公开(公告)号：US20160047304A1

公开(公告)日：2016-02-18

申请号：US14146758

申请日：2014-01-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Joseph Brent Staubach

IPC: F02C3/107 ,  F02C7/36

CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  Y02T50/671

Abstract: A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the compressors connected to rotate with the fan rotor, and the third turbine driving the upstream compressor and the fan both through a gear reduction. A second intermediate compressor is driven by the second intermediate turbine rotor, and a third compressor downstream of the first and second compressors is driven by the first turbine rotor.

Abstract translation: 燃气涡轮发动机包括位于第二中间涡轮机的上游的第一涡轮机和位于第一和第二涡轮机下游的第三涡轮机。 一个风扇和三个压缩机，其上游的一个压缩机连接成与风扇转子一起旋转，第三个涡轮通过齿轮减速器驱动上游压缩机和风扇。 第二中间压缩机由第二中间涡轮转子驱动，第一和第二压缩机下游的第三压缩机由第一涡轮转子驱动。

公开(公告)号：US20150377124A1

公开(公告)日：2015-12-31

申请号：US14793795

申请日：2015-07-08

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C3/107 ,  F02K3/02 ,  F01D5/06 ,  F01D9/04 ,  F01D25/24

CPC classification number: F02C3/107 ,  F01D9/041 ,  F01D25/24 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311

Abstract: A turbofan engine includes an engine case, a gaspath through the engine case, a fan having a circumferential array of fan blades, a compressor in fluid communication with the fan, a combustor in fluid communication with the compressor, and a turbine in fluid communication with the combustor. The turbine has a fan drive turbine section having 3 to 6 blade stages. A speed reduction mechanism couples the fan drive turbine section to the fan. A bypass area ratio is between about 8.0 and about 20.0. A ratio of maximum gaspath radius along the fan drive turbine section to maximum radius of the fan is less than about 0.50. A ratio of a turbine section airfoil count to the bypass area ratio is between about 10 and about 170. The fan drive turbine section airfoil count being the total number of blade airfoils and vane airfoils of the fan drive turbine section.

Abstract translation: 涡轮风扇发动机包括发动机壳体，通过发动机壳体的气路，具有圆周阵列的风扇叶片的风扇，与风扇流体连通的压缩机，与压缩机流体连通的燃烧器，以及与压缩机流体连通的涡轮机 燃烧器。 涡轮机具有风扇驱动涡轮机部分，具有3到6个叶片级。 减速机构将风扇驱动涡轮部分连接到风扇。 旁路面积比在约8.0和约20.0之间。 风扇驱动涡轮机部分的最大气路径半径与风扇的最大半径的比值小于约0.50。 涡轮机翼型计数与旁路面积比的比率在约10和约170之间。风扇驱动涡轮机翼型计数是风扇驱动涡轮机部分的叶片翼型和叶片翼型的总数。