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公开(公告)号：US12158123B1
公开(公告)日：2024-12-03
申请号：US17333986
申请日：2021-05-28
Applicant: Raytheon Technologies Corporation
Inventor： Steven W. Burd
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a supplemental thrust section and a duct. The supplemental thrust section includes a rotating detonation combustor. The duct includes a supplemental thrust section inlet fluidly coupled with and leading to the rotating detonation combustor. The supplemental thrust section inlet has a flow area that decreases as at least a first portion of the supplemental thrust section inlet extends towards the rotating detonation combustor.
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公开(公告)号：US20240368997A1
公开(公告)日：2024-11-07
申请号：US18410290
申请日：2024-01-11
Applicant: General Electric Company
IPC: F01D17/16 , B64C11/00 , B64C11/18 , B64C11/46 , B64C11/48 , B64D27/00 , F01D9/02 , F02C6/20 , F02K1/46 , F02K3/02
Abstract: An unducted thrust producing system, includes a rotating element, a stationary element. An inlet may be located forward or aft of the rotating element and the stationary element. An exhaust may be located forward, aft, or between the rotating element and the stationary element.
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公开(公告)号：US12044194B2
公开(公告)日：2024-07-23
申请号：US16811368
申请日：2020-03-06
Applicant: General Electric Company
Inventor： David Marion Ostdiek , Alan Roy Stuart , Daniel Alan Niergarth , Gert Johannes van der Merwe , Brandon Wayne Miller , Stephen William Freund
CPC classification number: F02K3/072 , B64D27/10 , F02C3/073 , F02K1/34 , F02K3/025 , F02K3/075 , F02K3/077
Abstract: A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.
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公开(公告)号：US12037962B1
公开(公告)日：2024-07-16
申请号：US18118606
申请日：2023-03-07
Applicant: General Electric Company
Inventor： David Perveiler , Craig D. Young , Dean P. Modroukas , Daniel Depperschmidt , Anthony Hazlett
CPC classification number: F02K7/10 , F02K3/02 , F02K7/14 , F23R7/00 , F05D2220/10 , F05D2240/35 , F05D2300/6033
Abstract: A high-speed, air-breathing propulsion engine includes an inlet configured to compress incoming air, a fuel injector configured to supply a fuel for mixing with the compressed incoming air to form a fuel-air mixture, and a combustor configured to burn the fuel-air mixture. The combustor includes a rotation detonation combustor system and a bluff body system that cooperate to generate thrust.
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公开(公告)号：US11982232B2
公开(公告)日：2024-05-14
申请号：US18100130
申请日：2023-01-23
Applicant: RTX Corporation
Inventor： James F. Wiedenhoefer , Russell J. Bergman , William P. Stillman , Patrick M. Hart
CPC classification number: F02C7/185 , B64D33/10 , F02K3/025 , F02K3/105 , F28D7/0075 , F05D2220/323 , F05D2260/213
Abstract: A turbine engine heat exchanger has: a manifold having a first face and a second face opposite the first face; a plurality of first plates along the first face, each first plate having an interior passageway; and a plurality of second plates along the second face, each second plate having an interior passageway. A first flowpath passing through the interior passageways of the first plates, the manifold, and the interior passageways of the second plates.
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Patent Agency Ranking
公开(公告)号：US20240068411A1
公开(公告)日：2024-02-29
申请号：US18387527
申请日：2023-11-07
Applicant: RTX CORPORATION
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
CPC classification number: F02C7/36 , F02C3/04 , F02C3/06 , F02C3/107 , F02K3/025 , F02K3/06 , F05D2220/32 , F05D2220/323 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine includes, among other things, a propulsor section including a propulsor, a core engine, a gear arrangement that drives the propulsor. A compressor section includes a first compressor section and a second compressor section. A turbine section includes a first turbine and a second turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than 40. The pressure ratio across the second compressor section is between 7 and 15, and the pressure ratio across the first compressor section is between 4 and 8.
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公开(公告)号：US11585292B2
公开(公告)日：2023-02-21
申请号：US16969228
申请日：2019-02-13
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Bruno Alexandre Didier Jacon , Baghdad Achbari , Thomas Claude Broage , Florent Robert André Godin , Joël François Roudil , Hervé Simonotti
Abstract: An outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud including: an annular downstream portion provided with a shroud opening passing through an annular downstream edge of the shroud; a connecting member (50) attached to the annular downstream portion, and intended to attach an arm that passes through a secondary flow path; an air-sealing and fire-resistance device including: a portion including: a pad arranged in a hollow annular area of the annular downstream edge of the shroud; a blade protruding from the pad and clamped between a circumferential end and the radially outer end of the arm, a leaf spring (pressing the pad into the hollow annular area.
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公开(公告)号：US11585273B2
公开(公告)日：2023-02-21
申请号：US17124551
申请日：2020-12-17
Applicant: Raytheon Technologies Corporation
Inventor： James F. Wiedenhoefer , Russell J. Bergman , William P. Stillman , Patrick M. Hart
Abstract: A turbine engine heat exchanger has: a manifold having a first face and a second face opposite the first face; a plurality of first plates along the first face, each first plate having an interior passageway; and a plurality of second plates along the second face, each second plate having an interior passageway. A first flowpath passing through the interior passageways of the first plates, the manifold, and the interior passageways of the second plates.
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公开(公告)号：US20220389883A1
公开(公告)日：2022-12-08
申请号：US17734324
申请日：2022-05-02
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： STEVEN W. BURD
Abstract: A turboshaft engine includes a core engine, including a fan section, a compressor section, a primary combustor and a turbine section positioned within a core flow path of the gas turbine engine; a bypass splitter positioned radially outward of the core engine and configured to house the compressor section, the primary combustor and the turbine section; a bypass duct positioned radially outward of the bypass splitter; and a power spool operably coupled to the core engine and configured rotationally drive a fan included within the fan section.
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公开(公告)号：US11448309B2
公开(公告)日：2022-09-20
申请号：US16785915
申请日：2020-02-10
Applicant: United Technologies Corporation
Inventor： Janice Jabido , Michael E. McCune
Abstract: A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.
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