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公开(公告)号：US10724540B2
公开(公告)日：2020-07-28
申请号：US15370497
申请日：2016-12-06
发明人： Yau-Wai Li , Peter Townsend , Ronald Dutton , Bernadette Mason
摘要： A turbofan engine is disclosed having a bypass duct with an asymmetry in aerodynamic profile caused by a local obstruction in the bypass duct. The engine comprises stator vanes circumferentially spaced-apart around a circumference of the bypass duct. A first group of adjacent stator vanes includes a majority of the plurality of stator vanes and are arranged in a first circumferential sector of the bypass duct and have equal stagger angles. A second group of adjacent stator vanes includes a minority of the plurality of stator vanes and are arranged in a second circumferential sector circumferentially positioned relative to the local obstruction. The stator vanes of the second group have stagger angles different from the stagger angles of the stator vanes of the first group.
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公开(公告)号：US10215194B2
公开(公告)日：2019-02-26
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
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：US10670041B2
公开(公告)日：2020-06-02
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
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：US10094223B2
公开(公告)日：2018-10-09
申请号：US14207957
申请日：2014-03-13
发明人： Hong Yu , Ronald Dutton
摘要： A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.
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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：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：US10808556B2
公开(公告)日：2020-10-20
申请号：US16122295
申请日：2018-09-05
发明人： Hong Yu , Ronald Dutton
摘要： A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.
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公开(公告)号：US09759230B2
公开(公告)日：2017-09-12
申请号：US14163588
申请日：2014-01-24
发明人： Kari Heikurinen , Ronald Dutton
CPC分类号： F04D29/541 , F01D5/143 , F01D5/145 , F04D19/028 , F04D29/547 , F04D29/681 , F05D2270/17
摘要： A multi-stage axial compressor with an inner wall including a step portion for each of the compressor stages. Each step portion is defined along a respective stage. Each step portion may extend over at least a majority of an axial length of the stage. Each step portion may optionally include a point aligned with a maximum thickness of the airfoil portions of the rotor blades and a point aligned with a maximum thickness of the stator vanes. Adjacent step portions are connected by a transition portion converging toward a central axis of the compressor from the upstream step to the downstream step. Each transition portion has a steeper slope than that of the adjacent step portions. A method of directing flow through a multi-stage axial flow compressor is also discussed.
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