公开(公告)号：US20230323815A1

公开(公告)日：2023-10-12

申请号：US17717402

申请日：2022-04-11

Applicant: General Electric Company

Inventor： Gregory Alexander Natsui ,  Giridhar Jothiprasad ,  Lana Maria Osusky ,  Thomas Malkus

IPC: F02C7/18 ,  F01D25/12 ,  F02C7/141

CPC classification number: F02C7/18 ,  F01D25/12 ,  F05D2260/213 ,  F05D2220/32 ,  F02C7/141

Abstract: A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.

公开(公告)号：US11781445B2

公开(公告)日：2023-10-10

申请号：US17420818

申请日：2020-03-04

Applicant: Mitsubishi Power, Ltd.

Inventor： Tetsuya Shimmyo ,  Shunsuke Torii ,  Masanori Yuri ,  Naoya Tatsumi ,  Shingo Yamasue

IPC: F01D25/24 ,  F01D25/12 ,  F02C7/18

CPC classification number: F01D25/12 ,  F01D25/24 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/14 ,  F05D2260/201

Abstract: According to an embodiment, a turbine casing comprises a cooling air supply unit configured to supply a cooling air to an interior space of a casing of a gas turbine, and the cooling air supply unit includes: a first supply unit disposed in an upper half of the casing so as to face a first region and configured to supply the cooling air to the first region, where the first region is a region on a radially outer side of a plurality of combustors arranged annularly around a rotor; and a second supply unit disposed so as to face a second region and configured to supply the cooling air to the second region, where the second region is a region on a radially inner side of the plurality of combustors.

公开(公告)号：US20230313741A1

公开(公告)日：2023-10-05

申请号：US17706814

申请日：2022-03-29

Applicant: General Electric Company

Inventor： Eyitayo James Owoeye ,  Scott Alan Schimmels

IPC: F02C7/18 ,  F01D25/12

CPC classification number: F02C7/185 ,  F01D25/125 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/2214 ,  F05D2260/606

Abstract: An air-to-air heat exchanger in flow communication with a gas turbine engine is provided. The air-to-air heat exchanger has an air-to-air heat exchanger potential defined by a product raised to a half power, the product being a heat transfer surface area density associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine. The air-to-air heat exchanger potential is between about 6.7 and 19.5 for a bypass ratio associated with the gas turbine engine between about 3 and 10 and the heat transfer surface area density being between about 3,000 m2/m3 and 10,000 m2/m3 and is between about 2.9 and 12.2 for a bypass ratio associated with the gas turbine engine between about 10 and 20 and the heat transfer surface area density being between about 1,000 m2/m3 and 10,000 m2/m3.

公开(公告)号：US20230313707A1

公开(公告)日：2023-10-05

申请号：US18320564

申请日：2023-05-19

Applicant: GE Avio S. r. l.

Inventor： Pietro Molesini ,  Alberto Frezet ,  Saypen Baraggia Au Yeung

IPC: F01D25/20 ,  F01D25/12 ,  F01M5/00 ,  F01M11/00 ,  F16H57/04 ,  F02C7/06

CPC classification number: F01D25/20 ,  F01D25/12 ,  F01M5/007 ,  F01M11/00 ,  F16H57/0412 ,  F16H57/0482 ,  F02C7/06 ,  F01M2250/60 ,  F01M1/02

Abstract: A lubricant system for supplying lubrication to a component in a turbine engine includes a lubricant reservoir, a supply line fluidly coupling the lubricant reservoir to the component in the turbine engine, a scavenge line fluidly coupling the component to the lubricant reservoir, and a bypass line fluidly coupling the supply line to the scavenge line and bypassing the component.

公开(公告)号：US11773736B2

公开(公告)日：2023-10-03

申请号：US17755426

申请日：2019-10-29

Applicant: ORGANOWORLD INC.

Inventor： Frederick Churchill

IPC: F01D9/04 ,  F02C7/055 ,  F01D25/12

CPC classification number: F01D9/041 ,  F01D25/12 ,  F02C7/055 ,  F05D2220/323 ,  F05D2220/80 ,  F05D2240/11 ,  F05D2240/128 ,  F05D2250/323 ,  F05D2250/511 ,  F05D2260/607

Abstract: A segmented augmented turbine assembly for generating electricity from a fluid in motion, the assembly comprising a segmented annular ducted channel extending between an inlet receiving the fluid and an outlet, the channel comprising a convergent accelerating the fluid, a segmented turbine-rotor section comprising blades and guide vanes rotating about a central shaft coupled to a generator, and a diffuser section configured to decelerate the fluid, wherein the channel comprises solid inserts attached to an outside face of the turbine-rotor section, the flow stream passing through open flow-through segments positioned between the solid inserts.

公开(公告)号：US20230296025A1

公开(公告)日：2023-09-21

申请号：US18067961

申请日：2022-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter T. IRELAND ,  John COULL ,  João António Coelho VIEIRA

IPC: F01D5/18 ,  F01D25/12

CPC classification number: F01D5/186 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/202

Abstract: A turbine blade includes an aerofoil including a leading edge, a trailing edge, a first sidewall, a second sidewall, and an internal cooling circuit disposed within the aerofoil and configured to direct a cooling fluid within the aerofoil. The turbine blade includes at least one first recessed portion formed on the first sidewall proximal to a tip of the turbine blade. The first recessed portion is disposed proximal to and spaced apart from the trailing edge of the aerofoil. The first recessed portion includes a base surface, a first surface, and a second surface. The first recessed portion further includes at least one slot extending from the first surface to the internal cooling circuit. The slot is configured to allow a flow of the cooling fluid from the internal cooling circuit to the first recessed portion.

公开(公告)号：US20230296023A1

公开(公告)日：2023-09-21

申请号：US18006536

申请日：2021-07-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Matthieu SIMON ,  Ulysse Jacques Bernard DANTENY

IPC: F01D5/08 ,  F01D1/26 ,  F01D25/12

CPC classification number: F01D5/08 ,  F01D1/26 ,  F01D25/12 ,  F05D2250/44

Abstract: A turbine has a first rotor and a second rotor configured to pivot about a longitudinal axis (X) according to two opposite directions of rotation. The first rotor has a radially outer drum from which bladesextend radially inwards. The first rotorand the second rotor are surrounded by a stator annular part. The stator annular partdelimits, with the drum, at least one upstream annular cavityand one downstream annular cavityseparated from each other by sealing means.

公开(公告)号：US11761347B2

公开(公告)日：2023-09-19

申请号：US18148504

申请日：2022-12-30

Applicant: General Electric Company

Inventor： Mithun Raj K K ,  Veerraju Chennoju

IPC: F01D25/12 ,  F01D25/14 ,  F01D9/06 ,  F01D25/28

CPC classification number: F01D25/125 ,  F01D9/065 ,  F01D25/14 ,  F01D25/28 ,  F05D2220/32 ,  F05D2260/232 ,  F05D2260/60 ,  F05D2270/303

Abstract: The present application provides an exhaust frame differential cooling system of a gas turbine engine to mitigate a temperature differential along a compressor and/or a turbine to minimize centerline eccentricity of a shaft. The exhaust frame differential cooling system may include a number of compressor temperature sensors positioned about the compressor and/or a number of turbine temperature sensors positioned about the turbine, an exhaust frame including an inner barrel with a bearing tunnel for the shaft, an outer barrel, and a number of struts extending from the inner barrel to the outer barrel, a blower, and a cooling air metering system that provides cooling air from the blower to the bearing tunnel and through the inner barrel, the struts, and the outer barrel in response to the temperature differential being determined along the compressor and/or the turbine.

公开(公告)号：US20230279811A1

公开(公告)日：2023-09-07

申请号：US17684772

申请日：2022-03-02

Applicant: General Electric Company

Inventor： Eyitayo James Owoeye

IPC: F02C7/18 ,  F01D25/12

CPC classification number: F02C7/185 ,  F01D25/125 ,  F05D2250/312 ,  F05D2250/313 ,  F05D2260/213 ,  F05D2260/2214 ,  F05D2260/232 ,  F05D2260/2212

Abstract: A heat exchanger is provided. The heat exchanger includes one or more exchanger units that each have a core and manifolds. The core of an exchanger unit is formed by multiple unit cells coupled together in flow communication to create a flow distribution grid. Each unit cell has at a first primary channel, a second primary channel, a first secondary channel in flow communication with the first primary channel, and a second secondary channel in flow communication with the second primary channel. The first secondary channel traverses through the second primary channel and the second secondary channel traverses through the first primary channel. Each manifold includes two chambers for separating fluids flowing through the heat exchanger, with one chamber being in flow communication with one of the primary channels and having one or more tubes traversing therethrough to provide flow communication between the other primary channel and the other chamber.

公开(公告)号：US11739691B2

公开(公告)日：2023-08-29

申请号：US16022658

申请日：2018-06-28

Applicant: Raytheon Technologies Corporation

Inventor： Benjamin Heneveld

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

CPC classification number: F02C7/18 ,  F01D25/12 ,  F02C7/12 ,  F05D2260/2212

Abstract: A combustion engine component is disclosed. The combustion engine component comprises a body that includes a first surface in operative thermal communication with a hot combustion gas, and a second surface in operative fluid communication with a cooling fluid. Also, as disclosed in greater detail below, the second surface includes a first surface contour feature configured to increase a contact angle of a liquid on the second surface.