-
公开(公告)号：US20220275730A1
公开(公告)日：2022-09-01
申请号：US17744973
申请日：2022-05-16
摘要： Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.
-
公开(公告)号：US20220259975A1
公开(公告)日：2022-08-18
申请号：US17177585
申请日：2021-02-17
摘要： A gas turbine engine rotor assembly, comprising: a shaft about an axis having an outer surface radially outward and a groove radially into the outer surface; a disc surrounding the shaft rotatable with the shaft about the axis, the disc having an inner surface extending axially defining an inner diameter, having a disc profile around the groove and axially away from and radially inwardly of the inner diameter, the shaft and the disc defining a gap circumscribed outwardly by the inner diameter and inwardly by the outer surface; and a seal including a split ring fitted into the groove and rotatable with the shaft about the axis, the ring having a ring profile complementary to the disc profile, the ring resiliently expandable radially in the gap to the inner diameter, the disc profile cooperable with the ring profile to axially load the shaft via the ring expanded across the gap.
-
公开(公告)号：US11408292B2
公开(公告)日：2022-08-09
申请号：US17278903
申请日：2019-09-06
摘要： Turbine nozzle for a turbomachine extending about an axis, the nozzle including a plurality of sectors each having at least one vane which extends radially between an internal platform and an external platform, the nozzle including at least two sealing strips each including a main portion configured to ensure the sealing between the nozzle and an element of the turbomachine which is adjacent to the nozzle, and a first portion folded relative to the main portion, the first folded portion being in contact with an outer face of at least one platform, each strip being held to the at least one platform by a clamping device configured to clamp the first folded portion between the outer face of the platform and the clamping device.
-
公开(公告)号：US20220228540A1
公开(公告)日：2022-07-21
申请号：US17575686
申请日：2022-01-14
发明人： Jérôme LESCOUP
摘要： A turbojet engine with two thrust reverser modules. Each module includes an outer casing, an inner casing and a securing system for securing the inner casing to the outer casing which comprises first and second hoods. A housing between the hoods has a securing wall, a seal with a sausage secured to the securing wall, and a crusher rigidly secured to the second hood and arranged so as to crush the sausage towards the securing wall when the second hood goes from the spaced-apart position to the close-together position. Therefore, the sausage moves in the longitudinal direction, thus limiting shearing of the seal and transverse movements owing to the manufacturing and assembly tolerances and the movements in flight.
-
公开(公告)号：US20220221056A1
公开(公告)日：2022-07-14
申请号：US17496288
申请日：2021-10-07
发明人： Anthony R. Bifulco
摘要： A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section.
-
公开(公告)号：US11384653B2
公开(公告)日：2022-07-12
申请号：US16802689
申请日：2020-02-27
发明人： Stephen S. Stone
摘要： A seal assembly includes at least one primary seal, whose ends terminate in a modified air duct that is housed in a precision bore located at the ends of the primary seal slots. The air duct functions to seal the primary seal slot ends. A slot milled in the face of the air duct allows the primary seal to pass through and terminate centrally in the air duct bore. Minimal interference between the bore and air duct prevents cooling air from escaping the bore, completing the seal. Proper specification of the length of the primary seal in conjunction with precise location of the air duct bores allows for ample thermal expansion without loss of sealing. Axial clearance between the mating bores and air duct ends provides allowance for build tolerance, thermal expansion and movements between mating nozzles including movements between corresponding vane manifold portions.
-
87.发明申请公开(公告)号：US20220213799A1
公开(公告)日：2022-07-07
申请号：US17520756
申请日：2021-11-08
发明人： Simon HAUSWIRTH , Wade Beaumont , Vincent GALOUL , Richard JONES , Yunchang JANG
摘要： The present invention presents a ring assembly 1 disposed radially outwardly of an array of circumferentially arranged blades 38 of a gas turbine engine rotor R. The ring assembly 1 includes ring segments 2 disposed circumferentially one adjacent to another and having a first circumferential end 2a and a second circumferential end 2b circumferentially spaced apart from each other. The first end 2a of a ring segment 2 and the second end 2b of an adjacent ring segment 2 of the plurality of ring segments 2 are arranged facing each other. An integrally formed projecting seal part 92 is formed at the first end 2a. An integrally formed receiving seal part 94 is formed at the second end 2b facing the first end 2a. The receiving seal part 94 receives the projecting seal part 92 to form a mating connection between the ring segment 2 and the adjacent ring segment 2. A gas turbine engine including the ring assembly 1 is also provided. Furthermore, a method of manufacturing the ring segment 2 of the ring assembly 1 is also provided.
-
公开(公告)号：US11377971B2
公开(公告)日：2022-07-05
申请号：US16670617
申请日：2019-10-31
发明人： Shota Igarashi , Tomomi Koganezawa , Keisuke Miura , Yoshitaka Hirata , Shohei Yoshida , Yoshitaka Terada , Takehiko Nishikawa
摘要： A gas turbine combustor includes multiple aft frames each having a floating seal that seals a gap between an aft frame and a gas turbine in inner and outer peripheries of the aft frame, and a side seal that seals a gap between the aft frames adjacent to each other in a circumferential direction, and a corner seal that is placed in a gap portion provided between corner portions of the aft frames adjacent to each other in the circumferential direction, seals air leaking from at least the gap portion into the gas turbine side, and is independent of the floating seal and the side seal.
-
公开(公告)号：US11371374B2
公开(公告)日：2022-06-28
申请号：US16935285
申请日：2020-07-22
IPC分类号： F01D25/12 , F01D11/00 , F16J15/324
摘要： A gas turbine engine component includes a first member, a second member rotatable relative to the first member about an axis, and a seal assembly that includes a seal supported by the first member and a seal runner that rotates with the second member relative to the seal. The seal runner includes at least one internal passage to direct cooling fluid flow through the seal runner. A restriction is associated with the at least one internal passage to restrict flow through the at least one internal passage in response to an engine condition.
-
公开(公告)号：US11371373B2
公开(公告)日：2022-06-28
申请号：US16666890
申请日：2019-10-29
摘要： A seal housing may comprise an aft flange, an outer diameter (OD) ring and a stopper. The stopper may extend radially inward from a radially inner surface of OD ring. The stopper may be configured to interface with a monobloc carbon seal. The stopper may comprise a circumferential stopping portion and an axial stopping portion. There may be a plurality of the stopper.
-
-
-
-
-
-
-
-
-
搜索结果
4718 条记录 (耗时 0.032 秒)
