公开(公告)号：US20180230841A1

公开(公告)日：2018-08-16

申请号：US15432094

申请日：2017-02-14

Applicant: General Electric Company

Inventor： Gary Michael Itzel ,  Ibrahim Sezer

IPC: F01D11/12 ,  F01D5/12 ,  F04D29/52 ,  F01D25/24 ,  F04D29/32 ,  F01D5/02

CPC classification number: F01D11/122 ,  F01D5/225 ,  F05D2250/283 ,  Y02T50/673

Abstract: A seal in a gas turbine for sealing a radial gap defined between rotating and stationary structure. The rotating structure may include a row of rotor blades. The seal may include a pad attached to the stationary structure. The pad may include an abradable structure. The pad may further include a liner attached to and covering an outer surface of the abradable structure. The stationary structure to which the pad is attached may define an axial section of the outer radial boundary of the annular flowpath, the axial section coinciding axially with an axial position of the row of rotor blades.

公开(公告)号：US09816388B1

公开(公告)日：2017-11-14

申请号：US15272864

申请日：2016-09-22

Applicant: General Electric Company

Inventor： Kevin Richard Kirtley ,  Ibrahim Sezer ,  Benjamin P. Lacy

IPC: F01D11/08 ,  F01D11/02 ,  F16J15/447 ,  B33Y80/00

CPC classification number: F01D11/02 ,  B22F3/1055 ,  B22F5/009 ,  B33Y80/00 ,  F01D11/127 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/31 ,  F05D2250/121 ,  F05D2250/132 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/283 ,  F05D2260/20 ,  F05D2300/514 ,  F16J15/447

Abstract: A seal in a gas turbine engine includes a shim base and a honeycomb structure having a number of cavities are formed as a single unitary structure using additive manufacturing.

公开(公告)号：US09464536B2

公开(公告)日：2016-10-11

申请号：US13654822

申请日：2012-10-18

Applicant: General Electric Company

Inventor： Xiuzhang James Zhang ,  Gary Michael Itzel ,  Ibrahim Sezer

IPC: F01D11/12 ,  F01D11/00

CPC classification number: F01D11/006 ,  F01D11/122

Abstract: A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.

Abstract translation: 涡轮机系统的密封装置包括具有外部尖端的桶，以及从外部末端径向向外延伸的至少一个铲斗脊，所述至少一个铲斗脊包含可磨损材料。 还包括从桶的外端径向向外设置的固定护罩。 还包括至少一个护罩脊，其从固定护罩朝向桶的外部末端径向向内延伸，所述至少一个护罩脊包括可磨损材料。

公开(公告)号：US20150192020A1

公开(公告)日：2015-07-09

申请号：US14150190

申请日：2014-01-08

Applicant: General Electric Company

Inventor： Anshuman Singh ,  Joe Timothy Brown ,  Ravi Meenaksh ,  Ibrahim Sezer

IPC: F01D5/18

CPC classification number: F01D11/24 ,  F01D5/187 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/294 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

Abstract: A turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a shroud mounted in one of the compressor portion and the turbine portion. The shroud includes a radial outer side, and a plurality of side surfaces. The radial outer side includes a recessed portion. A trench is formed in the recessed portion, and a cooling passage extends between the trench and at least one of the plurality of side surfaces. An airfoil component is arranged in the one of the compressor portion and the turbine portion. The airfoil component includes an airfoil portion having at least one mounting member. The at least one mounting member includes an internal cavity. A trench element is formed in the internal cavity, and a cooling passage element extends between the trench element and an external surface of the nozzle.

Abstract translation: 涡轮机包括压缩机部分，可操作地连接到压缩机部分的涡轮机部分和安装在压缩机部分和涡轮机部分之一中的护罩。 护罩包括径向外侧和多个侧表面。 径向外侧包括凹部。 在凹部中形成沟槽，并且冷却通道在沟槽和多个侧表面中的至少一个之间延伸。 在压缩机部分和涡轮部分中的一个中布置有翼型部件。 机翼部件包括具有至少一个安装部件的翼型部分。 所述至少一个安装构件包括内部空腔。 沟槽元件形成在内腔中，冷却通道元件在沟槽元件和喷嘴的外表面之间延伸。

公开(公告)号：US20150007581A1

公开(公告)日：2015-01-08

申请号：US13936583

申请日：2013-07-08

Applicant: General Electric Company

Inventor： Ibrahim Sezer ,  Anshuman Singh ,  Gary Michael Itzel ,  James William Vehr

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D11/24 ,  F05D2240/11 ,  F05D2250/191 ,  F05D2260/201 ,  F05D2260/205

Abstract: A shroud block segment for a gas turbine includes a main body having a leading portion, a trailing portion, a first side portion and an opposing second side portion that extend axially between the leading portion and the trailing portion. The main body further includes an arcuate combustion gas side, an opposing back side and a cooling chamber defined in the back side. A cooling plenum and an exhaust passage are defined within the main body where the exhaust passage provides for fluid communication out of the cooling plenum. An insert opening extends within the main body through the back side towards the cooling plenum. A cooling flow insert is disposed within the insert opening. The cooling flow insert comprises a plurality of cooling flow passages that provide for fluid communication between the cooling chamber and the cooling plenum.

Abstract translation: 用于燃气涡轮机的护罩块段包括主体，该主体具有在引导部分和后端部分之间轴向延伸的引导部分，后部部分，第一侧部分和相对的第二侧部分。 主体还包括在后侧限定的弧形燃烧气体侧，相对的后侧和冷却室。 在主体内限定有冷却气室和排气通道，其中排气通道提供流出冷却气室的流体连通。 插入开口在主体内通过后侧朝向冷却气室延伸。 冷却流动插入件设置在插入开口内。 冷却流动插入件包括多个冷却流动通道，其提供冷却室和冷却室之间的流体连通。

公开(公告)号：US11572803B1

公开(公告)日：2023-02-07

申请号：US17816574

申请日：2022-08-01

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy ,  Ibrahim Sezer ,  Brad Wilson VanTassel

IPC: F01D25/12 ,  F01D9/04

Abstract: A turbine airfoil includes a body including a wall defining pressure and suction sides, and a leading edge extending between the pressure and suction sides. A cooling circuit inside the wall of the body includes at least one of: a) a suction side to pressure side cooling sub-circuit including a first cooling passage(s) extending from the suction side to the pressure side around the leading edge to a first plenum, and a plurality of first film cooling holes communicating with the first plenum and extending through the wall on the pressure side; and b) a pressure side to suction side cooling sub-circuit including second cooling passage(s) extending from the pressure side to the suction side around the leading edge to a second plenum, and a plurality of second film cooling holes communicating with the second plenum and extending through the wall on the suction side.

公开(公告)号：US20210246829A1

公开(公告)日：2021-08-12

申请号：US16786250

申请日：2020-02-10

Applicant: General Electric Company

Inventor： Jason Ray Gregg ,  Christopher William Kester ,  Christopher Paul Cox ,  David Martin Johnson ,  Ibrahim Sezer

IPC: F02C7/18 ,  F01D25/12

Abstract: A turbine shroud for turbine systems may include a forward end including a first hook coupled to the turbine casing, an aft end including a second hook coupled to the turbine casing, and a base portion extending between the forward end and the aft end. The base portion may include an inner surface facing a hot gas flow path for the turbine system. Also, the turbine shroud may include a flange extending from the aft end and positioned radially between the base portion and the second hook, a cooling passage positioned within the base portion, adjacent the inner surface, and at least one aft end exhaust conduit in fluid communication with the cooling passage. The aft end exhaust conduit(s) may extend through the aft end, radially between the base portion and the flange.

公开(公告)号：US10989068B2

公开(公告)日：2021-04-27

申请号：US16040062

申请日：2018-07-19

Applicant: General Electric Company

Inventor： Travis J Packer ,  Benjamin Paul Lacy ,  Ibrahim Sezer ,  Zachary John Snider ,  Brad Wilson VanTassel

IPC: F01D25/12 ,  F01D11/08

Abstract: Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.

公开(公告)号：US10975724B2

公开(公告)日：2021-04-13

申请号：US16175413

申请日：2018-10-30

Applicant: General Electric Company

Inventor： Ibrahim Sezer ,  Benjamin Paul Lacy ,  Thomas James Brunt ,  Jason Ray Gregg

IPC: F01D25/14

Abstract: A rotary machine includes a rotatable member and a casing extending circumferentially over the rotatable member. The casing includes first and second target impingement surfaces. The cooling system includes first and second impingement plates. The first impingement plate is positioned over the first target impingement surface and at least a portion of the second target impingement surface. The first impingement plate defines a plurality of first impingement holes configured to channel a first flow of cooling fluid toward the first target impingement surface. The second impingement plate is positioned over the second target impingement surface. The second impingement plate defines a plurality of second impingement holes configured to channel a second flow of cooling fluid toward the second target impingement surface. A thickness of the casing in the first target impingement surface is different than a thickness of the casing in the second target impingement surface.

公开(公告)号：US10519861B2

公开(公告)日：2019-12-31

申请号：US15343369

申请日：2016-11-04

Applicant: General Electric Company

Inventor： Daniel Robert Burnos ,  Ibrahim Sezer

IPC: F01D25/12 ,  F02C7/12 ,  F02C3/04 ,  F01D11/08

Abstract: A cooled structure of a gas turbine engine having a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and are arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and are arranged along the second side portion. Each set of cooling air micro-channels has at least one transition manifold in fluid communication with an adjacent micro-channel and also in fluid communication with at least one of an intake end, an exhaust end, and mixtures thereof. The cooled structure described above is also embodied in a gas turbine.