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公开(公告)号：US20230392503A1
公开(公告)日：2023-12-07
申请号：US17805049
申请日：2022-06-02
发明人： Paul Aitchison , Paul Stone , Dikran Mangardich
CPC分类号： F01D5/147 , F01D5/021 , F01D5/3007 , F05D2240/307
摘要： A rotor of an aircraft engine has a plurality of blades extending radially from a disc. At least one of the blades has an airfoil, a root and a tip. The airfoil has a crack-mitigating rib extending chordwise along the airfoil. The crack-mitigating rib is disposed radially closer to the root than to the tip.
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公开(公告)号：US11927108B2
公开(公告)日：2024-03-12
申请号：US17396670
申请日：2021-08-07
发明人： Paul Stone , Dikran Mangardich
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/305 , F05D2240/306 , F05D2250/712
摘要： An integrated bladed rotor of a gas turbine engine is provided. The integrated bladed rotor includes a hub having a rotation axis and a radially outer platform relative to the rotation axis, and a plurality of blades extending radially outwardly from the outer platform of the hub. The blades are integrally formed with the hub to define a monolithic component with the hub. Two or more of the blades each include: an airfoil including a groove formed in an outer surface of the airfoil to mitigate crack propagation, and a root fillet providing a transition between the outer platform of the hub and the airfoil.
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公开(公告)号：US11353038B2
公开(公告)日：2022-06-07
申请号：US16861835
申请日：2020-04-29
发明人： Ignatius Theratil , Krishna Prasad Balike , Aldo Abate , Sean Kelly , Peter Townsend , Ronald Dutton , Anthony Brown , Paul Stone , Myron Klein , Milica Kojovic , Robert Venditti
摘要： The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.
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公开(公告)号：US11073082B2
公开(公告)日：2021-07-27
申请号：US16683552
申请日：2019-11-14
发明人： Richard Ivakitch , David Menheere , Paul Stone
IPC分类号： F02C7/047
摘要： A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.
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公开(公告)号：US10533420B2
公开(公告)日：2020-01-14
申请号：US15351783
申请日：2016-11-15
发明人： Paul Stone
摘要： A method of reducing stress concentration in a material subjected to a predominant stress in a direction parallel to an axial plane defined through an axis of a circular cylindrical hole in the material between a first material surface and a second material surface, the material having a material thickness defined between the first material surface and the second material surface, the method comprising: forming a first proximal recess in the first material surface on the axial plane having a depth less than the material thickness, the first proximal recess having an outer edge spaced a first proximal dimension in the axial plane from a first rim of the hole; and forming a second proximal recess in the second material surface on the axial plane having a depth less than the material thickness, the second proximal recess having an outer edge spaced a second proximal dimension in the axial plane from a second rim of the hole, wherein the first proximal dimension on the first material surface is diametrically opposite, relative to the hole, to the second proximal dimension on the second material surface.
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公开(公告)号：US20170175776A1
公开(公告)日：2017-06-22
申请号：US14976701
申请日：2015-12-21
发明人： Ignatius Theratil , Krishna Prasad Balike , Richard Ivakitch , Sean Michael Kelly , Peter Townsend , Ronald Dutton , Paul Stone , Robert Venditti , Daniel Fudge , Milica Kojovic , Aldo Abate
CPC分类号： F04D29/666 , F01D5/141 , F01D5/16 , F01D5/28 , F04D29/324 , F04D29/384
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：US11002293B2
公开(公告)日：2021-05-11
申请号：US15706311
申请日：2017-09-15
发明人： Karan Anand , Farid Abrari , Ernest Adique , Paul Aitchison , Daniel Fudge , Kari Heikurinen , Paul Stone , Tibor Urac , Thomas Veitch
摘要： A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.
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公开(公告)号：US10570741B2
公开(公告)日：2020-02-25
申请号：US15484425
申请日：2017-04-11
发明人： Paul Stone , Richard Ivakitch
摘要： A gas turbine engine rotor including a disc adapted to be mounted for rotation about an axis, the disc including an annular balancing flange integrally connected thereto, the balancing flange having a first radial dimension around a first arc angle and a second radial dimension greater than the first radial dimension around a second arc angle, the second arc angle corresponding to 360 minus the first arc angle, the second arc angle being less than 180 degrees, the balancing flange around the second arc angle defining a protuberance, the protuberance being defined through machining of the balancing flange, the protuberance compensating for an unbalance of the rotor.
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公开(公告)号：US10443411B2
公开(公告)日：2019-10-15
申请号：US15707133
申请日：2017-09-18
发明人： Thomas Veitch , Farid Abrari , Ernest Adique , Paul Aitchison , Daniel Fudge , Kari Heikurinen , Paul Stone , Tibor Urac
摘要： A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.
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公开(公告)号：US10689987B2
公开(公告)日：2020-06-23
申请号：US16562701
申请日：2019-09-06
发明人： Thomas Veitch , Farid Abrari , Ernest Adique , Paul Aitchison , Daniel Fudge , Kari Heikurinen , Paul Stone , Tibor Urac
摘要： A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.
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