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公开(公告)号：US20240060510A1
公开(公告)日：2024-02-22
申请号：US18234055
申请日：2023-08-15
Applicant: General Electric Company
Inventor： Stephan Priebe , Giridhar Jothiprasad , Joseph Capozzi , Thomas Malkus , Michael Macrorie , Trevor H. Wood
CPC classification number: F04D29/526 , F04D29/324
Abstract: A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).
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公开(公告)号：US11635030B2
公开(公告)日：2023-04-25
申请号：US15620904
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Stephen Raymond Donnelly , Masato Nakanishi , Joseph Capozzi
Abstract: A compressor bleed apparatus includes: a compressor comprising one or more rotors mounted for rotation about a central axis and enclosed in a compressor casing; a bleed slot passing through the compressor casing; an outer wall defining, in cooperation with the compressor casing, a plenum surrounding the compressor casing; at least one offtake pipe communicating with the plenum; and wherein at least one of the plenum and the bleed slot has a non-axisymmetric structure.
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公开(公告)号：US20180355877A1
公开(公告)日：2018-12-13
申请号：US15620904
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Stephen Raymond Donnelly , Masato Nakanishi , Joseph Capozzi
CPC classification number: F04D27/009 , F02C3/04 , F02C9/18 , F04D17/025 , F04D29/403 , F05D2220/32 , F05D2240/35
Abstract: A compressor bleed apparatus includes: a compressor comprising one or more rotors mounted for rotation about a central axis and enclosed in a compressor casing; a bleed slot passing through the compressor casing; an outer wall defining, in cooperation with the compressor casing, a plenum surrounding the compressor casing; at least one offtake pipe communicating with the plenum; and wherein at least one of the plenum and the bleed slot has a non-axisymmetric structure.
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Patent Agency Ranking
公开(公告)号：US10914318B2
公开(公告)日：2021-02-09
申请号：US16244559
申请日：2019-01-10
Applicant: General Electric Company
Inventor： Joseph Capozzi , Aspi Rustom Wadia
Abstract: A rotary component for a gas turbine engine defining a central axis extending along an axial direction, a radial direction extending perpendicular to the axial direction, and a circumferential direction perpendicular to both the central axis and the radial direction. The rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in the radial direction and defining an annular gap between a tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features on an interior surface of the outer casing. A first feature of the feature(s) defines a first casing thickness, and a second feature positioned at least partially circumferentially or axially from the first feature defines a second casing thickness different than the first casing thickness.
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公开(公告)号：US20240060429A1
公开(公告)日：2024-02-22
申请号：US17889542
申请日：2022-08-17
Applicant: General Electric Company
Inventor： Stephan Priebe , Giridhar Jothiprasad , Joseph Capozzi , Thomas Malkus , Michael Macrorie , Trevor H. Wood
CPC classification number: F01D25/24 , F02C3/04 , F01D9/041 , F05D2230/60 , F05D2220/323
Abstract: A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).
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公开(公告)号：US11149552B2
公开(公告)日：2021-10-19
申请号：US16713469
申请日：2019-12-13
Applicant: General Electric Company
Inventor： Anthony Louis DiPietro, Jr. , Tyler James Alexander , Joseph Capozzi , Aspi Rustom Wadia , Andrew Breeze-Stringfellow
Abstract: A fan for a gas turbine engine is provided. The fan includes a rotor including at least one rotor stage having a rotatable disk defining a flowpath surface and an array of rotor airfoils extending outward from the flowpath surface; an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement; and a shroud extending between the rotor airfoils and the splitter airfoils.
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公开(公告)号：US20210180458A1
公开(公告)日：2021-06-17
申请号：US16713469
申请日：2019-12-13
Applicant: General Electric Company
Inventor： Anthony Louis DiPietro, JR. , Tyler James Alexander , Joseph Capozzi , Aspi Rustom Wadia , Andrew Breeze-Stringfellow
Abstract: A fan for a gas turbine engine is provided. The fan includes a rotor including at least one rotor stage having a rotatable disk defining a flowpath surface and an array of rotor airfoils extending outward from the flowpath surface; an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement; and a shroud extending between the rotor airfoils and the splitter airfoils.
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公开(公告)号：US20200224675A1
公开(公告)日：2020-07-16
申请号：US16244559
申请日：2019-01-10
Applicant: General Electric Company
Inventor： Joseph Capozzi , Aspi Rustom Wadia
Abstract: A rotary component for a gas turbine engine defining a central axis extending along an axial direction, a radial direction extending perpendicular to the axial direction, and a circumferential direction perpendicular to both the central axis and the radial direction. The rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in the radial direction and defining an annular gap between a tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features on an interior surface of the outer casing. A first feature of the feature(s) defines a first casing thickness, and a second feature positioned at least partially circumferentially or axially from the first feature defines a second casing thickness different than the first casing thickness.
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