公开(公告)号：US20180328177A1

公开(公告)日：2018-11-15

申请号：US15590363

申请日：2017-05-09

Applicant: General Electric Company

Inventor： Alan Glenn Turner ,  Monty Lee Shelton ,  Anand Roday ,  Aigbedion Akwara

IPC: F01D5/08 ,  F01D25/12 ,  F02C7/28

CPC classification number: F01D5/084 ,  F01D25/12 ,  F02C7/28 ,  F05D2220/3216 ,  F05D2240/55

Abstract: A gas turbine engine includes a compressor section having a high pressure compressor, the high pressure compressor including an aft-most compressor stage. The gas turbine engine also includes a combustion section having a stage of discharge nozzles, the stage of discharge nozzles located downstream of the aft-most compressor stage and upstream of a diffuser cavity. The gas turbine engine also includes a high pressure spool drivingly coupled to the high pressure compressor, the high pressure spool forming in part a compressor discharge pressure seal and including a forward spool section. The forward spool section extends between the compressor discharge pressure seal and the aft-most compressor stage, the forward spool section defining an airflow cavity for providing a cooling airflow from the diffuser cavity to the aft-most compressor stage.

公开(公告)号：US10036278B2

公开(公告)日：2018-07-31

申请号：US14665797

申请日：2015-03-23

Applicant: United Technologies Corporation

Inventor： Brad Powell ,  Chong H. Park

IPC: F01D11/02 ,  F01D25/12 ,  F01D25/14 ,  F01D5/08 ,  F01D11/00 ,  F02C7/24 ,  F01D1/02 ,  F01D5/06

CPC classification number: F01D25/12 ,  F01D1/02 ,  F01D5/06 ,  F01D5/084 ,  F01D11/001 ,  F01D11/02 ,  F01D25/145 ,  F02C7/24 ,  F05D2220/32 ,  F05D2220/3219 ,  F05D2240/12 ,  F05D2240/15 ,  F05D2240/24 ,  F05D2260/231 ,  F05D2260/31 ,  Y02T50/671 ,  Y02T50/676

Abstract: In various embodiments, a high pressure compressor may comprise a thermal shield. The thermal shield may be installed between a first rotor and a second rotor. The thermal shield may also be installed radially inward of a stator. The stator may be a shrouded stator. Moreover, the thermal shield may be configured to thermally isolate and/or reduce the thermal load associated with windage on a rotor hub.

公开(公告)号：US10012084B2

公开(公告)日：2018-07-03

申请号：US14480706

申请日：2014-09-09

Applicant: SIEMENS ENERGY, INC.

Inventor： Sachin R. Shinde ,  Phillip W. Gravett ,  Santosh Narasimhachary ,  Christopher W. Ross

IPC: F01D5/06 ,  F01D11/00 ,  B23K20/12 ,  F02C7/28 ,  F01D5/08

CPC classification number: F01D5/06 ,  B23K20/129 ,  F01D5/066 ,  F01D5/084 ,  F01D11/005 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/55

Abstract: A sealing band arrangement for a gas turbine including first and second adjoining rotor disks separated by a gap wherein the first rotor disk includes an aperture. The sealing band arrangement includes at least one seal strip segment located within the gap, wherein the seal strip segment includes a first mating surface. The sealing band arrangement further includes a block having a locking section located within the aperture to stop circumferential movement of the seal strip segment relative to the first and second disks. A tapered pin element extends through the seal strip segment and the block. The tapered pin element is friction welded to both the seal strip segment and the block to attach the block to the first mating surface of the seal strip segment.

公开(公告)号：US09869183B2

公开(公告)日：2018-01-16

申请号：US14799994

申请日：2015-07-15

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  Wesley K. Lord

IPC: F01D5/08 ,  F01D5/28

CPC classification number: F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F01D5/288 ,  Y02T50/672 ,  Y02T50/676

Abstract: A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed.

公开(公告)号：US20170211590A1

公开(公告)日：2017-07-27

申请号：US15007257

申请日：2016-01-27

Applicant: General Electric Company

Inventor： Thomas Ory Moniz ,  Joseph George Rose

IPC: F04D29/58 ,  F04D29/54 ,  F02C7/18 ,  F04D29/32

CPC classification number: F04D29/582 ,  F01D5/082 ,  F01D5/084 ,  F01D5/087 ,  F01D5/3007 ,  F02C7/18 ,  F04D29/321 ,  F04D29/542 ,  F04D29/584 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/20 ,  Y02T50/676

Abstract: In one aspect, the present disclosure is directed to a cooling circuit for a gas turbine engine. The cooling circuit includes a rotor blade having a connection portion and a rotor disc having a first axial side and a second axial side. The rotor disc defines a connection slot and a cooling passage extending between the first axial side and the second axial side. The connection slot receives the connection portion to couple the rotor blade to the rotor disc. Cooling air flows through the cooling passage.

公开(公告)号：US20160333700A1

公开(公告)日：2016-11-17

申请号：US15154322

申请日：2016-05-13

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Oliver Joseph TAHENY ,  Sven OLMES ,  Armin BUSEKROS ,  Carlos SIMON-DELGADO ,  Daniel JEMORA ,  Christophe SIMONET ,  Luca ALBERTI ,  Eugenio ROSSI

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/12 ,  F01D5/08

CPC classification number: F01D5/18 ,  F01D5/082 ,  F01D5/084 ,  F01D5/087 ,  F01D25/12 ,  F02C7/12 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/15 ,  F05D2240/30 ,  F05D2260/14 ,  F05D2260/20 ,  F05D2260/231

Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.

Abstract translation: 公开了一种用于冷却具有涡轮机的燃气轮机的方法，其中围绕机器轴线旋转的转子承载多个旋转叶片，其由叶片根部安装并且随其翼型延伸到气体的热气体路径中 涡轮。 转子同轴地被承载有多个固定叶片的涡轮叶片载体围绕，由此旋转叶片和固定叶片沿轴向方向排列成交替排列。 通过为涡轮机提供第一和第二冷却系统来实现具有外部冷却的延长的寿命。

公开(公告)号：US20160222788A1

公开(公告)日：2016-08-04

申请号：US15021374

申请日：2014-09-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew Andrew Hough ,  Jeffrey S. Beattie

IPC: F01D5/08 ,  F01D5/30 ,  F01D11/00 ,  F01D5/12

CPC classification number: F01D5/082 ,  F01D5/081 ,  F01D5/084 ,  F01D5/085 ,  F01D5/12 ,  F01D5/3007 ,  F01D5/3015 ,  F01D11/006 ,  F05D2220/32 ,  F05D2260/232

Abstract: A turbine section comprises a rotor, blade and rim seal. The rotor comprises a rim defining an outer diameter surface, and a slot in the outer diameter surface. The blade comprises an airfoil, a platform surrounding the airfoil, a shank extending from the platform, a root extending from the shank for connecting to the slot, and a nub extending from the shank beneath the platform. The rim seal is disposed between the outer diameter surface and the nub. A method for cooling an outer diameter of a rotor disk comprises bleeding cooling air in a gas turbine engine, passing the flow of cooling air through a cover plate that retains a seal plate against the rotor disk, leaking the cooing air between a rotor disk rim and the seal plate, and guiding the cooling air across an outer diameter surface of the rotor disk rim utilizing a rim seal.

Abstract translation: 涡轮机部分包括转子，叶片和轮缘密封件。 转子包括限定外径表面的边缘和外径表面中的狭槽。 叶片包括翼型件，围绕翼型的平台，从平台延伸的柄部，从柄部延伸的用于连接到狭槽的根部以及从平台下方的柄延伸的突出部。 边缘密封件设置在外径表面和凸起之间。 用于冷却转子盘的外径的方法包括使燃气涡轮发动机中的冷却空气渗出，使冷却空气流通过将密封板保持在转子盘上的盖板，使冷凝空气在转子盘轮圈 和密封板，并且利用边缘密封件将冷却空气引导到转子盘边缘的外径表面。

公开(公告)号：US20160208713A1

公开(公告)日：2016-07-21

申请号：US14597442

申请日：2015-01-15

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu

IPC: F02C9/18 ,  F02C7/18 ,  F02C3/10

CPC classification number: F02C9/18 ,  F01D5/082 ,  F01D5/084 ,  F01D5/088 ,  F01D25/12 ,  F02C3/10 ,  F02C7/18 ,  F05D2250/322 ,  F05D2260/20 ,  Y02T50/676

Abstract: A gas turbine engine includes a turbine section that includes a turbine rotor arranged in a plenum. A compressor section includes a compressor rotor assembly that has spaced apart inner and outer portions that provide an axially extending cooling channel. Compressor blades extend radially outward from the outer portion which provides an inner core flow path. A rotor spoke is configured to receive a first cooling flow and fluidly connect the outer portion to the cooling channel. The compressor rotor assembly has a coolant exit that is in fluid communication with the cooling channel. The compressor rotor assembly is configured to communicate the first cooling flow to the turbine rotor. A bleed source is configured to provide a second cooling flow. A combustor section includes an injector in fluid communication with the bleed source. The tangential onboard injector is configured to communicate the second cooling flow to the turbine rotor.

Abstract translation: 燃气涡轮发动机包括涡轮机部分，其包括布置在增压室中的涡轮机转子。 压缩机部分包括具有间隔开的内部和外部部分的压缩机转子组件，其提供轴向延伸的冷却通道。 压缩机叶片从外部径向向外延伸，该外部部分提供内部核心流动路径。 转子轮辐被构造成接收第一冷却流并将外部部分流体连接到冷却通道。 压缩机转子组件具有与冷却通道流体连通的冷却剂出口。 压缩机转子组件构造成将第一冷却流通向涡轮转子。 排出源构造成提供第二冷却流。 燃烧器部分包括与排泄源流体连通的喷射器。 切向车载喷射器构造成将第二冷却流通向涡轮转子。

公开(公告)号：US09382802B2

公开(公告)日：2016-07-05

申请号：US13556722

申请日：2012-07-24

Applicant: Christian Dombek ,  Mauro Corradi

Inventor： Christian Dombek ,  Mauro Corradi

IPC: F01D5/08 ,  F01D25/08

CPC classification number: F01D5/08 ,  F01D5/081 ,  F01D5/084 ,  F01D25/08

Abstract: A compressor rotor is provided having a rotor blade groove thereon and also includes a device for cooling the rotor in the region of a compressor rotor exit. Efficient cooling is achieved by the compressor rotor, in a compressor rotor exit region, having a ring which is pushed concentrically, and at a distance, forming a gap, over a rotor disk of the rotor, and is fastened on the disk, by the rotor blades, in the compressor rotor exit region, being inserted into corresponding grooves on the ring and being retained there, by first means for directing an axial flow of cooling medium from the compressor rotor exit through the ring, and by second means for deflecting the cooling medium which issues from the ring such that the cooling medium flows back in the axial direction through the gap between the ring and the rotor disk, encompassed by the ring.

Abstract translation: 在其上设置有转子叶片槽的压缩机转子，还包括用于在压缩机转子出口的区域中冷却转子的装置。 通过压缩机转子在压缩机转子出口区域中实现有效的冷却，该压缩机转子出口区域具有同心推动的环，并且在转子的转子盘上形成间隙一定距离，并且被固定在盘上 压缩机转子出口区域中的转子叶片被插入到环上的相应凹槽中并被保持在其中，第一装置用于引导来自压缩机转子出口的冷却介质的轴向流动通过环，以及用于使第 所述冷却介质从所述环发出，使得所述冷却介质沿所述轴向方向通过由所述环包围的所述环和所述转子盘之间的间隙而流回。

公开(公告)号：US20160131037A1

公开(公告)日：2016-05-12

申请号：US14900730

申请日：2014-07-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Ricardo Trindade

IPC: F02C7/18 ,  F02C3/04

CPC classification number: F02C7/18 ,  F01D5/081 ,  F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F01D5/088 ,  F01D9/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/12 ,  F01D25/14 ,  F02C3/04 ,  F02C6/08 ,  F05D2220/32 ,  F05D2260/205 ,  F05D2260/232 ,  F05D2270/3062 ,  Y02T50/676

Abstract: In a featured embodiment, a gas turbine engine has a compressor section having a downstream rotor and a diffuser downstream of the compressor section. A combustor receives air downstream of the diffuser. A turbine section has at least one component to be cooled. A conduit is spaced from the diffuser and defines a cooling airflow path. The cooling airflow path is separate from an airflow downstream the diffuser, and passing to the combustor. The conduit passes cooling air to the component to be cooled.

Abstract translation: 在特征实施例中，燃气涡轮发动机具有压缩机部分，该压缩机部分具有在压缩机部分下游的下游转子和扩散器。 燃烧器在扩散器的下游接收空气。 涡轮部分具有至少一个待冷却的部件。 导管与扩散器间隔开并限定冷却气流路径。 冷却气流路径与扩散器下游的气流分离，并且通过燃烧器。 导管将冷却空气传递到要冷却的部件。