公开(公告)号：US20140338333A1

公开(公告)日：2014-11-20

申请号：US13898275

申请日：2013-05-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Mark Matwey

IPC: F02C7/057

CPC classification number: F02C7/057 ,  B64C21/04 ,  B64C2230/12 ,  F01D5/145 ,  F04D29/2272 ,  F04D29/684 ,  F04D29/687 ,  F05D2220/50 ,  F05D2250/232 ,  F05D2270/17 ,  F05D2270/172 ,  F15D1/008 ,  F15D1/0095

Abstract: Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure.

Abstract translation: 提供了一种燃气轮机发动机（“GTE”）的实施例，这些等离子体流量控制进气系统用于在GTE上部署。 在一个实施例中，GTE包括涡轮部分，涡轮部分上游的燃烧部分，燃烧部分上游的压缩机部分和压缩机部分上游的进气部分。 进气部分包括一个增压室，一个流体连接到集气室的第一入口，以及一个流入阻尼的结构，该流动阻塞结构突出到通风室中，并且具有外部表面，该外部表面在GTE运行期间通过第一入口引导进入通风室。 等离子体致动器的第一阵列设置在阻流结构上，并且当被激活时，抑制在阻流结构的外表面上流动的空气的涡流脱落。

公开(公告)号：US20180195729A1

公开(公告)日：2018-07-12

申请号：US15403286

申请日：2017-01-11

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  David K. Jan ,  Mark Matwey

IPC: F23R3/42 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F23R3/26

CPC classification number: F23R3/425 ,  F01D9/023 ,  F01D9/026 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2220/50 ,  F05D2240/35 ,  F05D2260/205 ,  F05D2260/22141 ,  F23R3/26 ,  Y02T50/675

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

公开(公告)号：US09377030B2

公开(公告)日：2016-06-28

申请号：US13853951

申请日：2013-03-29

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Mark Matwey ,  Mahmoud Mansour ,  Yogendra Y. Sheoran

IPC: F04D29/42 ,  F04D29/68 ,  F04D27/02 ,  F04D29/44

CPC classification number: F04D29/4213 ,  F04D27/0207 ,  F04D29/441 ,  F04D29/444 ,  F04D29/682 ,  F05D2250/51

Abstract: Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system. The impeller shroud recirculation system includes an impeller shroud extending around at least a portion of the impeller and having a shroud port therein. A shroud port cover circumscribes at least a portion of the shroud port and cooperates therewith to at least partially define an impeller recirculation flow path. The impeller recirculation flow path has an outlet positioned to discharge airflow into the main intake plenum at a location radially outboard of the shroud port when pressurized air flows from the impeller, through the shroud port, and into the impeller recirculation flow path during operation of the turbomachine.

Abstract translation: 提供涡轮机例如燃气轮机的实施例。 在一个实施例中，涡轮机包括叶轮，与叶轮的入口流体连通的主进气室和叶轮罩再循环系统。 叶轮护罩再循环系统包括围绕叶轮的至少一部分延伸并且其中具有护罩端口的叶轮护罩。 护罩端口盖限定护罩端口的至少一部分并与其配合以至少部分地限定叶轮再循环流动路径。 叶轮再循环流动路径具有一个出口，该出口定位成当加压空气从叶轮通过护罩端口流动并进入叶轮再循环流动路径时，在外壳端口的径向外侧的位置处将气流排放到主进气通风室中 涡轮机

公开(公告)号：US09359950B2

公开(公告)日：2016-06-07

申请号：US13898275

申请日：2013-05-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Mark Matwey

IPC: F01D5/14 ,  F04D29/22 ,  F04D29/68 ,  B64C21/04 ,  F15D1/00 ,  F02C7/057

CPC classification number: F02C7/057 ,  B64C21/04 ,  B64C2230/12 ,  F01D5/145 ,  F04D29/2272 ,  F04D29/684 ,  F04D29/687 ,  F05D2220/50 ,  F05D2250/232 ,  F05D2270/17 ,  F05D2270/172 ,  F15D1/008 ,  F15D1/0095

Abstract: Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure.

Abstract translation: 提供了一种燃气轮机发动机（“GTE”）的实施例，这些等离子体流量控制进气系统用于在GTE上部署。 在一个实施例中，GTE包括涡轮部分，涡轮部分上游的燃烧部分，燃烧部分上游的压缩机部分和压缩机部分上游的进气部分。 进气部分包括一个增压室，一个流体连接到集气室的第一入口，以及一个流入阻尼的结构，该流动阻塞结构突出到通风室中，并且具有外部表面，该外部表面在GTE运行期间通过第一入口引导进入通风室。 等离子体致动器的第一阵列设置在阻流结构上，并且当被激活时，抑制在阻流结构的外表面上流动的空气的涡流脱落。

公开(公告)号：US20200182471A1

公开(公告)日：2020-06-11

申请号：US16736199

申请日：2020-01-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  David K. Jan ,  Mark Matwey

IPC: F23R3/42 ,  F02C7/18 ,  F23R3/26 ,  F02C3/04 ,  F01D25/12 ,  F01D11/08 ,  F01D9/02 ,  F23R3/52

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

公开(公告)号：US20140294564A1

公开(公告)日：2014-10-02

申请号：US13853951

申请日：2013-03-29

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Mark Matwey ,  Mahmoud Mansour ,  Yogendra Y. Sheoran

IPC: F04D29/42 ,  F04D29/44

CPC classification number: F04D29/4213 ,  F04D27/0207 ,  F04D29/441 ,  F04D29/444 ,  F04D29/682 ,  F05D2250/51

Abstract: Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system. The impeller shroud recirculation system includes an impeller shroud extending around at least a portion of the impeller and having a shroud port therein. A shroud port cover circumscribes at least a portion of the shroud port and cooperates therewith to at least partially define an impeller recirculation flow path. The impeller recirculation flow path has an outlet positioned to discharge airflow into the main intake plenum at a location radially outboard of the shroud port when pressurized air flows from the impeller, through the shroud port, and into the impeller recirculation flow path during operation of the turbomachine.

Abstract translation: 提供涡轮机例如燃气轮机的实施例。 在一个实施例中，涡轮机包括叶轮，与叶轮的入口流体连通的主进气室和叶轮罩再循环系统。 叶轮护罩再循环系统包括围绕叶轮的至少一部分延伸并且其中具有护罩端口的叶轮护罩。 护罩端口盖限定护罩端口的至少一部分并与其配合以至少部分地限定叶轮再循环流动路径。 叶轮再循环流动路径具有一个出口，该出口定位成当加压空气从叶轮通过护罩端口流动并进入叶轮再循环流动路径时，在外壳端口的径向外侧的位置处将气流排放到主进气通风室中 涡轮机。

公开(公告)号：US11293292B2

公开(公告)日：2022-04-05

申请号：US16736199

申请日：2020-01-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  David K. Jan ,  Mark Matwey

IPC: F01D9/02 ,  F23R3/52 ,  F23R3/42 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F23R3/26 ,  F02C7/18

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

公开(公告)号：US10655859B2

公开(公告)日：2020-05-19

申请号：US15403286

申请日：2017-01-11

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  David K. Jan ,  Mark Matwey

IPC: F23R3/52 ,  F23R3/42 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F23R3/26 ,  F02C7/18

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.