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公开(公告)号：WO2015142395A3
公开(公告)日：2015-11-19
申请号：PCT/US2014070278
申请日：2014-12-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ALARCON ANDREW G , TATTON ROYCE E , FORD BARRY M , LI LINDA S , TURNER MATTHEW A
CPC classification number: 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
Abstract: 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.
Abstract translation: 本公开总体上涉及用于燃气涡轮发动机的风扇叶片平台领域。 更具体地，本公开涉及一种用于燃气涡轮发动机的压缩的短切纤维风扇叶片平台。
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公开(公告)号：WO2015175073A3
公开(公告)日：2016-01-14
申请号：PCT/US2015016584
申请日：2015-02-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
CPC classification number: 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
Abstract: 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.
Abstract translation: 燃气涡轮发动机包括风扇部分，压缩机部分和涡轮部分，其中之一包括翼型件。 翼型件包括从径向方向延伸的压力和吸力侧，从内部流动路径位置处的0％跨度位置到翼型端部处的100％跨度位置。 翼型具有不在轴向视图中的最大弦长突出部。
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公开(公告)号：SG11201403700YA
公开(公告)日：2014-10-30
申请号：SG11201403700Y
申请日：2012-12-28
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL
Abstract: A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the propulsor and the spool such that rotation of the spool results in rotation of the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge such that the chord forms a stagger angle α with the axis. The stagger angle α is less than 62° at all positions along the span, with said hub being at 0% of the span and the tip being at 100% of the span.
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公开(公告)号：EP3108100A4
公开(公告)日：2017-11-22
申请号：EP14882896
申请日：2014-08-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F02C7/36 , F04D29/324 , F04D29/325 , F04D29/386 , F05D2200/222 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/713 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for 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 leading edge location and a span position that corresponds to a curve that is at least a third order polynomial with a generally S-shaped curve that has an initial negative slope followed by a positive slope and then a second negative slope. The positive slope leans toward the suction side and the negative slopes lean toward the pressure side.
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公开(公告)号：EP3108105A4
公开(公告)日：2017-12-06
申请号：EP14883503
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
CPC classification number: F01D5/141 , F02C3/04 , F02C7/36 , F04D29/324 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for a turbine engine 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 relationship between an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/−0.04 inch (1.01 mm) per 1% span.
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Patent Agency Ranking
公开(公告)号：EP3108114A4
公开(公告)日：2017-03-15
申请号：EP15752887
申请日：2015-02-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
IPC: F01D5/14
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F02C3/14 , F02C7/36 , F02K3/04 , F04D29/325 , F05D2220/36 , F05D2240/35 , F05D2250/71 , F05D2250/713 , F05D2250/75 , F05D2260/4031 , F05D2270/3013 , Y02T50/672 , Y02T50/673
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公开(公告)号：EP3108106A4
公开(公告)日：2017-03-15
申请号：EP14883515
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
CPC classification number: F01D5/141 , F01D5/14 , F01D5/145 , F04D29/324 , F04D29/325 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: 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 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, and a negative dihedral corresponds to pressure side-leaning.
Abstract translation: 用于涡轮发动机的翼型件包括翼型件，该翼型件具有从径向方向从内部流动路径位置处的0％跨度位置延伸至翼型尖端处的100％跨距位置的压力侧和吸力侧。 翼型在前缘二面角和跨度位置之间具有关系。 前缘二面角从0％跨度位置到100％跨度位置为负值。 正二面角对应于吸力侧倾，负二面角对应于压力侧倾。
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公开(公告)号：EP3108109A4
公开(公告)日：2017-03-15
申请号：EP15751738
申请日：2015-02-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
IPC: F01D5/14
CPC classification number: F01D5/141 , F02C3/107 , F02K3/00 , F02K3/06 , F04D29/384 , F05D2200/222 , F05D2220/323 , F05D2220/36 , F05D2240/301 , F05D2250/713 , Y02T50/672 , Y02T50/673
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公开(公告)号：EP3108101A4
公开(公告)日：2017-03-15
申请号：EP14883036
申请日：2014-08-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F02C7/36 , F02K3/06 , F04D29/324 , F04D29/325 , F04D29/386 , F05D2220/32 , F05D2220/36 , F05D2250/314 , Y02T50/672 , Y02T50/673
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公开(公告)号：EP3108103A4
公开(公告)日：2017-02-22
申请号：EP14883154
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL , FORD BARRY M
IPC: F01D5/14
CPC classification number: F04D29/38 , F01D5/141 , F02C3/04 , F02C7/36 , F02K3/06 , F04D29/325 , F05D2220/32 , F05D2220/36 , F05D2240/35 , Y02T50/672 , Y02T50/673
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