公开(公告)号：US11702992B2

公开(公告)日：2023-07-18

申请号：US17541758

申请日：2021-12-03

Applicant: Raytheon Company

Inventor： Julian Winkler ,  Kenji Homma ,  Craig A. Reimann ,  Jeffrey M. Mendoza

IPC: F23R3/00 ,  F02C7/24 ,  F02C7/16

CPC classification number: F02C7/24 ,  F02C7/16 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00014

Abstract: An engine assembly includes a combustor wall with a first skin, a second skin, a core and a sound attenuation passage. The first skin forms a peripheral boundary of a combustion volume on a first side of the combustor wall. The second skin forms a peripheral boundary of a plenum on a second side of the combustor wall. The core includes a plurality of resonator elements between the first skin and the second skin. A first resonator element includes a first base and a plurality of first protrusions projecting out from the first base. Each first protrusion includes a first bore fluidly coupled with a first cavity within the first base. The sound attenuation passage extends within the core and is fluidly coupled with the combustion volume through an attenuation passage aperture in the first skin. The sound attenuation passage is fluidly decoupled from the plenum by the second skin.

公开(公告)号：US20230212949A1

公开(公告)日：2023-07-06

申请号：US17970662

申请日：2022-10-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Thomas J. Martin ,  Gajawalli V. Srinivasan ,  Paul F. Croteau ,  Matthew B. Kennedy

IPC: F01D5/18 ,  F23R3/00

CPC classification number: F01D5/186 ,  F23R3/007 ,  F05D2300/222 ,  F05D2260/202

Abstract: A gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gaspath side and an internal side that borders a cooling air cavity. The external combustion gaspath side has an associated combustion gas flow direction there along. An array of cooling holes extends through the silicon-containing ceramic wall and connects the internal side with the external combustion gaspath side. The cooling holes are oriented to discharge cooling air to the external gaspath side in a direction counter to the combustion gas flow direction.

公开(公告)号：US11692486B2

公开(公告)日：2023-07-04

申请号：US17843833

申请日：2022-06-17

Applicant: Raytheon Technologies Corporation

Inventor： Stephen K. Kramer ,  Brian Knisely ,  Eric DeShong ,  Shawn Siroka ,  Ivan Monge-Concepcion

IPC: F02C7/16 ,  B22F12/00 ,  F02C3/14 ,  F23R3/00 ,  F23R3/06 ,  B33Y50/00 ,  B22F5/00

CPC classification number: F02C7/16 ,  B22F12/00 ,  F02C3/14 ,  F23R3/002 ,  F23R3/06 ,  B22F2005/005 ,  B33Y50/00 ,  F05D2230/21 ,  F05D2240/35 ,  F23R2900/00018 ,  F23R2900/03044

Abstract: Methods for manufacturing combustor panels of gas turbine engines and combustor panels are described. The methods include defining a particle deposit near-steady state for at least a portion of a combustor panel, the particle deposit near-steady state representative of a build-up of particles on the at least a portion of the combustor panel during use, generating a template based on the defined particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles, and forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.

公开(公告)号：US20230151965A1

公开(公告)日：2023-05-18

申请号：US18157565

申请日：2023-01-20

Applicant: TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION

Inventor： Yasunori IWAI ,  Masao ITOH ,  Yuichi MORISAWA ,  Yoshihisa KOBAYASHI ,  Shinju SUZUKI

IPC: F23R3/00 ,  F02C6/00 ,  F02C7/264

CPC classification number: F23R3/002 ,  F02C6/00 ,  F02C7/264 ,  F05D2220/32 ,  F05D2240/35

Abstract: A combustor of an embodiment includes: a combustor casing; a combustor liner which is provided in the combustor casing and combusts a fuel and an oxidant to produce a combustion gas; a pipe-shaped member provided to penetrate the combustor casing and the combustor liner; a heat-resistant glass which is provided on the combustor casing side in the pipe-shaped member and closes the pipe-shaped member; a laser light supply mechanism which irradiates an interior of the combustor liner through the heat-resistant glass and an interior of the pipe-shaped member with a laser light; and a contact prevention mechanism which prevents a combustion gas in the combustor liner from coming into contact with the heat-resistant glass.

公开(公告)号：US11635211B2

公开(公告)日：2023-04-25

申请号：US16255632

申请日：2019-01-23

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

IPC: F23R3/52 ,  F23R3/00 ,  F02C7/143 ,  F02C3/04 ,  F02C7/10 ,  F02C6/12 ,  F23R3/32 ,  F02K1/00 ,  F02K1/36 ,  F02K3/10

Abstract: A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

公开(公告)号：US11614234B2

公开(公告)日：2023-03-28

申请号：US16476776

申请日：2018-01-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jacques Marcel Arthur Bunel ,  Dan-Ranjiv Joory ,  Patrice André Commaret ,  Romain Nicolas Lunel

IPC: F23R3/00 ,  F23R3/60

Abstract: A combustion chamber for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine. The combustion chamber includes a radially outer annular shroud, a radially inner annular shroud coaxial with the radially outer shroud, and an end wall connecting the radially outer shroud and the radially inner shroud. The combustion chamber further includes a first annular sealing member coaxial with said radially inner and outer shrouds. The first annular sealing member is radially interposed between the end wall and the radially outer shroud.

公开(公告)号：US11578829B2

公开(公告)日：2023-02-14

申请号：US16738873

申请日：2020-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher A. Sanchez

IPC: F16L39/00 ,  F01D5/18 ,  F02C7/22 ,  F16L9/19 ,  F23R3/28 ,  F02C7/055 ,  F23R3/00

Abstract: A fitting for forming a double-walled tube includes an inner fitting having a first inner weld lip, a second inner weld lip, and an inner body extending from the first inner weld lip to the second inner weld lip and having an outer surface with a first threading. The fitting also includes an outer fitting having a first outer weld lip, a second outer weld lip, and an outer body extending from the first outer weld lip to the second outer weld lip and having an inner surface with a second threading that is configured to mate with the first threading.

公开(公告)号：US20230044804A1

公开(公告)日：2023-02-09

申请号：US17392884

申请日：2021-08-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Tin-Cheung John HU

IPC: F23R3/00 ,  F23M5/08 ,  F02C7/18

Abstract: A combustor of an aircraft engine comprises a liner defining a primary and a dilution zone having a hot surface exposed to a flow of combustion gases traveling from the primary zone downstream to the dilution zone and a cold surface. Dilution holes extending through the liner from the cold to the hot surface delimit the primary from the dilution zone. Effusion holes extending through the liner from the cold to the hot surface direct cooling air into the dilution zone. Two or more rows of effusion holes positioned within three dilution hole diameters downstream of the dilution holes are oriented relative to the liner to direct the cooling air in a cooling direction that is at least one of normal to the direction of the flow of gases passing adjacent the effusion holes, and against the direction of the flow of gases passing adjacent the effusion holes.

公开(公告)号：US20230033194A1

公开(公告)日：2023-02-02

申请号：US17791737

申请日：2020-12-21

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： Matthias Gralki ,  Claus Krusch

IPC: F23R3/46 ,  F23R3/00

Abstract: A resonator formed as a ring for a gas turbine combustion chamber, includes an outer shell and an inner shell, wherein one part of a hot gas channel of the gas turbine combustion chamber is delimited by the inner shell, wherein at least one Helmholtz resonator is arranged between the outer shell and the inner shell.

公开(公告)号：US11549437B2

公开(公告)日：2023-01-10

申请号：US17178418

申请日：2021-02-18

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Hamdullah Ozogul ,  Atul Verma ,  Amy Kujala ,  Michael Wedig ,  Ryan Meyer ,  Bradley Culbertson

IPC: F02C7/12 ,  F23R3/00

Abstract: A combustor for a gas turbine engine includes an outer liner having a first end interconnected to an opposite second end by an outer liner wall composed of a plurality of outer segments. The inner liner has a first inner end interconnected to an opposite second inner end by an inner liner wall composed of a plurality of inner segments. The outer liner wall and the inner liner wall define a combustion chamber, and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments includes a first segment, a second segment that extends at a second angle relative to the first segment, which is less than a third angle defined between the second segment and a third segment and is substantially the same as a fourth angle defined between the third segment and a fourth segment.