-
公开(公告)号：US12221984B2
公开(公告)日：2025-02-11
申请号：US17610486
申请日：2020-04-06
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Typhaine Raslain
Abstract: A method for parameterizing a digital filter for attenuation of a torsional mode of a power transmission line of an aircraft turbine engine is disclosed. The mode is associated with a frequency in a confidence interval, the digital filter is low-pass and described by a transfer function equal to the quotient N(z)/D(z), integrated into a pre-existing monitoring loop of the turbine engine, to filter signals sampled at a frequency. The method includes: calculating zeros of N(z), so that the filter attenuates the frequency; updating the zeros of N(z), so that the gain of the filter satisfies, in the interval, a first gain template; and determining the poles of D(z), so that, in the bandwidth of the loop: the phase of the filter satisfies a phase template, and the gain of the filter satisfies a second gain template.
-
公开(公告)号：US20250035005A1
公开(公告)日：2025-01-30
申请号：US18536843
申请日：2023-12-12
Applicant: General Electric Company
Inventor： Deepak Trivedi , Rahul Anil Bidkar , Bugra Han Ertas , Ravindra Shankar Ganiger , Narendra Anand Hardikar
Abstract: A seal assembly for a turbomachine includes a rotating component, a non-rotating component having a ring carrier, a face seal ring, and a joint disposed between the ring carrier and the non-rotating component. The non-rotating component is arranged with the rotating component at a sealing interface. The joint is capable of linear and tilt displacement to allow the non-rotating component to displace with respect to the rotating component. The sealing interface defines a gap between the face seal ring and the rotating component. The seal assembly also includes at least one damping element arranged with the ring carrier for maintaining the seal assembly centrally in a radial direction in the turbomachine. Further, the damping element(s) includes at least one mass element.
-
公开(公告)号：US20250020069A1
公开(公告)日：2025-01-16
申请号：US18349524
申请日：2023-07-10
Applicant: Pratt & Whitney Canada Corp.
Inventor： Tomasz Olech , Morgan Demenois , Negin Abaeian , Domenico Di Florio , Raghavendra Pendyala
Abstract: A gas turbine engine includes a compressor section, a combustor and a turbine section. At least one case surrounds at least one of the compressor section and the turbine section. The case is formed from sheet metal and includes a case wall and at least one potential displacement location due to vibration. At least one retaining ring is assembled to the case and biased against the case wall at the at least one potential displacement location to dampen vibration.
-
公开(公告)号：US12116932B2
公开(公告)日：2024-10-15
申请号：US17819426
申请日：2022-08-12
Applicant: General Electric Company
Inventor： Nikolai Pastouchenko , Kishore Ramakrishnan , Trevor H. Wood , Timothy Richard DePuy
CPC classification number: F02C7/045 , F01D25/04 , F05D2220/32 , F05D2260/96
Abstract: An inlet duct for a nacelle of a ducted fan engine includes an inlet portion at an upstream end of the inlet duct, an acoustic liner arranged downstream of the inlet portion, and a fan section arranged downstream of the acoustic liner. The inlet portion and the acoustic liner are coupled together at an inlet-acoustic liner interface extending circumferentially about the inner surface of the inlet duct, and the acoustic liner and the fan section are coupled together at a fan section hardwall-acoustic liner interface extending circumferentially about the inner surface of the inlet duct. At least one of the acoustic liner, the inlet-acoustic liner interface, and the fan section hardwall-acoustic liner interface having a structure that circumferentially alters a magnitude and a phase of an acoustic wave reflection of the inlet duct to attenuate flutter bite of a fan.
-
公开(公告)号：US20240254895A1
公开(公告)日：2024-08-01
申请号：US18421033
申请日：2024-01-24
Applicant: BRP-ROTAX GMBH & CO. KG
Inventor： Hubert LOIMAYR , Markus WOLFSGRUBER , Paul ALLMANN , Rudolf KUSEL , Rudolf TSCHERNE
CPC classification number: F01D25/18 , F01D25/04 , F02B37/00 , F05D2220/40 , F05D2260/40 , F05D2260/96 , F05D2260/98
Abstract: A supercharger assembly has a supercharger housing defining an air inlet and an air outlet; an impeller disposed in the supercharger housing; an impeller shaft connected to the impeller for driving the impeller; a driveshaft connected to the impeller shaft for driving the impeller shaft, the driveshaft defining an oil supply passage; and a torsional damper connected to the driveshaft for driving the driveshaft. The torsional damper is configured for being operatively connected to a crankshaft of an internal combustion engine. The oil supply passage is positioned to supply oil to the torsional damper for lubricating the torsional damper.
-
Patent Agency Ranking
公开(公告)号：US20240068378A1
公开(公告)日：2024-02-29
申请号：US17823912
申请日：2022-08-31
Applicant: SAUDI ARABIAN OIL COMPANY
Inventor： Ahmed Mohammed Al Dossary , Majed S. Alaboush , Marzuoq T. Otaibi , Nassir Saleh Al Faihani , Saleh Ali Al-Najrani
CPC classification number: F01D21/003 , F01D25/04 , F01D25/20 , F05D2220/40 , F05D2260/83 , F05D2260/96 , F05D2260/98 , F05D2270/301 , F05D2270/303
Abstract: A system for bench-testing a turbocharger before installing the turbocharger on an engine has the turbocharger with a turbocharger turbine inlet, a turbocharger lubricating oil inlet, and a turbocharger lubricating oil outlet. The turbocharger is mounted on a support. An air supply device provides a gas flow to run the turbocharger. The air supply device is mounted on a support and has an air supply device outlet. A diffusor directs the gas flow from the air supply device outlet to the turbocharger turbine inlet. A lubricating oil pump is connected to the turbocharger lubricating oil inlet; and pumps lubricating oil from a lubricating oil tank to the turbocharger. The turbocharger is disposed above the tank and the lubricating oil flows directly into the tank via a tank hole that is open to a surrounding atmosphere.
-
公开(公告)号：US20240052781A1
公开(公告)日：2024-02-15
申请号：US18260923
申请日：2022-01-13
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Guillaume GLEMAREC , Jean-Baptiste VIGNES , Romuald Muriel GENTILS , Valerio CAPASSO
CPC classification number: F02C7/20 , F01D25/04 , B64D27/26 , F05D2260/96 , B64D2027/262
Abstract: Assembly including an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft. The pylon includes members for suspending the turbine engine, the members being connected to the turbine engine in at least one plane which is perpendicular to the axis and which is located upstream of the combustion chamber of the turbine engine, such that the turbomachine is cantilevered to the pylon, The assembly further includes at least one damper which connects the turbomachine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, the damper being configured to limit the relative movements between the turbine engine and the pylon without transmitting force.
-
公开(公告)号：US20240052778A1
公开(公告)日：2024-02-15
申请号：US17951619
申请日：2022-09-23
Applicant: General Electric Company
Inventor： Nageswar Rao Ganji , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Ambika Shivamurthy , Trevor H. Wood
CPC classification number: F02C6/08 , F01D25/04 , F01D25/28 , F05D2260/606 , F05D2260/963 , F05D2250/131
Abstract: Variable bleed valves with struts for aerodynamic stability are described. An apparatus described herein includes a variable bleed valve port, and a strut disposed within the variable bleed valve port, the strut defining a plane and a plurality of holes disposed perpendicularly to the plane, the plurality of holes disposed in a pattern to dampen an acoustic response associated with the variable bleed valve port.
-
公开(公告)号：US20240035384A1
公开(公告)日：2024-02-01
申请号：US17815372
申请日：2022-07-27
Applicant: General Electric Company
Inventor： Zachary John Snider , Brad Wilson VanTassel , Brian Denver Potter , John McConnell Delvaux
CPC classification number: F01D25/04 , F01D25/06 , F05D2220/32 , F05D2260/96
Abstract: A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.
-
公开(公告)号：US20240018882A1
公开(公告)日：2024-01-18
申请号：US18036035
申请日：2021-11-17
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Sylvain Yves Jean DUVAL , Amaud Lasantha GENILIER , Olivier RENON
CPC classification number: F01D25/243 , F01D25/04 , F05D2260/941
Abstract: The invention relates to a turbine engine case (1), extending around an axis, said case (1) comprising: a hub comprising an outer wall (21) and an inner wall (22) between which an annular flange (23) extends; an outer shell (3); a plurality of arms (4) which each extend between the hub and the outer shell (3); the case (1) further comprising a plurality of main stiffeners (5), each being disposed in the extension of an arm (4) between the outer wall (21) and the inner wall (22) projecting from the flange (23), each main stiffener (5) comprising two ribs (51, 52) arranged opposite one another and which move away from one another from the outer wall (21) towards the inner wall (22).
-
-
-
-
-
-
-
-
-
Search Results
772
records
(took 0.025 seconds)
