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公开(公告)号：US20240318613A1
公开(公告)日：2024-09-26
申请号：US18680469
申请日：2024-05-31
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberley Simpson , Syed Arif Khalid , Jeffrey S. Spruill , Daniel Lawrence Tweedt , William Joseph Solomon , Kevin Edward Hinderliter
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
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公开(公告)号：US20240295224A1
公开(公告)日：2024-09-05
申请号：US18656056
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan blades include a composite blade including a composite airfoil section having an airfoil leading edge and an airfoil trailing edge, a root attached to the composite airfoil section, and a blade shank therebetween. A metallic leading edge shield covers an axially extending portion of the composite airfoil section including at least a portion of the airfoil leading edge and covers a radially and chordwise extending portion of the airfoil leading edge of the blade shank. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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公开(公告)号：US20240288002A1
公开(公告)日：2024-08-29
申请号：US18656067
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The annular casing is formed at least partially of a composite material. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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公开(公告)号：US10883515B2
公开(公告)日：2021-01-05
申请号：US15601674
申请日：2017-05-22
Applicant: General Electric Company
Inventor： David Paul Lurie , Sherif Alykadry Abdelfattah , Michael Julian Castillo , Anthony Louis DiPietro, Jr. , Aspi Rustom Wadia , Eric Andrew Falk , William Joseph Solomon , Andrew Breeze-Stringfellow
Abstract: An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a row of vane pairs including a first row of main vanes extending radially inwardly from a stationary casing member and spaced circumferentially about a first axial location of the stationary casing member. The apparatus also includes a second row of auxiliary vanes extending radially inwardly from the stationary casing member and spaced circumferentially about a second axial location of the stationary casing member. The apparatus also includes a flow channel defined between a pressure side of each auxiliary vane and a suction side of an adjacent main vane proximate a leading edge of the adjacent main vane.
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公开(公告)号：US20240318661A1
公开(公告)日：2024-09-26
申请号：US18678321
申请日：2024-05-30
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Aaron J. King
CPC classification number: F04D29/384 , F04D19/002
Abstract: A gas turbine engine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, a core turbine engine drivingly coupled to the fan and comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, and a variable bleed assembly comprising a variable bleed duct extending between a VB inlet and a VB outlet. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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Patent Agency Ranking
公开(公告)号：US20240301889A1
公开(公告)日：2024-09-12
申请号：US18667278
申请日：2024-05-17
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Aaron J. King
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, and an airfoil. The fan includes fan blades that extend radially outwardly toward the annular casing. The airfoil includes a composite core having a pressure sidewall and a suction sidewall extending between a core leading edge and a core trailing edge and a leading edge protective wrap. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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公开(公告)号：US10823067B2
公开(公告)日：2020-11-03
申请号：US15152202
申请日：2016-05-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Mohammed El Hacin Sennoun , William Joseph Solomon , Kyle Louis Miller
Abstract: The heat exchanger assembly includes a first conduit, an external surface, and a set of fins. The first conduit includes a first inlet, a first outlet, and a first internal flow path extending between the first inlet and first outlet. The first conduit is configured to channel a flow of fluid to be cooled from the first inlet to the first outlet. The external surface which includes a plurality of regions. Each region of the plurality of regions includes a respective set of fins extending from the external surface. Each set of fins of a respective region of the plurality of regions are oriented in a different direction than sets of fins of other regions of the plurality of regions.
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公开(公告)号：US20170328279A1
公开(公告)日：2017-11-16
申请号：US15152202
申请日：2016-05-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Mohammed El Hacin Sennoun , William Joseph Solomon , Kyle Louis Miller
Abstract: The heat exchanger assembly includes a first conduit, an external surface, and a set of fins. The first conduit includes a first inlet, a first outlet, and a first internal flow path extending between the first inlet and first outlet. The first conduit is configured to channel a flow of fluid to be cooled from the first inlet to the first outlet. The external surface which includes a plurality of regions. Each region of the plurality of regions includes a respective set of fins extending from the external surface. Each set of fins of a respective region of the plurality of regions are oriented in a different direction than sets of fins of other regions of the plurality of regions.
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公开(公告)号：US20240318660A1
公开(公告)日：2024-09-26
申请号：US18678303
申请日：2024-05-30
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Aaron J. King
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, and an airfoil. The fan includes fan blades that extend radially outwardly toward the annular casing. The airfoil includes a first side and a second side coupled together at a leading edge and a trailing edge, a plurality of first chord sections defining at least one first chord length, and a plurality of second chord sections defining at least one second chord length. The plurality of first chord sections and second chord sections define a waveform along a leading edge of the airfoil. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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公开(公告)号：US20240288003A1
公开(公告)日：2024-08-29
申请号：US18656078
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan blades include a first fan blade having a fan blade airfoil body and a metal edge. The fan blade airfoil body has a leading edge. The metal edge is located at the leading edge and has a plurality of fail-fuse elements. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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