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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：US20170241432A1
公开(公告)日：2017-08-24
申请号：US15436091
申请日：2017-02-17
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
CPC分类号： F04D29/327 , F02K3/06 , F04D19/002 , F04D21/00 , F04D29/324 , F04D29/666 , F05D2220/36 , F05D2240/302 , F05D2240/303 , F05D2240/307 , F05D2260/961
摘要： A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.
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公开(公告)号：US20230382539A1
公开(公告)日：2023-11-30
申请号：US17804570
申请日：2022-05-30
发明人： Alexandre CAPRON , Karan ANAND , Tammy YAM , Ali AZMI , Sylvain CLAUDE , Krishna Prasad BALIKE , Prakul MITTAL
摘要： An aircraft engine, has: an upstream stator having upstream stator vanes distributed about a central axis; and a downstream stator having downstream stator vanes distributed about the central axis, the downstream stator located downstream of the upstream stator, a number of the upstream stator vanes different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes; and a second vane differing from the first vane by a geometric parameter, the geometric parameter causing the second vane to have one or more of: a stiffness greater than that of the first vane, and a major portion of a leading edge of the second vane circumferentially overlapped by another one of the upstream stator vanes.
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公开(公告)号：US20170370374A1
公开(公告)日：2017-12-28
申请号：US15674865
申请日：2017-08-11
发明人： Hien DUONG , Krishna Prasad BALIKE , Thomas VEITCH , Keegan LOBO , Raman WARIKOO
摘要： A compressor rotor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented.
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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：US20160061042A1
公开(公告)日：2016-03-03
申请号：US14469948
申请日：2014-08-27
发明人： Hien DUONG , Krishna Prasad BALIKE , Thomas VEITCH , Raman WARIKOO , Keegan LOBO
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/145 , F04D29/324 , F05D2240/303 , F05D2250/71
摘要： A rotary airfoil in a gas turbine engine is provided. The airfoil includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. An axial component of a center of gravity of a cross-section taken chordally toward the tip of the airfoil being upstream relative to an axial component of a center of gravity of a cross-section taken chordally toward the root of the airfoil. A method for forming such blade is also presented.
摘要翻译： 提供了一种在燃气涡轮发动机中的旋转翼型件。 翼型件包括相对的压力和吸力侧面，它们在弦向相对的前缘和后缘处连接在一起。 压力和吸力侧在从根部到尖端的跨度方向上延伸。 横截面的轴向分量是相对于翼型向翼面的根部截取的横截面的重心的轴向分量在翼面上朝向翼型的末端方向向上延伸的横截面的轴向分量。 还提出了一种用于形成这种刀片的方法。
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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：US20180066522A1
公开(公告)日：2018-03-08
申请号：US15808060
申请日：2017-11-09
发明人： Raman WARIKOO , Krishna Prasad BALIKE , Keegan LOBO , Hien DUONG , Thomas VEITCH
CPC分类号： F01D5/141 , F01D9/041 , F04D29/324 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/301 , F05D2250/292
摘要： An airfoil for a gas turbine engine comprises at least three successive sections defined between a root and a tip. A first decrease of maximum thickness-to-chord ratios defined by a difference between a maximum thickness-to-chord ratio at the root and a maximum thickness-to-chord ratio at a first spanwise position, a second decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the first spanwise position and a maximum thickness-to-chord ratio at a second spanwise position, a third decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the second spanwise position and a maximum thickness-to-chord ratio at the tip, the second decrease being greater than the corresponding first and third decreases.
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公开(公告)号：US20160146012A1
公开(公告)日：2016-05-26
申请号：US14553119
申请日：2014-11-25
发明人： Raman WARIKOO , Krishna Prasad BALIKE , Keegan LOBO , Hien DUONG , Thomas VEITCH
CPC分类号： F01D5/141 , F01D9/041 , F04D29/324 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/301 , F05D2250/292
摘要： An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil. The spanwise distribution of maximum thicknesses decreases from the root to the tip. In one aspect, the spanwise distribution is stepped between a first portion extending from the root and a second portion extending to the tip.
摘要翻译： 燃气涡轮发动机中的翼型件包括在弦向相对的前缘和后缘处连接在一起的相对的压力和吸力侧。 压力和吸力侧从翼面的根部延伸到尖端。 翼型件具有翼型的弦横截面的最大厚度的翼展方向分布。 最大厚度的翼展方向分布从根部向尖端减小。 在一个方面，翼展方向分布在从根部延伸的第一部分和延伸到尖端的第二部分之间是阶梯状的。
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