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公开(公告)号：EP3108104A4
公开(公告)日：2018-05-23
申请号：EP14883170
申请日：2014-08-25
发明人： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
CPC分类号： F04D29/325 , F01D5/141 , F02K3/06 , F04D19/002 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/30 , Y02T50/672 , Y02T50/673
摘要： An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning. The trailing edge sweep angle is positive from 0%-95% span. A positive-most trailing edge sweep angle is within the range of 10° to 20° in the range of 40-70% span position. The airfoil is a fan blade for the turbine engine.
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公开(公告)号：EP3108118A4
公开(公告)日：2018-01-03
申请号：EP15793127
申请日：2015-02-19
发明人： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
CPC分类号： F04D29/384 , F01D5/141 , F02C3/04 , F02K3/06 , F04D29/325 , F04D29/388 , F05D2220/323 , F05D2220/36 , F05D2240/301 , F05D2240/303 , F05D2240/35 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a maximum chord length projection that is not in an axial view.
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公开(公告)号：EP3108110A4
公开(公告)日：2018-01-03
申请号：EP15752013
申请日：2015-02-19
发明人： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/02 , F02C3/107 , F02K3/00 , F05D2200/222 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/30 , F05D2240/301 , F05D2250/713 , F05D2260/40311 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starting at the 0% span position is either zero or positive. The first critical point is in the range of 5-15% span.
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公开(公告)号：EP3102791A4
公开(公告)日：2017-12-13
申请号：EP14886052
申请日：2014-12-15
发明人： ALARCON ANDREW G , TATTON ROYCE E , FORD BARRY M , LI LINDA S , TURNER MATTHEW A
CPC分类号： F01D25/005 , B29C70/12 , B29D99/0025 , B29K2105/12 , F01D11/008 , F02K3/06 , F04D29/325 , F05D2220/36 , F05D2240/30 , F05D2240/80 , F05D2300/123 , F05D2300/2102 , F05D2300/224 , F05D2300/434 , F05D2300/436 , F05D2300/603 , Y02T50/672
摘要： The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.
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公开(公告)号：EP3114321A4
公开(公告)日：2018-01-03
申请号：EP15751617
申请日：2015-02-17
发明人： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/02 , F01D15/12 , F02C3/04 , F02C3/14 , F05D2220/32 , F05D2220/36 , F05D2250/71 , Y02T50/672 , Y02T50/673
摘要： An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.
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