公开(公告)号：US20160290214A1

公开(公告)日：2016-10-06

申请号：US14676917

申请日：2015-04-02

Applicant: General Electric Company

Inventor： Sanji Ekanayake ,  Alston Ilfrod Scipio ,  Timothy Tahteh Yang

IPC: F01P9/00 ,  F02M31/16 ,  F02C3/04 ,  F01P9/02

CPC classification number: F01P9/00 ,  F01D11/24 ,  F01D25/14 ,  F01P9/02 ,  F02C3/04 ,  F02C6/18 ,  F02C7/224 ,  F02M31/16 ,  F05D2260/208 ,  Y02E20/16 ,  Y02T10/126 ,  Y02T10/16

Abstract: A turbomachine includes a compressor configured to compress air received at an intake portion to form a compressed airflow that exits into an outlet portion. A combustor is operably connected with the compressor, and the combustor receives the compressed airflow. A turbine is operably connected with the combustor, and the turbine receives combustion gas flow from the combustor. The turbine has a turbine casing. A cooling system is operatively connected to the turbine casing. The cooling system includes a plurality of heat pipes attached to and in thermal communication with the turbine casing. The plurality of heat pipes are operatively connected to one or more manifolds. The plurality of heat pipes and the one or more manifolds are configured to transfer heat from the turbine casing to a plurality of heat exchangers.

Abstract translation: 涡轮机包括压缩机，其构造成压缩在进气部分处接收的空气，以形成离开出口部分的压缩空气流。 燃烧器与压缩机可操作地连接，并且燃烧器接收压缩气流。 涡轮机与燃烧器可操作地连接，并且涡轮机接收来自燃烧器的燃烧气体流。 涡轮机具有涡轮机壳体。 冷却系统可操作地连接到涡轮机壳体。 冷却系统包括附接到涡轮壳体并与涡轮机壳体热连通的多个热管。 多个热管可操作地连接到一个或多个歧管。 多个热管和一个或多个歧管被构造成将热量从涡轮壳体传递到多个热交换器。

公开(公告)号：US20160290230A1

公开(公告)日：2016-10-06

申请号：US14676905

申请日：2015-04-02

Applicant: General Electric Company

Inventor： Sanji Ekanayake ,  Alston Ilfrod Scipio ,  Dale Joel Davis ,  Timothy Tahteh Yang

IPC: F02C7/12 ,  F02C3/04

CPC classification number: F02C7/12 ,  F01D11/24 ,  F01D25/14 ,  F02C3/04 ,  F02C6/18 ,  F02C7/224 ,  F05D2260/208 ,  Y02E20/16

Abstract: A turbomachine includes a compressor configured to compress air received at an intake portion to form a compressed airflow that exits into an outlet portion. A combustor is operably connected with the compressor, and the combustor receives the compressed airflow. A turbine is operably connected with the combustor. The turbine receives combustion gas flow from the combustor. The compressor has a compressor casing. A cooling system is operatively connected to the compressor casing. The cooling system includes a plurality of heat pipes attached to and in thermal communication with the compressor casing. The plurality of heat pipes are operatively connected to one or more manifolds. The plurality of heat pipes and the one or more manifolds are configured to transfer heat from the compressor casing to a plurality of heat exchangers.

Abstract translation: 涡轮机包括压缩机，其构造成压缩在进气部分处接收的空气，以形成离开出口部分的压缩空气流。 燃烧器与压缩机可操作地连接，并且燃烧器接收压缩气流。 涡轮与燃烧器可操作地连接。 涡轮机接收来自燃烧器的燃烧气体流。 压缩机具有压缩机壳体。 冷却系统可操作地连接到压缩机壳体。 冷却系统包括附接到压缩机壳体并与压缩机壳体热连通的多个热管。 多个热管可操作地连接到一个或多个歧管。 多个热管和一个或多个歧管被构造成将热量从压缩机壳体传递到多个热交换器。

公开(公告)号：US20160290231A1

公开(公告)日：2016-10-06

申请号：US14676889

申请日：2015-04-02

Applicant: General Electric Company

Inventor： Sanji Ekanayake ,  Alston Ilfrod Scipio ,  Joseph Paul Rizzo

IPC: F02C7/141 ,  F01K23/02 ,  F02C7/224

CPC classification number: F02C7/141 ,  F01K23/02 ,  F02C6/18 ,  F02C7/143 ,  F02C7/224 ,  F05D2260/208 ,  Y02E20/16

Abstract: A turbomachine includes a compressor including an intake portion and an outlet portion. The compressor compresses air received at the intake portion to form a compressed airflow that exits into the outlet portion. A combustor is operably connected with the compressor, and the combustor receives the compressed airflow. A turbine is operably connected with the combustor. The turbine receives combustion gas flow from the combustor. An intercooler is operatively connected to the compressor, and at least a portion of the intercooler is placed in an inter-stage gap between rotor blades and stator vanes of the compressor. The intercooler has a plurality of heat pipes that extend into the inter-stage gap. The plurality of heat pipes is operatively connected to one or more manifolds. The plurality of heat pipes and the one or more manifolds are configured to transfer heat from the compressed airflow to a plurality of heat exchangers.

Abstract translation: 涡轮机包括压缩机，该压缩机包括进气部分和出口部分。 压缩机压缩容纳在进气部分处的空气，以形成离开出口部分的压缩气流。 燃烧器与压缩机可操作地连接，并且燃烧器接收压缩气流。 涡轮与燃烧器可操作地连接。 涡轮机接收来自燃烧器的燃烧气体流。 中间冷却器可操作地连接到压缩机，并且中间冷却器的至少一部分被放置在压缩机的转子叶片和定子叶片之间的阶段间隙中。 中间冷却器具有延伸到阶段间间隙中的多个热管。 多个热管可操作地连接到一个或多个歧管。 多个热管和一个或多个歧管被构造成将热量从压缩气流传递到多个热交换器。

公开(公告)号：US20160290232A1

公开(公告)日：2016-10-06

申请号：US14676895

申请日：2015-04-02

Applicant: General Electric Company

Inventor： Sanji Ekanayake ,  Alston Ilfrod Scipio

IPC: F02C7/141

CPC classification number: F02C7/141 ,  F01D5/181 ,  F01D9/065 ,  F01D25/14 ,  F05D2260/208

Abstract: A turbomachine includes a compressor configured to compress air received at an intake portion to form a compressed airflow that exits into an outlet portion. The compressor has a plurality of rotor blades and a plurality of stator vanes, and a compressor casing forming an outer shell of the compressor. A combustor is operably connected with the compressor, and the combustor receives the compressed airflow. A turbine is operably connected with the combustor, and the turbine receives combustion gas flow from the combustor. The turbine has a turbine casing. A cooling system is operatively connected to the compressor casing. The cooling system includes a plurality of heat pipes located in at least a portion of the plurality of stator vanes. The heat pipes are configured to be in thermal communication with the compressor casing. The heat absorbed by the plurality of heat pipes is transferred to the compressor casing.

Abstract translation: 涡轮机包括压缩机，其构造成压缩在进气部分处接收的空气，以形成离开出口部分的压缩空气流。 压缩机具有多个转子叶片和多个定子叶片，以及形成压缩机的外壳的压缩机壳体。 燃烧器与压缩机可操作地连接，并且燃烧器接收压缩气流。 涡轮机与燃烧器可操作地连接，并且涡轮机接收来自燃烧器的燃烧气体流。 涡轮机具有涡轮机壳体。 冷却系统可操作地连接到压缩机壳体。 冷却系统包括位于多个定子叶片的至少一部分中的多个热管。 热管被构造成与压缩机壳体热连通。 多个热管吸收的热量被传送到压缩机壳体。

公开(公告)号：US20160290174A1

公开(公告)日：2016-10-06

申请号：US14676884

申请日：2015-04-02

Applicant: General Electric Company

Inventor： Sanji Ekanayake ,  Alston Ilfrod Scipio ,  Joseph Paul Rizzo

IPC: F01K23/10 ,  F02C3/04

CPC classification number: F01K23/10 ,  F02C3/04 ,  F02C6/18 ,  F02C7/141 ,  F02C7/143 ,  F02C7/224 ,  F05D2260/205 ,  F05D2260/208 ,  F05D2260/213 ,  Y02E20/16

Abstract: A turbomachine includes a compressor having an intake portion and an outlet portion. The compressor compresses air received at the intake portion to form a compressed airflow that exits into the outlet portion. A combustor is operably connected with the compressor, and the combustor receives the compressed airflow. A turbine is operably connected with the combustor, and the turbine receives combustion gas flow from the combustor. An aftercooler is operatively connected to the outlet portion of the compressor. The aftercooler includes a plurality of heat pipes that extend into the outlet portion. The plurality of heat pipes are operatively connected to one or more manifolds. The plurality of heat pipes and the one or more manifolds are configured to transfer heat from the compressed airflow in the outlet portion to a plurality of heat exchangers.

Abstract translation: 涡轮机包括具有进气部分和出口部分的压缩机。 压缩机压缩容纳在进气部分处的空气，以形成离开出口部分的压缩气流。 燃烧器与压缩机可操作地连接，并且燃烧器接收压缩气流。 涡轮机与燃烧器可操作地连接，并且涡轮机接收来自燃烧器的燃烧气体流。 后冷却器可操作地连接到压缩机的出口部分。 后冷却器包括延伸到出口部分的多个热管。 多个热管可操作地连接到一个或多个歧管。 多个热管和一个或多个歧管被构造成将热量从出口部分中的压缩气流传递到多个热交换器。