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公开(公告)号：US20250067190A1
公开(公告)日：2025-02-27
申请号：US18456159
申请日：2023-08-25
Applicant: RTX CORPORATION
Inventor： Cheng Gao , David J. Wasserman , Thomas S. Heylmun
Abstract: A method is disclosed for a design geometry of a ceramic matrix composite (CMC) vane arc segment that has a platform and an airfoil section that extends off of the platform. The platform defines an axially trailing face, an axially leading face that is circumferentially offset from the axially trailing face, and first and second circumferential faces. In the method, a modal excitation response of the platform is determined based upon an external engine operation excitation frequency. If the modal excitation response is greater than a target modal excitation response, the design geometry of the platform is adjusted to be detuned with the external engine operation excitation frequency by reducing an overhang distance of the platform in which the modal excitation response at the external engine operation excitation frequency is equal to or lower than the target modal excitation response.
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公开(公告)号：US20250067187A1
公开(公告)日：2025-02-27
申请号：US18455265
申请日：2023-08-24
Applicant: RTX CORPORATION
Inventor： Howard J. Liles
Abstract: A gas turbine engine includes a ceramic matrix composite (CMC) vane arc segment that has first and second platforms and an airfoil section that extends radially therebetween. The airfoil section includes an internal through-cavity, and the first and second platforms include, respectively, platform inlet and outlet ports connected to the internal through-cavity for conveying cooling air. The CMC vane arc segment is radially mounted between first and second metallic vane supports. The second metallic vane support includes a plenum and a plenum inlet port connected with the platform outlet port for receiving the cooling air from the internal through-cavity. There is a seal located radially between the second platform and the second metallic vane support. The seal circumscribes the platform outlet port to limit leakage of the cooling air between the second platform and the second metallic vane support.
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公开(公告)号：US20250067185A1
公开(公告)日：2025-02-27
申请号：US18452901
申请日：2023-08-21
Applicant: RTX CORPORATION
Inventor： David J. Wasserman , Craig R. McGarrah
Abstract: A method of forming a vane assembly for a gas turbine engine includes the steps of 1) determining a re-stagger angle for an airfoil on a ceramic matrix composite (“CMC”) vane, 2) determine an adjusted position of a baffle to be inserted within a central chamber in the vane, inserting the baffle into a bathtub seal, and adjusting an upper face of the baffle to an orientation relative to a bathtub seal support face to account for the adjusted position of the baffle and 3) fixing the baffle upper face to the bathtub seal flange support face. A vane assembly and a gas turbine engine are also disclosed.
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公开(公告)号：US20250059894A1
公开(公告)日：2025-02-20
申请号：US18476474
申请日：2023-09-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Abhijeet Jayshingrao Yadav , Frank Worthoff , Nicholas Joseph Kray , Nitesh Jain , Balaraju Suresh
Abstract: A turbine engine including a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The turbine engine further including a composite airfoil assembly. The composite airfoil assembly having an outer wall, a composite body at least partially defining the outer wall, and a tip cap at least partially defining the outer wall.
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5.发明授权公开(公告)号：US12228050B2
公开(公告)日：2025-02-18
申请号：US17943696
申请日：2022-09-13
Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
Inventor： Shigeki Senoo , Soichiro Tabata , Tetsuya Sawatsubashi , Hiroyuki Mitsui , Kunio Asai , Ryuichi Matsubara , Kiyoshi Tatsuhara
Abstract: A steam turbine according to the present invention comprises: a shaft which rotates about the rotation axis thereof; a plurality of moving blades which extend in the radial direction from the outer peripheral surface of the shaft and which are arranged along the circumferential direction; a casing main body which covers the shaft and the moving blades from the outer peripheral side; a plurality of stationary blades which are arranged on the inner circumferential surface of the casing main body; and a substance supply unit which supplies, to the surfaces of the moving blades and/or the surfaces of the stationary blades, a film forming substance that is hydrophobic, wherein the substance supply unit has a storage unit, a supply passage which is formed inside the casing and through which the film forming substance flows, and discharge units which are formed inside the moving blades and/or the stationary blades and which guide the film forming substance to the surfaces.
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Patent Agency Ranking
公开(公告)号：US20250052162A1
公开(公告)日：2025-02-13
申请号：US18447525
申请日：2023-08-10
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A gas turbine engine includes a fan section, a compressor section, combustion section, and turbine section in serial flow arrangement, that defining an engine centerline extending between a forward direction and an aft direction. A composite component, such as an airfoil, extends between a root and a tip, defining a span-wise direction therebetween, and between a leading edge and a trailing edge, defining a chord-wise direction therebetween. The composite component includes a preform core including a first set of fibers as a first set of warp fibers and a first set of weft fibers.
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公开(公告)号：US20250027418A1
公开(公告)日：2025-01-23
申请号：US18353196
申请日：2023-07-17
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Christian X. Campbell , Aaron Tomich , Peter J. Rosenfeld
Abstract: An airfoil wall that includes a wishbone-shaped fiber layup structure that has first and second arms that merge into a single leg. The leg includes fiber tows from each of the arms and the tows are interwoven in the leg. Each of the arms includes a first section that is distal from the leg and a second section that is proximal to the leg. The first section defines a first thickness and a first fiber tow count. The second section defines a second thickness that is greater than the first thickness and a second fiber tow count that is greater than the first fiber tow count. The single leg defines a third thickness that is greater than the second thickness and a third fiber tow count that is greater than the second fiber tow count.
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公开(公告)号：US20250019821A1
公开(公告)日：2025-01-16
申请号：US18713007
申请日：2022-11-21
Applicant: SAFRAN CERAMICS
Inventor： Eric BOUILLON , Lisa PIN , Simon ARNAL , Benjamin COSSOU
Abstract: A method including a step of forming a bond coating on a surface of a substrate, and a step of forming a barrier coating on the bond coating. The bond coating is formed by chemical vapor deposition, at a deposition temperature higher than 150° C., in particular 1200° C. or higher, of a precursor including silicon, and includes columnar grains of crystalline silicon.
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公开(公告)号：US12196107B2
公开(公告)日：2025-01-14
申请号：US18172723
申请日：2023-02-22
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D5/28
Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.
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公开(公告)号：US20240426251A1
公开(公告)日：2024-12-26
申请号：US18825435
申请日：2024-09-05
Applicant: ROLLS-ROYCE plc
Inventor： Pascal DUNNING , Roderick M. TOWNES , Michael J. WHITTLE
Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
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