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公开(公告)号：US20180274558A1
公开(公告)日：2018-09-27
申请号：US15465825
申请日：2017-03-22
发明人： Ignatius THERATIL , Krishna BALIKE
摘要： A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode. The cutback may be a tip trailing edge cutback at a span position located a distance away from the hub of at least 75% of the total span length. The selected natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 3rd or 6th natural vibration mode.
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公开(公告)号：US20200049076A1
公开(公告)日：2020-02-13
申请号：US16391627
申请日：2019-04-23
摘要： There is disclosed a diffuser pipe assembly having: a plurality of diffuser pipes circumferentially distributed around the central axis and configured for diffusing a flow of compressed air received from an impeller, the diffuser pipes having a diffuser conduit for directing the flow of compressed air, the diffuser conduit curving between an inlet end and an outlet end along a conduit axis, the diffuser conduit having a baseline surface, a first subset of the diffuser pipes having aero-dampers protruding from the baseline surfaces of their diffuser conduits such that the diffuser pipes of the first subset have a natural vibration frequency different than a natural vibration frequency of at least a second subset of the diffuser pipes.
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公开(公告)号：US20190145431A1
公开(公告)日：2019-05-16
申请号：US16245516
申请日：2019-01-11
发明人： Ignatius THERATIL , Krishna Prasad BALIKE , Sean Michael KELLY , Richard IVAKITCH , Peter TOWNSEND , Ronald DUTTON , Paul STONE , Robert VENDITTI , Daniel FUDGE , Milica KOJOVIC , Aldo ABATE
摘要： A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.
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公开(公告)号：US20190078589A1
公开(公告)日：2019-03-14
申请号：US15703472
申请日：2017-09-13
发明人： Thomas VEITCH , Farid ABRARI , Ernest ADIQUE , Daniel FUDGE , Kari HEIKURINEN , Paul STONE , Ignatius THERATIL , Peter TOWNSEND , Tibor URAC
CPC分类号： F04D29/666 , F01D5/16 , F04D29/324 , F04D29/327 , F04D29/668 , F05D2220/36 , F05D2240/307 , F05D2260/961
摘要： A rotor for a gas turbine engine comprises a rotor having a hub and blades around the hub, and extending from the hub to tips. The tips include first and second tip portions between their respective tip leading edge and tip trailing edge. Tips are spaced from a rotational axis of the rotor by spans. A mean span of a first tip portion of a first blade is greater than a mean span of a corresponding first tip portion of a second blade. A mean span of a second tip portion the first blade is less than a mean span of a corresponding second tip portion of the second blade.
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公开(公告)号：US20200149554A1
公开(公告)日：2020-05-14
申请号：US16591876
申请日：2019-10-03
发明人： Ignatius THERATIL , Krishna BALIKE
摘要： A rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 20% and 50% of the total span length. The selected natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 5th natural vibration mode.
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公开(公告)号：US20200049161A1
公开(公告)日：2020-02-13
申请号：US16100473
申请日：2018-08-10
摘要： The diffuser pipe assembly for a compressor of a gas turbine engine includes diffuser pipes circumferentially distributed around a central axis and configured for distributing a flow of compressed air from the compressor to the combustor. Each of the diffuser pipes curving between an inlet end and an outlet end. A first subset of the diffuser pipes has a natural vibration frequency different than a natural vibration frequency of at least a second subset of the diffuser pipes. A method of operating a compressor including the diffuser pipe assembly is also disclosed.
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公开(公告)号：US20180142565A1
公开(公告)日：2018-05-24
申请号：US15357158
申请日：2016-11-21
发明人： Ignatius THERATIL , Daniel COUTU , Nicola HOULE
IPC分类号： F01D11/12 , F16J15/3288 , F04D29/32 , F04D29/54 , F04D29/08 , F04D29/66 , F01D5/02 , F01D9/02 , F01D25/04
CPC分类号： F01D25/04 , F01D11/001 , F04D29/164 , F05D2240/56 , F05D2260/96 , F16J15/3288
摘要： The application is directed to a brush seal assembly adapted to be operatively mounted between a stator and a rotor of a gas turbine engine. The brush seal assembly comprises a housing and a seal operatively coupled to the housing. The seal comprises at least two annular brushes each having a plurality of bristles extending away from the housing. The at least two annular brushes and the housing defines a cavity therebetween. The housing defines at least one circumferential surface within the cavity. The housing comprises at least one discontinuity defined in the at least one circumferential surface. The at least one discontinuity disrupts a continuity of annularity of the circumferential surface.
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公开(公告)号：US20230349297A1
公开(公告)日：2023-11-02
申请号：US17661454
申请日：2022-04-29
发明人： Krishna Prasad BALIKE , Edwin WONG , Daniel FUDGE , Ignatius THERATIL , Paul STONE , Charles MASON , Karan ANAND , Pascal DORAN
CPC分类号： F01D5/16 , F01D5/141 , F05D2260/961 , F05D2240/305 , F05D2240/303 , F05D2240/304
摘要： A method includes: obtaining a rotor having a hub and a plurality of blades protruding from the hub, the plurality of blades including first blades and second blades disposed in alternation around a central axis of the rotor, natural vibration frequencies of the first blades different from natural vibration frequencies of the second blades; determining that a difference between a first natural vibration frequency of a first blade of the first blades and a second natural vibration frequency of a second blade of the second blades is below a threshold; and modifying a shape of the first blade until the difference between the first natural vibration frequency and the second natural vibration frequency is at or above the threshold.
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公开(公告)号：US20200080645A1
公开(公告)日：2020-03-12
申请号：US16127714
申请日：2018-09-11
发明人： Daniel COUTU , Ignatius THERATIL , Nicola HOULE
IPC分类号： F16J15/3288
摘要： There is disclosed a brush seal assembly including at least one annular bristle pack. The at least one annular bristle pack extends circumferentially around a central axis of the brush seal assembly. The at least one annular bristle pack has bristles extending along longitudinal axes from roots to free tips. The bristles extend toward a cylindrical plane of a the seal land. Projections of the free tips on the cylindrical plane define a bristle tip projection surface being non-axisymmetric. A method of operating a brush seal assembly is also disclosed.
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公开(公告)号：US20200072056A1
公开(公告)日：2020-03-05
申请号：US16674264
申请日：2019-11-05
发明人： Maksim PANKRATOV , Ignatius THERATIL , Tony CHANG , Nicola HOULE , Vincent SAVARIA , Daniel COUTU
IPC分类号： F01D5/10
摘要： The stiffness of a rotor part is varied over its circumference to allow damper rings to effectively work in high speed applications. Circumferentially spaced-apart pockets may be defined in the rotor to create discontinuous strain to increase the force required to lock the damper ring in the groove above the centrifugal force of the ring when the rotor is rotating.
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