形冷却回路包括与第一腔体流动连通的第一入口和与第二和第三腔室中的至少一个流体连通的第二入口，其中在铸造翼型件期间形成第一和第二入口。

2. 发明授权

US06464453B2 Turbine interstage sealing ring 有权
标题翻译：涡轮级间密封圈
公开(公告)号：US06464453B2
公开(公告)日：2002-10-15
申请号：US09729370
申请日：2000-12-04
申请人： Steven Milo Toborg , Dennis Eugene Moore , Richard William Albrecht, Jr.
发明人： Steven Milo Toborg , Dennis Eugene Moore , Richard William Albrecht, Jr.
IPC分类号： F01D518
CPC分类号： F01D11/001 , F01D5/081 , F05D2240/55 , Y02T50/676
摘要： A unitary interstage sealing ring for bridging and sealing the space between the blade shanks of adjacent turbine rotors in a multi-stage turbine. The sealing ring serves to confine relatively cool air conveyed to the turbine so the cooling air flows into the turbine blades for maintaining the blades at a desired temperature. The sealing ring includes a disk-shaped body member that includes a pair of axially-spaced, radially-extending arms that terminate in respective seal teeth for engagement with a stationary annular sealing member. Each of the radial arms includes an outwardly-extending axial arm that terminates in a disk engagement member for sealing engagement with the face of an adjacent turbine disk to confine cooling air within the space between the adjacent turbine disks. Additionally, one of the disk engagement members includes at least one, projection that contacts a respective turbine rotor to limit relative rotation between the sealing ring and the turbine.
摘要翻译：用于桥接和密封多级涡轮机中相邻涡轮转子的叶片柄之间的空间的整体级间密封环。密封环用于限制输送到涡轮机的相对较冷的空气，使得冷却空气流入涡轮机叶片，以将叶片保持在期望的温度。密封环包括盘形主体构件，其包括一对轴向间隔开的径向延伸的臂，其终止于相应的密封齿中，用于与静止的环形密封构件接合。每个径向臂包括向外延伸的轴向臂，其终止于盘接合构件，用于与相邻涡轮盘的表面密封接合，以将冷却空气限制在相邻涡轮盘之间的空间内。此外，一个盘接合构件包括至少一个突出部，其与相应的涡轮转子接触以限制密封环和涡轮机之间的相对旋转。

3. 发明授权

US07458774B2 High pressure turbine disk hub with curved hub surface and method 有权
标题翻译：具有弯曲轮毂表面和方法的高压涡轮盘毂
公开(公告)号：US07458774B2
公开(公告)日：2008-12-02
申请号：US11306227
申请日：2005-12-20
申请人： Richard William Albrecht, Jr. , Craig William Higgins
发明人： Richard William Albrecht, Jr. , Craig William Higgins
IPC分类号： F01D5/02
CPC分类号： F01D5/00 , F01D5/02 , F01D5/06 , F01D5/08 , F01D5/30 , Y02T50/671 , Y02T50/676
摘要： A first stage turbine disk section for a gas turbine engine, including a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a convex, curved hub surface exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable axial stress in the disk hub and allows separation of the peak axial and hoop stresses, thereby reducing the magnitude of the peak hub surface effective stress.
摘要翻译：用于燃气涡轮发动机的第一级涡轮盘部分，包括中心设置的盘毂，其具有终止于外端的一体形成的径向向外延伸的纤维网。盘毂具有在发动机运行期间暴露于高压，高温压缩机排气和放电气体的凸形弯曲毂表面，并且凸形弯曲毂表面用于减小在轴向应力峰值位置处的轴向约束，从而减轻在盘毂中形成不期望的轴向应力并允许峰值轴向和环向应力的分离，从而减小峰值毂表面有效应力的大小。

4. 发明授权

US06715988B2 Turbine airfoil for gas turbine engine 有权
标题翻译：燃气轮机的涡轮机翼
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。

5. 发明授权

US06652226B2 Methods and apparatus for reducing seal teeth wear 有权
公开(公告)号：US06652226B2
公开(公告)日：2003-11-25
申请号：US09783277
申请日：2001-02-09
申请人： Richard William Albrecht, Jr. , Joseph Charles Kulesa , Robert Paul Czachor , Shesh Krishna Srivatsa , Daniel Edward Wines , Thomas Tracy Wallace
发明人： Richard William Albrecht, Jr. , Joseph Charles Kulesa , Robert Paul Czachor , Shesh Krishna Srivatsa , Daniel Edward Wines , Thomas Tracy Wallace
IPC分类号： F01D1112
CPC分类号： F01D11/127 , F01D5/225 , F16J15/444 , Y02T50/672
摘要： A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.

6. 发明授权

US06551062B2 Turbine airfoil for gas turbine engine 有权
标题翻译：燃气轮机的涡轮机翼
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。

7. 发明授权

US06592330B2 Method and apparatus for non-parallel turbine dovetail-faces 有权
标题翻译：非平行涡轮燕尾面的方法和装置
公开(公告)号：US06592330B2
公开(公告)日：2003-07-15
申请号：US09943528
申请日：2001-08-30
申请人： Leslie Eugene Leeke , Sean Robert Keith , Ronald Eugene Mc Rae, Jr. , Robert Ingram Ackerman , Richard William Albrecht, Jr.
发明人： Leslie Eugene Leeke , Sean Robert Keith , Ronald Eugene Mc Rae, Jr. , Robert Ingram Ackerman , Richard William Albrecht, Jr.
IPC分类号： F03B314
CPC分类号： F01D5/3007 , Y10T29/49321
摘要： A dovetail assembly including non-parallel relief faces that facilitates reduced pressure face brinelling in turbine engines. The assembly includes a plurality of rotor blades, each including a dovetail. Each dovetail includes at least a pair of blade tangs including blade relief faces. The dovetail assembly also includes a rotor disk including a plurality of dovetail slots, each sized to receive a dovetail. Each dovetail slot is defined by at least one pair of opposing disk tangs including disk relief faces. The disk relief faces are non-parallel to the blade relief faces when the dovetail is mounted in the dovetail slot.
摘要翻译：燕尾组件包括不平行的浮雕面，其有利于在涡轮发动机中降低压力。组件包括多个转子叶片，每个转子叶片包括燕尾形。每个燕尾榫至少包括一对刀片，包括刀片浮雕面。燕尾组件还包括转子盘，该转子盘包括多个燕尾槽，每个燕尾槽的尺寸被设计成接纳燕尾。每个燕尾槽由至少一对相对的盘形凸起限定，包括盘浮雕面。当燕尾榫安装在燕尾槽中时，盘浮雕面不平行于刀片浮雕面。

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