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公开(公告)号：EP4001597A1
公开(公告)日：2022-05-25
申请号：EP21209876.8
申请日：2021-11-23
摘要： A gas turbine engine (20) includes at least one shaft that interconnects a compressor section (24) and a turbine section (28). A starter turbine (90) provides torque to the at least one shaft (118) during an engine start event. The starter turbine (90) includes an air inlet (108) and an outlet (112). A buffer air system (140) is in fluid communication with the starter turbine (90) and is configured to receive air associated with the outlet (112) to supplement sealing of a bearing compartment sealing system.
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公开(公告)号：EP3862552A1
公开(公告)日：2021-08-11
申请号：EP21156240.0
申请日：2021-02-10
IPC分类号： F02C7/06
摘要： A lubrication system (60) for a gas turbine engine (20) includes a primary fluid tank (62) to receive a primary fluid, at least one secondary fluid tank (64) to receive at least one fluid additive, and a mixer (66). The mixer (66) has at least a first inlet (68) in fluid communication with the primary fluid tank (62) and a second inlet (70) in fluid communication with the at least one secondary fluid tank (64). The mixer (66) has at least one outlet (72) that delivers a mixture of the primary fluid and the at least one fluid additive to a gas turbine engine component (74).
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公开(公告)号：EP3760545A1
公开(公告)日：2021-01-06
申请号：EP20184058.4
申请日：2020-07-03
发明人： WAGNER, Joel H. , SCHLICHTING, Kevin W. , MURPHY, Michael Joseph , ZYSMAN, Steven H. , SAWYERS-ABBOTT, Nigel David , CONSIGLIO, Andrew A. , HALDERMAN IV, Charles Waldo
摘要： An environmental sampling system (60) includes a passage (62) in an aircraft component and a removable collector (64) disposed in the passage (62). The passage (62) has an inlet (62a) at a first region (R1) and an outlet (62b) at a second region (R2). When the aircraft (21) component is in operation the first region (R1) is at a greater pressure than the second region (R2) such that air flows through the passage (62) from the inlet (62a) to the outlet (62b). The removable collector (64) is configured to retain constituents from the air and to react with the media designed to mimic corrosion effects seen at higher temperatures on engine parts. The constituents can then be characterized and correlated to engine deterioration (94) to predict maintenance activity.
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公开(公告)号：EP4036376A1
公开(公告)日：2022-08-03
申请号：EP21214893.6
申请日：2021-12-15
摘要： A seal system has: a first member including a seal with a seal face; and
a second member including a seat (212) with a seat face and a plurality of cooling passageways (320). The second member is rotatable about an axis relative to the first member. The seal face and the seat face are in sliding sealing engagement The cooling passageways (320) have respective surface enhancements (322).-
公开(公告)号：EP4012167A1
公开(公告)日：2022-06-15
申请号：EP21213880.4
申请日：2021-12-10
摘要： A passive transpirational flow acoustic liner assembly (61;161) for a gas turbine engine (20) includes a guide vane (64;164) assembly and a conduit (80;180) configured to deliver airflow received from the guide vane (64;164). The guide vane (64;164) assembly includes an airfoil having a transpirational flow acoustic liner (100;200). The acoustic liner (100;200) includes a face sheet (106) defining a portion of an outer surface of the airfoil and having a plurality of first apertures (116), a segmented member (108) coupled to the face sheet (106) and having a plurality of chambers (110) in fluid communication with the outer surface via the plurality of first apertures (116), a backing sheet (112) having a plurality of apertures (118) and being coupled to the segmented member (108) such that the segmented member (108) is positioned between the face sheet (106) and the backing sheet (112), and a plenum (114) coupled to the backing sheet (112) opposite the segmented member (108) and fluidly connected to the conduit (80;180).
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公开(公告)号：EP3964693A1
公开(公告)日：2022-03-09
申请号：EP21191481.7
申请日：2021-08-16
摘要： A vane (60) for use in a gas turbine engine (20) includes an airfoil having a suction side (96) and a pressure side (94), and a transpirational flow acoustic liner (98) disposed in the airfoil. The liner (98) includes a face sheet (101) defining a portion of an outer surface of the airfoil and having a plurality of first apertures (110), a segmented member (102) coupled to the face sheet (101), and a backing sheet (106) coupled to the segmented member (102) the segmented member (102) such that the segmented member (102) is positioned between the face sheet (101) and the backing sheet (106). The segmented member (102) includes a plurality of chambers (104) in fluid communication with the outer surface (68) via the plurality of first apertures (110). The backing sheet (106) has a plurality of second apertures (112).
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公开(公告)号：EP4249731A1
公开(公告)日：2023-09-27
申请号：EP23158339.4
申请日：2023-02-23
摘要： An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor (212, 222, 232), cause the processor (212, 222, 232) to perform operations comprising: commanding, via the processor (212, 222, 232), a first scan of a bladed rotor (100) ; generating, via the processor, a three-dimensional model based on a first set of data received from a first scanner (310); comparing, via the processor (212, 222, 232), the three-dimensional model to an acceptable three-dimensional model of the bladed rotor (100); determining, via the processor (212, 222, 232), areas of interest based on the comparison; and commanding, via the processor (212, 222, 232), a contact probe (1010) to perform a non-destructive inspection on the areas of interest.
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公开(公告)号：EP4039597A1
公开(公告)日：2022-08-10
申请号：EP22165499.9
申请日：2018-08-14
IPC分类号： B64D27/26
摘要： A turbofan engine (20) may comprise an inlet (64) and a fan case (66) coupled to the inlet (64). An engine case (36) may be coupled to the fan case (66) via a vane (70) extending between the fan case (66) and the engine case (36). A strut apparatus (75) may extend from the fan case (66) and limit deflection of the fan case (66). The strut apparatus (75) may comprise a first end (100) proximate the fan case (66), and a second end (102) coupled to at least one of the engine case (36) or a structure for mounting the turbofan engine (20) to an aircraft.
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公开(公告)号：EP4258073A1
公开(公告)日：2023-10-11
申请号：EP23164474.1
申请日：2023-03-27
摘要： A method can comprise receiving (702), via the processor (602), one of a point cloud and a three-dimensional model for an inspected integrally bladed rotor (IBR) (100) and a defect (140) including a defect shape, a defect size, and a defect location; performing (210), via the processor (602), a simulation of a rotor module (111) in a gas turbine engine (20), the rotor module including the inspected IBR with a potential repaired defect; determining, via the processor, the potential repaired defect would produce an estimated life less than a design life for the inspected IBR; determining, via the processor, the estimated life would exceed a remaining life threshold for the inspected IBR; and generating (712), via the processor, a repair process for the potential repaired defect.
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公开(公告)号：EP3960992A2
公开(公告)日：2022-03-02
申请号：EP21187058.9
申请日：2021-07-21
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.
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