公开(公告)号：US20140165582A1

公开(公告)日：2014-06-19

申请号：US13716247

申请日：2012-12-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Victor Pascu ,  Nipulkumar G. Shah

IPC: F02C7/18 ,  F02C9/16

CPC classification number: F02C9/16 ,  F02C3/08 ,  F02C3/14 ,  F02C7/06 ,  F05D2260/20 ,  Y02T50/671 ,  Y02T50/675

Abstract: An embodiment of the present invention is a gas turbine engine including a compressor, a turbine, an annular combustor, an exhaust duct, a first engine shaft bearing, and a second engine shaft bearing. The turbine has an axial flow direction toward the compressor. The combustor has an axial flow direction away from the compressor. The exhaust duct is disposed between the compressor and the combustor. The first engine shaft bearing is disposed on an axial side of the compressor opposite the turbine. The second engine shaft bearing is disposed on an axial side of the turbine opposite the compressor.

Abstract translation: 本发明的一个实施例是一种燃气涡轮发动机，其包括压缩机，涡轮机，环形燃烧器，排气管，第一发动机轴轴承和第二发动机轴轴承。 涡轮机具有朝向压缩机的轴向流动方向。 燃烧器具有远离压缩机的轴向流动方向。 排气管设置在压缩机和燃烧器之间。 第一发动机轴轴承设置在与涡轮机相对的压缩机的轴向侧。 第二发动机轴轴承设置在与压缩机相对的涡轮的轴向侧。