公开(公告)号：US20120114479A1

公开(公告)日：2012-05-10

申请号：US13337354

申请日：2011-12-27

申请人： Joseph B. Staubach

发明人： Joseph B. Staubach

IPC分类号： F01D1/04

CPC分类号： F02C3/107 ,  F02K3/06

摘要： A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case than the front compressor case portion. A support member extends between the fan section and the front compressor case portion.