公开(公告)号：US08231353B2

公开(公告)日：2012-07-31

申请号：US12347341

申请日：2008-12-31

申请人： Gunnar L. Siden ,  Craig A. Bielek ,  Brian C. Barr ,  Bradley T. Boyer ,  Thomas W. Vandeputte ,  Peter A. Galie

发明人： Gunnar L. Siden ,  Craig A. Bielek ,  Brian C. Barr ,  Bradley T. Boyer ,  Thomas W. Vandeputte ,  Peter A. Galie

IPC分类号： F01D5/22

CPC分类号： F01D5/145 ,  Y02T50/673

摘要： A flow directing assembly for use in a turbine engine comprising: a plurality of circumferentially spaced blades, each of the blades including a radial projecting airfoil with a concave pressure side and a convex suction side that extend from a platform; and a plurality of flow passages, each flow passage defined by the airfoils of neighboring blades and an inner wall formed by abutting platforms of neighboring blades, the inner wall forming the inner radial boundary of the flow passage; wherein the inner wall of one or more of the flow passages comprises means for reducing frictional losses between the flow through the turbine engine and the inner wall. The means for reducing frictional losses may comprise a non-axisymmetrical trough positioned between neighboring airfoils that is configured to reduce frictional losses.

摘要翻译： 一种用于涡轮发动机的流动引导组件，包括：多个周向间隔开的叶片，每个叶片包括径向突出的翼型，其具有从平台延伸的凹压侧和凸吸力侧; 以及多个流动通道，每个流动通道由相邻叶片的翼型限定，以及由相邻叶片的邻接平台形成的内壁，所述内壁形成流动通道的内部径向边界; 其中一个或多个流动通道的内壁包括用于减少通过涡轮发动机的流动与内壁之间的摩擦损失的装置。 用于减少摩擦损失的装置可以包括位于相邻翼型之间的非轴对称槽，其构造成减小摩擦损失。

公开(公告)号：US20100166558A1

公开(公告)日：2010-07-01

申请号：US12347341

申请日：2008-12-31

申请人： Gunnar L. Siden ,  Craig A. Bielek ,  Brian C. Barr ,  Bradley T. Boyer ,  Thomas W. Vandeputte ,  Peter A. Galie

发明人： Gunnar L. Siden ,  Craig A. Bielek ,  Brian C. Barr ,  Bradley T. Boyer ,  Thomas W. Vandeputte ,  Peter A. Galie

IPC分类号： F01D5/22 ,  F01D5/14

CPC分类号： F01D5/145 ,  Y02T50/673

摘要： A flow directing assembly for use in a turbine engine comprising: a plurality of circumferentially spaced blades, each of the blades including a radial projecting airfoil with a concave pressure side and a convex suction side that extend from a platform; and a plurality of flow passages, each flow passage defined by the airfoils of neighboring blades and an inner wall formed by abutting platforms of neighboring blades, the inner wall forming the inner radial boundary of the flow passage; wherein the inner wall of one or more of the flow passages comprises means for reducing frictional losses between the flow through the turbine engine and the inner wall. The means for reducing frictional losses may comprise a non-axisymmetrical trough positioned between neighboring airfoils that is configured to reduce frictional losses.

摘要翻译： 一种用于涡轮发动机的流动引导组件，包括：多个周向间隔开的叶片，每个叶片包括径向突出的翼型，其具有从平台延伸的凹压侧和凸起的吸力侧; 以及多个流动通道，每个流动通道由相邻叶片的翼型限定，以及由相邻叶片的邻接平台形成的内壁，所述内壁形成流动通道的内部径向边界; 其中一个或多个流动通道的内壁包括用于减少通过涡轮发动机的流动与内壁之间的摩擦损失的装置。 用于减少摩擦损失的装置可以包括位于相邻翼型之间的非轴对称槽，其构造成减小摩擦损失。

公开(公告)号：US20090193785A1

公开(公告)日：2009-08-06

申请号：US12023343

申请日：2008-01-31

申请人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

发明人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

IPC分类号： F02C6/06

CPC分类号： F02C6/00 ,  F01D15/10 ,  F02C3/10 ,  F02C3/107 ,  F02C6/18

摘要： A power generating turbine system that includes: a turbine that includes three sections, a high-pressure turbine section, a mid-pressure turbine section, and a low-pressure turbine section that each reside on a separate shaft; 2) an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through the turbine, the axial compressor comprising a high-pressure compressor section and a low-pressure compressor section; 3) a two-pole generator; 4) a four-pole generator; 5) a first shaft that couples the high-pressure turbine section to the high-pressure compressor section such that, in operation, the high-pressure turbine section drives the high-pressure compressor section; 6) a second shaft that couples the mid-pressure turbine section to the high-pressure compressor section and the two-pole generator such that, in operation, the mid-pressure turbine section drives the high-pressure compressor section and two-pole generator; and 7) a third shaft that couples the low-pressure turbine section to the four-pole generator such that in operation the low-pressure turbine section drives the four-pole generator.

摘要翻译： 一种发电涡轮机系统，其包括：涡轮机，其包括三个部分，高压涡轮部分，中压涡轮部分和低压涡轮部分，每个部分驻留在单独的轴上; 2）一种轴向压缩机，其压缩与燃料混合并在燃烧器中燃烧的空气流，使得所产生的热气流引导通过涡轮机，轴向压缩机包括高压压缩机部分和低压 压缩机部分; 3）双极发电机; 4）四极发生器; 5）将高压涡轮部分连接到高压压缩机部分的第一轴，使得在操作中，高压涡轮部分驱动高压压缩机部分; 6）将中压涡轮部分连接到高压压缩机部分和两极发生器的第二轴，使得在运行中，中压涡轮部分驱动高压压缩机部分和两极发生器 ; 以及7）第三轴，其将所述低压涡轮机部分联接到所述四极发电机，使得在运行中所述低压涡轮部分驱动所述四极发电机。

公开(公告)号：US20090193784A1

公开(公告)日：2009-08-06

申请号：US12023319

申请日：2008-01-31

申请人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

发明人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

IPC分类号： F02C6/04

CPC分类号： F01D15/10 ,  F02C3/10 ,  F02C3/107 ,  F02C6/00 ,  F02C6/18

摘要： A power generating turbine system that may include: 1) a turbine that includes two sections, a high-pressure turbine section and a low-pressure turbine section that each reside on a separate shaft; 2) an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through the turbine; 3) a two-pole generator; 4) a four-pole generator; 5) a first shaft that couples the high-pressure turbine section to the axial compressor and the two-pole generator such that, in operation, the high-pressure turbine section drives the axial compressor and the two-pole generator; and 6) a second shaft that couples the low-pressure turbine section to the four-pole generator such that, in operation, the low-pressure turbine section drives the four-pole generator.

摘要翻译： 一种发电涡轮机系统，其可以包括：1）包括两个部分的涡轮机，每个部分都存在于单独的轴上的高压涡轮部分和低压涡轮部分; 2）轴向压缩机，其压缩然后与燃料混合并在燃烧器中燃烧的空气流，使得所产生的热气流引导通过涡轮机; 3）双极发电机; 4）四极发生器; 5）将高压涡轮部分连接到轴向压缩机和双极发生器的第一轴，使得在操作中，高压涡轮部分驱动轴向压缩机和两极发电机; 以及6）第二轴，其将所述低压涡轮部分连接到所述四极发电机，使得在操作中所述低压涡轮部分驱动所述四极发电机。

公开(公告)号：US20090193783A1

公开(公告)日：2009-08-06

申请号：US12023298

申请日：2008-01-31

申请人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

发明人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

IPC分类号： F02C6/06

CPC分类号： F02C3/107 ,  F01D15/10 ,  F02C3/10 ,  F02C6/00 ,  F02C6/18

摘要： A power generating turbine system that may include: 1) a turbine that includes two sections, a high-pressure turbine section and a low-pressure turbine section that each reside on a separate shaft; 2) an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through the turbine, the axial compressor comprising a low-pressure compressor section and a high-pressure compressor section; 3) a four-pole generator; 4) a first shaft that couples the high-pressure turbine section to the high-pressure compressor section such that, in operation, the high-pressure turbine section drives the high-pressure compressor; and 5) a second shaft that couples the low-pressure turbine section to the four-pole generator and the low-pressure compressor such that, in operation, the low-pressure turbine section drives the four-pole generator and the low-pressure compressor.

摘要翻译： 一种发电涡轮机系统，其可以包括：1）包括两个部分的涡轮机，每个部分都存在于单独的轴上的高压涡轮部分和低压涡轮部分; 2）一种轴向压缩机，其压缩与燃料混合并在燃烧器中燃烧的空气流，使得所产生的热气流引导通过涡轮机，轴向压缩机包括低压压缩机部分和高压 压缩机部分; 3）四极发电机; 4）将高压涡轮部分连接到高压压缩机部分的第一轴，使得在操作中，高压涡轮部分驱动高压压缩机; 以及5）第二轴，其将低压涡轮部分连接到四极发电机和低压压缩机，使得在操作中，低压涡轮部分驱动四极发电机和低压压缩机 。

公开(公告)号：US08087253B2

公开(公告)日：2012-01-03

申请号：US12274568

申请日：2008-11-20

申请人： Wei Ning ,  Stephen W. Tesh ,  Gunnar L. Siden ,  Bradley T. Boyer

发明人： Wei Ning ,  Stephen W. Tesh ,  Gunnar L. Siden ,  Bradley T. Boyer

IPC分类号： F02C7/12

CPC分类号： F01D25/12 ,  F01D9/023 ,  F01D9/04 ,  F02C7/125 ,  F02C7/18 ,  Y02T50/675

摘要： A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades, and a plurality of circumferentially spaced injection ports disposed upstream of a first row of stator blades in the turbine; the injection ports comprising a port through which cooling air is injected into the hot-gas path of the turbine, the method comprising: configuring the stator blades in the first row of stator blades such that the circumferential position of a leading edge of one of the stator blades is located within +/−15% pitch of the first row of stator blades of the circumferential location of the injection port midpoint of at least a plurality of the injection ports.

摘要翻译： 一种运行涡轮发动机的方法，其中所述涡轮发动机包括压缩机，燃烧器，涡轮机，多个连续的轴向堆叠的级，其包括一排周向间隔开的定子叶片和周向间隔开的转子叶片，以及多个周向间隔开的 喷射口设置在涡轮机中的第一排定子叶片的上游; 所述喷射口包括将所述冷却空气注入到所述涡轮机的热气路径中的端口，所述方法包括：将所述第一排定子叶片中的所述定子叶片配置成使得所述第一排定子叶片的前缘的周向位置 定子叶片位于至少多个喷射口的喷射口中点的圆周位置的第一排定子叶片的+/- 15％的间距内。

公开(公告)号：US20100122538A1

公开(公告)日：2010-05-20

申请号：US12274568

申请日：2008-11-20

申请人： Wei Ning ,  Stephen W. Tesh ,  Gunnar L. Siden ,  Bradley T. Boyer

发明人： Wei Ning ,  Stephen W. Tesh ,  Gunnar L. Siden ,  Bradley T. Boyer

IPC分类号： F02C7/18 ,  F01D25/12 ,  F01D1/02

CPC分类号： F01D25/12 ,  F01D9/023 ,  F01D9/04 ,  F02C7/125 ,  F02C7/18 ,  Y02T50/675

摘要： A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades, and a plurality of circumferentially spaced injection ports disposed upstream of a first row of stator blades in the turbine; the injection ports comprising a port through which cooling air is injected into the hot-gas path of the turbine, the method comprising: configuring the stator blades in the first row of stator blades such that the circumferential position of a leading edge of one of the stator blades is located within +/−15% pitch of the first row of stator blades of the circumferential location of the injection port midpoint of at least a plurality of the injection ports.

摘要翻译： 一种运行涡轮发动机的方法，其中所述涡轮发动机包括压缩机，燃烧器，涡轮机，多个连续的轴向堆叠的级，其包括一排周向间隔开的定子叶片和周向间隔开的转子叶片，以及多个周向间隔开的 喷射口设置在涡轮机中的第一排定子叶片的上游; 所述喷射口包括将所述冷却空气注入到所述涡轮机的热气路径中的端口，所述方法包括：将所述第一排定子叶片中的所述定子叶片配置成使得所述第一排定子叶片的前缘的周向位置 定子叶片位于至少多个喷射口的喷射口中点的圆周位置的第一排定子叶片的+/- 15％的间距内。

公开(公告)号：US20090193782A1

公开(公告)日：2009-08-06

申请号：US12023279

申请日：2008-01-31

申请人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

发明人： Gunnar L. Siden ,  Sal A. Leone ,  John E. Sholes ,  Victor G. Hatman ,  Douglas C. Hofer ,  Thomas W. Vandeputte ,  Sylvain Pierre

IPC分类号： F02C6/06

CPC分类号： F02C6/00 ,  F01D15/10 ,  F02C3/10 ,  F02C3/107 ,  F02C6/18

摘要： A power generating turbine system that may include an axial compressor that compresses a flow of air that is then mixed with a fuel and combusted in a combustor such that the resulting flow of hot gas is directed through a turbine. The turbine may include a high-pressure turbine section and a low-pressure turbine section. The high-pressure turbine section may be coupled via a first shaft to the axial compressor such that in operation the high-pressure turbine section drives the axial compressor. And, the low-pressure turbine section may be coupled via a second shaft to a low-speed generator such that in operation the low-pressure turbine section drives the low-speed generator.

摘要翻译： 发电涡轮机系统，其可以包括轴向压缩机，其压缩空气流，然后将其与燃料混合并在燃烧器中燃烧，使得所产生的热气流引导通过涡轮机。 涡轮可以包括高压涡轮部分和低压涡轮部分。 高压涡轮机部分可以经由第一轴联接到轴向压缩机，使得在操作中，高压涡轮部分驱动轴向压缩机。 并且，低压涡轮机部分可以经由第二轴联接到低速发电机，使得在运行中，低压涡轮部分驱动低速发电机。