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公开(公告)号：US12209652B2
公开(公告)日：2025-01-28
申请号：US17805380
申请日：2022-06-03
Applicant: SAFRAN TRANSMISSION SYSTEMS
Inventor： Juan-Luis Marcos Izquierdo
Abstract: A mechanical part for an aircraft turbomachine, the mechanical part being made of metal and comprising at least one profiled surface configured to ensure an oil flow during operation. According to the invention, the surface includes a more hydrophobic and/or lipophobic coating than the surface or a surface texturing rendering the surface more hydrophobic and/or lipophobic
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公开(公告)号：US20240271577A1
公开(公告)日：2024-08-15
申请号：US18436826
申请日：2024-02-08
Applicant: Pratt & Whitney Canada Corp.
Inventor： Yusuf Syed , Thomas Trevor Ricci , James Jarvo
Abstract: A method of and system for operating a hybrid electric propulsion system for an aircraft in a start sequence is provided. The hybrid electric propulsion system includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, and a propulsion unit having a propeller having propeller blades. The method includes: driving the propeller from a static state to a target rotational speed within a predetermined range of speeds using the electric motor; transitioning the propeller blades from a feathered mode to an unfeathered mode while the propeller is being driven at the target rotational speed solely by the electric motor; starting the thermal engine; and transitioning the driving of the propeller using the electric motor to driving the propeller using the thermal engine.
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公开(公告)号：US12025726B2
公开(公告)日：2024-07-02
申请号：US17245317
申请日：2021-04-30
Applicant: Murata Manufacturing Co., Ltd.
Inventor： Katsuhisa Kashiwagi , Nobuya Arakawa , Hideaki Yamada
IPC: F01D25/20 , F01D25/18 , F01M5/00 , F02C7/06 , F02C7/14 , F02K9/64 , G01S7/03 , G01S7/41 , H01Q1/42 , H01Q9/04 , H01Q21/08 , G01S7/35
Abstract: An antenna apparatus includes multiple antenna elements each performing at least one of transmission and reception of radio waves. The coverage areas of main lobes of radiation patterns of the multiple antenna elements are overlapped with each other and the shapes of side lobes thereof are varied among the multiple antenna elements. With this configuration, it is possible to discriminate and acquire the signal of the radio waves coming from the coverage areas of the main lobes of the antenna from the signal of the radio waves coming from the outside of the coverage areas.
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公开(公告)号：US20240209752A1
公开(公告)日：2024-06-27
申请号：US18573938
申请日：2022-06-28
Applicant: SAFRAN POWER UNITS
Inventor： Romain QUINTON , Serge Marie Gabriel COT , Jean-Paul Salvador LOPEZ
CPC classification number: F01D25/18 , F01D25/16 , F05D2240/50 , F05D2260/98
Abstract: An assembly for a gas turbine includes a hollow central shaft which is guided in rotation by at least one bearing, the assembly further including a device for lubricating said at least one bearing, the device including a hollow lubricant delivery tube which is arranged fixedly in the central shaft and is configured to deliver lubricant to the at least one bearing, the lubricant delivery tube having a first section with a first diameter and a second section with a second diameter which is greater than the first diameter, the second section including a plurality of radial channels connecting the inside of the lubricant delivery tube and leading radially to the outside of the lubricant delivery tube towards a radially inner wall of the central shaft so as to form a lubricant film between said second section of the lubricant delivery tube and said radially inner wall of the central shaft.
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公开(公告)号：US12012862B2
公开(公告)日：2024-06-18
申请号：US17813452
申请日：2022-07-19
Applicant: VOLVO TRUCK CORPORATION
Inventor： Claes Kuylenstierna , Pontus Eriksson
CPC classification number: F01D25/183 , F01D9/06 , F01D11/005 , F01D25/16 , F05D2220/40 , F05D2260/60 , F05D2260/98
Abstract: An internal combustion engine, ICE, system, includes a turbocharger having a turbine and a compressor for compressing intake air and feeding the intake air to the ICE. A turbo turbine unit is disposed in an exhaust gas path downstream the turbocharger to receive exhaust gas from the turbocharger. The turbo turbine unit having a turbine wheel, a bearing housing defining an inside volume for containing lubrication oil, and a sealing arrangement positioned in the vicinity of the turbine wheel for preventing lubrication oil from escaping from the inside volume of the bearing housing to an exhaust duct of the turbo turbine unit. A buffer air conduit extends between a selected position at the compressor and a buffer air inlet of the turbo turbine unit. The buffer air inlet is in fluid communication with a buffer air channel inside the turbo turbine unit to direct buffer air to a position in-between axially opposite arranged annular sealing members to provide a counter-pressure against at least one of the annular sealing members.
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公开(公告)号：US12000342B2
公开(公告)日：2024-06-04
申请号：US17946238
申请日：2022-09-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra Dev Mahadevaiah , Sharad Pundlik Patil , Subrata Nayak , Milind Chandrakant Dhabade , Shiloh Montegomery Meyers , David Allan Dranschak
CPC classification number: F02C7/277 , F01D25/18 , F02C7/32 , F16H57/02 , F16H57/04 , F05D2260/85 , F16H2057/02017
Abstract: An air turbine starter (ATS) for a gas turbine engine having an accessory gear box (AGB) with a lubricant reservoir, the air turbine starter comprising a housing at least partially defining a working air flow path; a turbine section comprising a turbine having an output shaft and a plurality of blades circumferential spaced about the output shaft and at least partially extending into the working air flow path; a drive section having a drive shaft operably coupled to the output shaft to engage the AGB; and a lubrication recirculation circuit fluidly coupled to the lubricant reservoir.
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公开(公告)号：US11982197B2
公开(公告)日：2024-05-14
申请号：US17907623
申请日：2021-03-22
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Christophe Marcel Lucien Perdrigeon , Didier Gabriel Bertrand Desombre , Regis Eugene Henri Servant
CPC classification number: F01D25/125 , F01D25/16 , F01D25/18 , F02C7/06 , F16C33/6685 , F05D2220/323 , F05D2240/54 , F05D2260/20 , F05D2260/31 , F05D2260/98
Abstract: Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: —a rolling bearing (8), —an oil distributor ring (5) and —an annular track (26) of a dynamic seal (22), characterised in that it further comprises a nut (16) screwed on to a thread (5d) of the distributor ring and bearing axially against an axial end of the inner ring so as to clamp it axially, and in that the annular track is configured to bear axially against the distributor ring and comprises rotating locking elements (27) engaging with the additional elements (28) of the nut.
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公开(公告)号：US20240151161A1
公开(公告)日：2024-05-09
申请号：US18546709
申请日：2022-02-17
Applicant: NUOVO PIGNONE TECNOLOGIE - SRL
Inventor： Andrea MAGAROTTO , Luca FRASSINELLI , Venkata Rambabu DABIRU
IPC: F01D25/18
CPC classification number: F01D25/18 , F05D2220/32 , F05D2260/98
Abstract: A turbomachinery assembly, comprising a turbomachinery having an outlet oil pipe for collecting the exhaust oil of the turbomachine, and a collection manifold, connected to a main oil collection tank is disclosed. The turbomachinery assembly comprises also an oil flood retention tank for collecting the exhaust oil of the turbomachinery. The oil flood retention tank comprises inlet and outlet ports, wherein the inlet port is placed at a higher position with respect to the outlet port. Also disclosed is a flood retention tank.
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公开(公告)号：US20240110507A1
公开(公告)日：2024-04-04
申请号：US17957726
申请日：2022-09-30
Applicant: General Electric Company
Inventor： Constantinos Minas , William Wesley Morton
CPC classification number: F02C7/06 , F01D25/18 , F05D2220/323 , F05D2260/98
Abstract: A gas turbine engine is provided defining an axial direction, a radial direction, and a circumferential direction. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; a fan section including a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an oil tank positioned within the nacelle, wherein the oil tank defines an effective length (LT) along the axial direction, a circumference span (CS) along the circumferential direction, and a radial height (ΔrT) along the radial direction, and wherein these parameters are related by a tank sizing factor (TSF) equal to the effective length (LT) times the circumference span (CS) divided by the radial height (ΔrT) squared LT×CS/ΔrT2), wherein the tank sizing factor (TSF) is between 20 and 2200.
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公开(公告)号：US11938431B2
公开(公告)日：2024-03-26
申请号：US16648189
申请日：2018-09-24
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Arnaud Nifenecker , Benjamin Fulleringer , Cédric Lempegnat , Samuel Jousselin , Pierre Gaymu , Cédric Georget , Rémi Lanquetin , Philippe Olharan
CPC classification number: B01D45/14 , F01D25/18 , F16N39/002 , B01D46/0056 , F02C7/06 , F05D2260/602 , F05D2260/98 , F16N2210/02
Abstract: A component for a centrifugal deaerator for removing gas from a turbomachine air/oil mixture includes a structural part configured to delimit a duct for the flow of the air/oil mixture, and includes a circumferential enclosure for the centrifugal separation of the air/oil mixture, an axial inlet for the air/oil mixture, radial oil outlets, and an outlet for oil-free air. The component includes at least one cellular structure configured to filter the oil while allowing the air to pass and occupying at least a space in the duct.
