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公开(公告)号：US12286932B1
公开(公告)日：2025-04-29
申请号：US18441736
申请日：2024-02-14
Applicant: General Electric Company
Inventor： Hejie Li , Hiranya Nath , Habeeb Kunnummal Manat , Shai Birmaher , Craig Alan Gonyou , Anquan Wang , Michael A. Benjamin
Abstract: A combustor of a turbine engine has a combustion chamber for combusting fuel and air, generating heat. A fuel nozzle-mixer assembly mixes and injects fuel and air into the combustion chamber for combustion. The assembly has a heat shield at an aft end for shielding the assembly from the heat. A centerbody outer shell defines a cooling air flow cavity. A cooling air flow gap is defined between the centerbody outer shell and the heat shield. The centerbody outer shell has cooling air exit holes between the cooling air flow cavity and the cooling air flow gap, the air passing through the cooling air exit holes and into the cooling air flow gap. The cooling air exits the cooling air flow gap at a cooling air exit angle, the cooling air exit angle having a non-zero axially aft component, displacing the combustion downstream, to protect the assembly.
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公开(公告)号：US11998974B2
公开(公告)日：2024-06-04
申请号：US17898751
申请日：2022-08-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Craig Alan Gonyou , Daniel Lee Durstock , Kevin R. Feldmann , Kirk Douglas Gallier , William C. Herman , Nicholas Charles Gentilli
IPC: B22C9/10
CPC classification number: B22C9/10
Abstract: A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:
(
D
1
eq
min
D
2
eq
min
)
(
R
D
2
eq
min
)
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公开(公告)号：US20230340889A1
公开(公告)日：2023-10-26
申请号：US17845213
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Mehmet Cem Apaydin , Craig Alan Gonyou , Scott Alan Schimmels , Christopher Michael Thompson
CPC classification number: F01D21/003 , G01M15/14 , F02C3/04 , F05D2270/3015
Abstract: A turbine engine includes a pressurized fluid source, a duct system comprising a plurality of ducts in fluid communication with the pressurized fluid source, and a duct failure detection system. The duct failure detection system includes a plurality of pressure sensors. Each of the plurality of pressure sensors is in operable communication with two ducts of the plurality of ducts. Each of the plurality of ducts has at least two pressure sensors of the plurality of pressure sensors in operable communication therewith.
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公开(公告)号：US11674396B2
公开(公告)日：2023-06-13
申请号：US17389503
申请日：2021-07-30
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Jonathan Russell Ratzlaff , Craig Alan Gonyou
CPC classification number: F01D5/085 , F01D9/065 , F01D25/12 , F02C7/185 , F05D2240/35 , F05D2260/213 , F05D2260/2212 , F05D2260/232 , F05D2260/607
Abstract: A gas turbine engine includes a combustion section, a turbine section, and a compressor section. The combustion section includes a combustor casing, a combustor, a cooling duct, and an outer duct. The combustor casing defines at least in part a diffuser cavity and a fluid inlet. The combustor disposed is in the diffuser cavity. The cooling duct is in fluid communication with the fluid inlet in the combustor casing and is configured to transport a flow of cooled air. The outer duct surrounds at least a portion of the cooling duct and extends along a portion of an entire length of the cooling duct. The outer duct defines a gap with the cooling duct and is configured to transport a flow of buffer air. The turbine section is disposed downstream from the combustion section. The cooling duct is in fluid communication with the turbine section.
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公开(公告)号：US20230066740A1
公开(公告)日：2023-03-02
申请号：US17461113
申请日：2021-08-30
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Yu-Liang Lin , Craig Alan Gonyou , Scott Alan Schimmels , Jeffrey Douglas Rambo , Brian Gregg Feie
Abstract: A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.
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Patent Agency Ranking
公开(公告)号：US20220268443A1
公开(公告)日：2022-08-25
申请号：US17663079
申请日：2022-05-12
Applicant: General Electric Company
Inventor： Andrew Scott Bilse , Craig Alan Gonyou , Paul Christopher Schilling , Hojjat Nasr , Ryan Christopher Jones , Donald Lee Gardner
Abstract: A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.
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公开(公告)号：US11242804B2
公开(公告)日：2022-02-08
申请号：US15622262
申请日：2017-06-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Craig Alan Gonyou , Nathan Joel Mullenix , Fei Huang
Abstract: A leakage management assembly for an orifice configured to limit a flow of at least one of a leakage fluid and a cooling fluid past an instrument positioned within the orifice are provided. The leakage management assembly includes a labyrinth ferrule including an annular ferrule body having a central bore extending therethrough. The labyrinth ferrule further includes an annular assembly cone formed at a first end of the labyrinth ferrule. The annular assembly cone includes an annular convergent lip and is configured to facilitate directing the instrument into the central bore. The labyrinth ferrule also includes a plurality of labyrinthine annular restrictions extending from a radially inner surface of the annular body toward the central bore. A combustor and a gas turbine engine including such a seal assembly are also provided.
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公开(公告)号：US20210199051A1
公开(公告)日：2021-07-01
申请号：US16730570
申请日：2019-12-30
Applicant: General Electric Company
Inventor： Craig Alan Gonyou , Robert Proctor , Christopher Michael Thompson , Scott Alan Schimmels , Steven Douglas Johnson
IPC: F02C7/18
Abstract: An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.
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公开(公告)号：US10907501B2
公开(公告)日：2021-02-02
申请号：US16106641
申请日：2018-08-21
Applicant: General Electric Company
Inventor： Sergio Filippi , Ryan Nicholas Porter , Craig Alan Gonyou , Scott Alan Schimmels
Abstract: Shroud assemblies and methods for cooling gas turbine engine shrouds are provided. For example, a shroud assembly comprises a shroud segment having hot and cold side portions. The hot side portion faces a gas flow path, and the cold side portion faces a cooling fluid flow path. The shroud assembly further comprises a shroud hanger for mounting the shroud segment in the gas turbine engine. The shroud hanger includes a conduit for receipt of a flow of cooling fluid that defines an outlet configured for the flow of cooling fluid to exit the conduit substantially tangential to the cold side portion of the shroud segment. The shroud and shroud hanger together define an annular cavity that forms the cooling fluid flow path, and fluid exits a plurality of conduits defined in the shroud hanger into the cavity substantially tangential to the shroud cold side to cool the shroud cold side.
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公开(公告)号：US20190162117A1
公开(公告)日：2019-05-30
申请号：US15823732
申请日：2017-11-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Anquan Wang , Hojjat Nasr , Craig Alan Gonyou , Michael Anthony Benjamin
Abstract: A combustor assembly for a turbine engine and method for cooling a portion of the combustor assembly, the combustor assembly comprising a combustor liner defining a combustion chamber with an inlet and an outlet, a fuel dome located in the inlet and having a wall adjacent at least a portion of the combustor liner, and a deflector overlying and spaced from at least a portion of the wall.
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