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公开(公告)号：WO2014099085A3
公开(公告)日：2014-09-18
申请号：PCT/US2013062104
申请日：2013-09-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOMZER DAVID , SCHWARZ FREDERICK M
CPC classification number: F01D25/28 , F02C7/20 , F02K3/06 , F05D2260/4031 , Y02T50/672
Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.
Abstract translation: 燃气涡轮发动机包括可围绕轴线旋转的多个风扇叶片，其中多个风扇叶片中的每一个包括前缘。 燃气涡轮发动机还包括涡轮部分，其包括具有后缘的后部大多数涡轮机叶片和由涡轮机部分驱动的用于使多个风扇叶片绕轴线旋转的齿轮架构。 燃气涡轮发动机的重心位于距离尾部最大涡轮机叶片的后缘的第一轴向距离处，其在多个风扇叶片的前缘之间的总长度的约35％和约75％之间， 尾部最后端的涡轮叶片。
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公开(公告)号：CA2884976C
公开(公告)日：2018-03-06
申请号：CA2884976
申请日：2013-09-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOMZER DAVID , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.
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公开(公告)号：CA2884976A1
公开(公告)日：2014-06-26
申请号：CA2884976
申请日：2013-09-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOMZER DAVID , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.
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公开(公告)号：EP2904210A4
公开(公告)日：2015-12-02
申请号：EP13865250
申请日：2013-09-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOMZER DAVID , SCHWARZ FREDERICK M
CPC classification number: F01D25/28 , F02C7/20 , F02K3/06 , F05D2260/4031 , Y02T50/672
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