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1985 条记录 (耗时 0.018 秒)

    POWER TURBINE SHAFT FOR DECOUPLED GAS GENERATOR
    2.
    发明公开
    POWER TURBINE SHAFT FOR DECOUPLED GAS GENERATOR 审中-公开

    公开(公告)号：EP4455448A2

    公开(公告)日：2024-10-30

    申请号：EP24173140.5

    申请日：2024-04-29

    申请人： RTX Corporation

    发明人： SOBANSKI, Jon Erik

    IPC分类号： F01D5/02 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F02K3/062

    摘要： A propulsion system (25) for an aircraft includes a propulsor section (34) that includes a fan with a plurality of fan blades (40) that are rotatable about a fan axis (A), a core engine (66) that is configured to generate a gas flow (30), a power turbine (44) where the gas flow (30) from the core engine is expanded to generate shaft power, and a power turbine shaft (48) that is coupled between the power turbine (44) and the propulsor section (34). The shaft (48) has an axial length (50) that is greater than half a distance between a leading edge (42) of the fan blades (40) and a mechanical coupling (46) of the shaft (48) to the power turbine (44), and an outer diameter that increases in a direction away from each end thereof.

    SYSTEM AND METHOD FOR MEASURING AN AXIAL POSITION OF A ROTATING COMPONENT
    3.
    发明公开
    SYSTEM AND METHOD FOR MEASURING AN AXIAL POSITION OF A ROTATING COMPONENT 审中-公开

    公开(公告)号：EP4450916A1

    公开(公告)日：2024-10-23

    申请号：EP24170890.8

    申请日：2024-04-17

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： SHENOUDA, Antwan

    IPC分类号： G01B7/00 ,  G01D5/20 ,  F02K3/06 ,  G01B7/14 ,  G01P3/488

    摘要： A system for measuring an axial position (54) of a phonic wheel (38) includes a phonic wheel (38) rotatable about a rotation axis and translatable along the rotation axis, a first sensor (40A), a second sensor (40B) and a computer (42). The phonic wheel (38) includes an inclined tooth (44A) having an axially non-uniform radial height and a reference tooth (44B) having an axially uniform radial height. The first sensor (40A) generates a positioning signal (50A) indicative of a gap between the inclined tooth (44A) and the first sensor (40A). The second sensor (40B) generates a reference signal (50B) indicative of a gap between the reference tooth (44B) and the reference sensor (40B). The first and second sensors (40A, 40B) have different orientations. The computer (42) generates an output indicative of the axial position (54) of the phonic wheel (38) based on the positioning signal (50A) and the reference signal (50B).

    PROPULSION SYSTEM ARRANGEMENT FOR TURBOFAN GAS TURBINE ENGINE
    7.
    发明公开
    PROPULSION SYSTEM ARRANGEMENT FOR TURBOFAN GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP4411128A3

    公开(公告)日：2024-10-09

    申请号：EP24184479.4

    申请日：2016-02-08

    申请人： RTX Corporation

    发明人： ECKETT, Christopher A. ,  SUCIU, Gabriel L.

    IPC分类号： F02K3/06 ,  F02C7/20 ,  F01D21/04 ,  F02K1/72 ,  F02K1/76 ,  F02K1/09

    CPC分类号： F02K1/09 ,  F02K1/72 ,  F02K3/06 ,  F02K1/763 ,  F01D21/045 ,  Y02T50/60

    摘要： An integrated propulsion system (10) comprises components that include a gas turbine engine (20) and a nacelle assembly (82). The nacelle assembly (82) includes a fan nacelle (86) arranged at least partially about a fan (42) and an engine. The system includes a fan section (22) at least partially defined by the fan nacelle (82), and the fan section (22) has a fan pressure ratio of less than about 1.7. The engine includes a turbine section (28) configured to drive the fan section (22) and a compressor section (24), the compressor section (24) including a first compressor (44) and a second compressor (52). An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor (44) and a pressure ratio across the second compressor (52), and wherein the overall pressure ratio is greater than or equal to about 35. The fan section (22) is configured to deliver a portion of air into the compressor section (24), and a portion of air into a bypass duct, and wherein a bypass ratio, defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section (24), is equal to or greater than about 5.

    AIRCRAFT ENGINE HAVING TWO RADIALLY OFFSET TURBINES
    8.
    发明公开
    AIRCRAFT ENGINE HAVING TWO RADIALLY OFFSET TURBINES 审中-公开

    公开(公告)号：EP4438867A1

    公开(公告)日：2024-10-02

    申请号：EP24164304.8

    申请日：2024-03-18

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： MENHEERE, David

    IPC分类号： F02C3/10 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F02K3/062 ,  F02K3/072

    摘要： An aircraft engine (10), has: a high-pressure spool (25) having a high-pressure turbine (18A) drivingly engaged to a high-pressure compressor (14A); and a low-pressure spool (26) having: a first low-pressure turbine (18B) downstream of the high-pressure turbine (18A); and a second low-pressure turbine (18C) downstream of the first low-pressure turbine (18B), one or more of the first low-pressure turbine (18B) and the second low-pressure turbine (18C) drivingly engaged to a rotatable load (12), the first low-pressure turbine (18B) and the second low-pressure turbine (18C) radially offset from one another relative to a central axis (11) of the aircraft engine (10).