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公开(公告)号：US11421536B2
公开(公告)日：2022-08-23
申请号：US17344099
申请日：2021-06-10
发明人： Yau-Wai Li , Peter Townsend , Vijay Kandasamy
摘要： A gas turbine engine includes rotor having a hub, and a plurality of blades extending generally radially from the hub. Each of the blades has an airfoil portion. The airfoil portion has a leading edge and a trailing edge defining a chordwise direction, and a root and a tip defining a spanwise direction. Only a sub-set of the blades has a cutback at at least one of the trailing edge and the leading edge. A method of designing and a method of assembling a rotor having noise reduction properties in a gas turbine engine is also presented.
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公开(公告)号：US20210293149A1
公开(公告)日：2021-09-23
申请号：US17344099
申请日：2021-06-10
发明人： Yau-Wai Li , Peter Townsend , Vijay Kandasamy
摘要： A gas turbine engine includes rotor having a hub, and a plurality of blades extending generally radially from the hub. Each of the blades has an airfoil portion. The airfoil portion has a leading edge and a trailing edge defining a chordwise direction, and a root and a tip defining a spanwise direction. Only a sub-set of the blades has a cutback at at least one of the trailing edge and the leading edge. A method of designing and a method of assembling a rotor having noise reduction properties in a gas turbine engine is also presented.
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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：US11041388B2
公开(公告)日：2021-06-22
申请号：US14673101
申请日：2015-03-30
发明人： Yau-Wai Li , Peter Townsend , Vijay Kandasamy
摘要： A gas turbine engine includes rotor having a hub, and a plurality of blades extending generally radially from the hub. Each of the blades has an airfoil portion. The airfoil portion has a leading edge and a trailing edge defining a chordwise direction, and a root and a tip defining a spanwise direction. Only a sub-set of the blades has a cutback at at least one of the trailing edge and the leading edge. A method of designing and a method of assembling a rotor having noise reduction properties in a gas turbine engine is also presented.
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公开(公告)号：US09879540B2
公开(公告)日：2018-01-30
申请号：US13795936
申请日：2013-03-12
发明人： Yau-Wai Li , Karan Anand , Peter Townsend
CPC分类号： F01D5/143 , F01D9/04 , F05D2240/10 , F05D2240/301 , F05D2240/304 , F05D2240/80 , F05D2250/711 , F05D2250/712 , Y02T50/673
摘要： Compressor stators (22) for gas turbine engines (10) are disclosed. An exemplary compressor stator (22) comprises a circumferential array of stator vanes (28) and a shroud (24, 26) for supporting the stator vanes (28). The shroud (24, 26) has a circumferentially extending inner endwall (30, 32) exposed to an annular gas path (20) of the compressor (14). The endwall (30, 32) has a circumferentially uniform axial cross-sectional profile (42). The axial cross-sectional profile (42) comprises at least one deviation (48, 50) from a nominal axial cross-sectional profile (44) defining an overall shape of the annular gas path (20). The at least one deviation comprises a concave deviation (48) and a convex deviation (50).
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