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公开(公告)号：US20180209300A1
公开(公告)日：2018-07-26
申请号：US15411592
申请日：2017-01-20
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Nicholas R. Dinsmore , Daniel Tyler Jarboe
CPC classification number: F01D9/065 , F01D11/001 , F01D11/06
Abstract: A turbine interstage structure for a gas turbine engine that includes a first stage disk and a second stage disk. A central plenum is defined by a an inner band for supporting nozzle vanes, a forward stator plate and an aft stator plate wherein the forward stator plate is spaced-apart from the aft stator plate, and an inner boundary. A forward mid-seal positioned between the inner boundary and the forward stator plate. An aft mid-seal positioned between the inner boundary and the aft stator plate; and wherein the inner boundary is a solid annular component.
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公开(公告)号：US12123350B2
公开(公告)日：2024-10-22
申请号：US17190076
申请日：2021-03-02
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Nicholas M. Daggett , Steven Douglas Johnson , Anand P. Roday , Scott Alan Schimmels
CPC classification number: F02C7/18 , F02C7/14 , F02C7/047 , F02K3/077 , F05D2240/12 , F05D2260/213
Abstract: A three-stream engine is provided. The three-stream engine includes a fan section, a core engine disposed downstream of the fan section, and a core cowl annularly encasing the core engine and at least partially defining a core duct. A fan cowl is disposed radially outward from the core cowl and annularly encasing at least a portion of the core cowl. The fan cowl at least partially defining an inlet duct and a fan duct. The fan duct and the core duct at least partially co-extending axially on opposite sides of the core cowl. A heat exchanger disposed within the fan duct. The heat exchanger provides for thermal communication between a fluid flowing through fan duct and a motive fluid flowing through the heat exchanger.
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公开(公告)号：US12116896B1
公开(公告)日：2024-10-15
申请号：US18189408
申请日：2023-03-24
Applicant: General Electric Company
Inventor： Grant Robert Portune , Steven Douglas Johnson , Mallikarjun Metri , Ajith Jogi , Pratish Patil , Nageswar Rao Ganji , Rahul Anil Bidkar , Prateek Jalan , Ravindra Shankar Ganiger , David Raju Yamarthi , Narendra Anand Hardikar , Chandrashekhar Kandukuri
CPC classification number: F01D11/001 , F01D11/025 , F01D11/04 , F01D25/22 , F16J15/40 , F16J15/445 , F16J15/164
Abstract: A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments, the plurality of seal segments having a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprises a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine.
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公开(公告)号：US20240133308A1
公开(公告)日：2024-04-25
申请号：US18315736
申请日：2023-05-10
Applicant: General Electric Company
Inventor： David Yamarthi , Prateek Jalan , Grant Portune , Steven Douglas Johnson , Mark L. Hopper , Richard A. Wesling , Ravindra Shankar Ganiger
CPC classification number: F01D11/001 , F01D11/025
Abstract: A rotary machine, such as a turbomachine of a gas turbine engine, for example, including a rotor and a rotor seal assembly. The rotor is rotatable about a rotational axis and has a rotor seal face. The rotor seal assembly includes a seal body, one or more primary fluid conduits formed in the seal body, and a retraction assembly. The seal body has a seal face and is positionable to form a fluid-bearing gap between the seal face of the seal body and the rotor seal face. The one or more primary fluid conduits are fluidly connected to the fluid-bearing gap to supply a fluid to the fluid-bearing gap. The retraction assembly is connected to the seal body to move the seal body in a retraction direction away from the rotor seal face.
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公开(公告)号：US20240133303A1
公开(公告)日：2024-04-25
申请号：US17970918
申请日：2022-10-20
IPC: F01D9/04
CPC classification number: F01D9/041 , F05D2240/128 , F05D2250/323 , F05D2250/38 , F05D2260/2212 , F05D2260/606 , F05D2260/97
Abstract: A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.
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Patent Agency Ranking
公开(公告)号：US20230383670A1
公开(公告)日：2023-11-30
申请号：US17385331
申请日：2021-07-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Rahul Anil Bidkar , Steven Douglas Johnson , Uttara Vijay Kumar , Randy Thomas Antelo , Keith William Gary
IPC: F01D11/02
CPC classification number: F01D11/025 , F05D2220/32 , F05D2240/55
Abstract: A turbine engine comprising an engine core having a rotor and a stator, and a floating seal assembly sealing at least portions of the rotor and the stator relative to a higher-pressure area and a lower-pressure area. The floating seal assembly can comprise a carriage assembly at least partially defining a seal cavity and a seal body floating within the seal cavity. The floating seal assembly can further include at least one of a seal located between the seal body and the carriage assembly, and a seal face located between the seal body and the carriage assembly.
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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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公开(公告)号：US20230059027A1
公开(公告)日：2023-02-23
申请号：US17409106
申请日：2021-08-23
Applicant: General Electric Company
Inventor： Steven Douglas Johnson
IPC: F01D5/18
Abstract: A gas turbine engine defining an axial direction and a radial direction, and including a primary cooling circuit configured to receive a first flow of air; and a turbine rotor comprising a rotor blade, the rotor blade defining at least in part a forward wheelspace that is located forward of the rotor blade, the forward wheelspace configured to receive a second flow of air, the rotor blade further defining: a first cooling circuit internal to the rotor blade and in fluid communication with the primary cooling circuit for receiving the first flow of air from the primary cooling circuit; a second cooling circuit internal to the rotor blade and in fluid communication with the forward wheelspace for receiving a portion of the second flow of air from the forward wheelspace; and a means for drawing a portion of the second flow of air into the second cooling circuit.
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公开(公告)号：US20220154644A1
公开(公告)日：2022-05-19
申请号：US17098998
申请日：2020-11-16
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Jonathan Russell Ratzlaff
Abstract: A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.
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