公开(公告)号：WO2014099085A2

公开(公告)日：2014-06-26

申请号：PCT/US2013/062104

申请日：2013-09-27

Applicant: UNITED TECHNOLOGIES CORPORATION

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。 该燃气涡轮发动机还包括涡轮部分，该涡轮部分包括最后涡轮叶片，该涡轮叶片具有后缘和由涡轮部分驱动的齿轮架构，用于使多个风扇叶片围绕轴线旋转。 燃气涡轮发动机的重心位于距最后涡轮叶片的后缘的第一轴向距离处，该距离介于多个风扇叶片的前缘之间的总长度的大约35％与大约75％之间， 大多数涡轮叶片的后缘。

公开(公告)号：WO2015006472A1

公开(公告)日：2015-01-15

申请号：PCT/US2014/045991

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： ROACH, James, T. ,  WATSON, Charles, R. ,  COOK III, Grant, O. ,  KLING, Colin, J. ,  BUGAJ, Shari, L. ,  LEVASSEUR, Glenn ,  GALOS, Camelia ,  BOMZER, David

IPC: A63B59/00 ,  A63B59/12 ,  A63B49/10 ,  A63C5/14 ,  A63B65/02

CPC classification number: A63C5/003 ,  A63B37/0001 ,  A63B49/10 ,  A63B59/00 ,  A63B59/70 ,  A63B65/02 ,  A63B2209/00 ,  A63C5/12 ,  B32B27/08 ,  B32B27/281 ,  B32B27/285 ,  B32B27/286 ,  B32B27/30 ,  B32B27/34 ,  B32B27/36 ,  B32B27/40 ,  B32B2255/10 ,  B32B2255/205 ,  B32B2262/101 ,  B32B2262/103 ,  B32B2262/106 ,  B32B2270/00 ,  B32B2307/554 ,  B63B35/7909 ,  B63B2035/715

Abstract: Metal-plated polymeric components and other materials having improved properties such as increased interfacial bond strengths, increased durability, increased heat resistance, and improved wear and erosion resistance are described. Methods for fabricating such metal- plated polymeric components and other materials are also described.

Abstract translation: 描述了具有改进性能的金属镀覆聚合物组分和其它材料，例如增加的界面粘合强度，增加的耐久性，增加的耐热性和改善的耐磨性和耐冲蚀性。 还描述了制造这种金属镀覆的聚合物组分和其它材料的方法。

公开(公告)号：EP2904210A2

公开(公告)日：2015-08-12

申请号：EP13865250.8

申请日：2013-09-27

Applicant: United Technologies Corporation

Inventor： BOMZER, David ,  SCHWARZ, Frederick M.

IPC: F01D5/14 ,  F02C7/00

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。 该燃气涡轮发动机还包括涡轮部分，该涡轮部分包括最后涡轮叶片，该涡轮叶片具有后缘和由涡轮部分驱动的齿轮架构，用于使多个风扇叶片围绕轴线旋转。 燃气涡轮发动机的重心位于距最后涡轮叶片的后缘的第一轴向距离处，该距离介于多个风扇叶片的前缘之间的总长度的大约35％与大约75％之间， 大多数涡轮叶片的后缘。