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公开(公告)号：US20230057786A1
公开(公告)日：2023-02-23
申请号：US17796981
申请日：2021-02-26
摘要： A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.
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公开(公告)号：US20230030587A1
公开(公告)日：2023-02-02
申请号：US17785217
申请日：2020-12-18
摘要： A turbomachine compressor module, comprising an annular array of structural arms defining inter-arm spaces between two circumferentially adjacent arms; and an annular array of stator vanes with variable orientation about a respective axis (A) and disposed at least partially within the inter-arm spaces. The arms are provided with flaps pivotable about a respective axis (B). Also, a turbomachine provided with such a module and a row of rotor blades directly downstream of the module.
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公开(公告)号：US11506068B2
公开(公告)日：2022-11-22
申请号：US16627632
申请日：2018-09-03
发明人： Jean Felske
摘要： Turbine engine assembly comprising: an external casing (28) of a low-pressure compressor (4), an annular wall (30) and an oil tank (46) with a circular chamber (48) around an axis (14) of the compressor. The wall (30) comprises an inner surface (38) delimiting an primary guide path for the flow of the compressor, and an external surface (40) radially opposite the inner surface and delimiting the internal chamber (48) of the tank (46).
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公开(公告)号：US20220251974A1
公开(公告)日：2022-08-11
申请号：US17604652
申请日：2020-04-10
发明人： Morgan VYVEY
摘要： A compressor casing for a turbine engine, the casing comprising: a housing comprising a radially inner e surface; an upstream ferrule; and a downstream ferrule; each of the ferrules having a respective inner surface capable of defining an air stream, and each of the ferrules having an outer surface facing the inner surface of the housing, the ferrules being attached to the cantilevered housing and being axially arranged so as to be separated by an axial clearance. Additionally, a turbine engine comprising such a casing and a stage of variable-setting vanes.
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公开(公告)号：US11313282B2
公开(公告)日：2022-04-26
申请号：US16758749
申请日：2019-06-21
发明人： Stephane Maljean
摘要： A turbojet engine (2), such as an aircraft turbojet engine, comprising: an epicyclic gear train (36); a turbine rotating a transmission shaft (34) constrained to rotate with the inner planetary gear (60) of the epicyclic gear train (36); a fan (18) rigidly connected to the ring gear (66) of the epicyclic gear train (36); and an electric machine (70) comprising a rotor (72) and a stator (74), the rotor (72) being rigidly connected to the planet carrier (68) of the epicyclic gear train (36). Alternatively, the fan (18) is rigidly connected to the planet carrier and the electric machine (70) is rigidly connected to the ring gear. The invention also relates to methods for using said turbojet engine, in particular for controlling the reduction ratio between the transmission shaft and the turbine, in order to recover kinetic energy or for taxiing.
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公开(公告)号：US20220082332A1
公开(公告)日：2022-03-17
申请号：US17531987
申请日：2021-11-22
发明人： Roxane Koeune , Nicolas Fellin
IPC分类号： F28D7/10
摘要： A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the first and second fluid have a respective general direction of flow, and the general direction of flow of the first fluid is parallel to the general direction of flow of the second fluid. The present disclosure also concerns a turbine engine comprising the heat exchanger and a manufacturing method for manufacturing the heat exchanger.
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公开(公告)号：US20220074678A1
公开(公告)日：2022-03-10
申请号：US17479490
申请日：2021-09-20
发明人： Vincent Thomas , Bruno Servais , Roel Vleugels
摘要： In a matrix for a heat exchanger to exchange heat between a first fluid and a second fluid, the first fluid being for instance air and the second fluid being for instance oil, the matrix includes a channel for the first fluid, an array of passages for the second fluid, the passages extending in the channel. The array supports at least two cooling fins. The matrix is made by a process of additive manufacturing. The fins are inclined with respect to each other along the direction of the flow of the first fluid. The array defines rectangular corridors for the first fluid.
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公开(公告)号：US11236634B2
公开(公告)日：2022-02-01
申请号：US16650622
申请日：2019-06-20
发明人： Morgan Vyvey
摘要： The invention relates to a turbine engine (2) compressor shroud, comprising: first and second sections (130, 230) and respective flanges (131, 231), the flanges (131, 231) making it possible to hold the two sections (130, 230) together, the first section (130) comprising a cylindrical surface (137) forming a seat for an actuating device (136, 140, 166, 168, 170) for orienting stator blades (126), characterised in that the first shroud (130) comprises a tubular wall (132) axially overlapping both flanges (131, 231) and said cylindrical surface (137) is an outer surface of the tubular wall (132). The invention also relates to an assembly with the shroud (130, 230), the blade (126) and means (140) for actuating the orientation of the blade (126), the shroud being produced using the kit described above. The invention finally relates to a method for assembling a compressor with such an assembly.
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9.发明申请公开(公告)号：US20210062662A1
公开(公告)日：2021-03-04
申请号：US16644359
申请日：2018-08-30
发明人： Mathieu Renaud , Alain Derclaye , Sébastien Vacca
IPC分类号： F01D9/04
摘要： Assembly for axial turbomachine, in particular for an aircraft turbojet, the assembly comprising: an annular casing with an internal surface (40); an annular row of stator baffles (26) with at least one stator baffle (26) comprising an airfoil (50) which extends radially from a fixing platform (34), the fixing platform (34) being fixed to the casing and having a polygonal outline; characterised in that it further comprises a gasket (80) comprising a frame, the outline of which conforms to the polygonal outline of the fixing platform (34), the frame being in radial contact with the fixing platform (34) and the casing in order to ensure a seal.
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公开(公告)号：US10900366B2
公开(公告)日：2021-01-26
申请号：US16259262
申请日：2019-01-28
IPC分类号： F01D5/14 , F01D11/00 , F01D5/08 , F04D29/68 , F04D29/32 , F01D5/06 , F01D11/02 , F01D9/04 , F01D11/12
摘要： A turbomachine assembly and, in particular, a low-pressure compressor of an aircraft turbojet engine includes an annular row of upstream vanes with trailing edges extending radially from an upstream support; an annular row of downstream vanes with leading edges axially facing the trailing edges and extending radially from a downstream support; an annular passageway delimited by the upstream support and the downstream support. The downstream support has a profile with: an upstream portion delimiting the annular passageway forming an annular slide, a downstream portion axially at the level of downstream vanes, and a connecting arc connecting the upstream portion to the downstream portion. The connecting arc is arranged downstream of the leading edges.
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