Patent ID: 8176725
Filing Date: 2012-05-15
Classification: F02C,F02K,F05D,Y02T

Abstract:
1. A gas turbine engine comprising: a fan drive gear system comprising: a low spool connected to the fan drive gear system, the low spool comprising: a high spool disposed aft of the low spool, the high spool comprising: a reverse ducting disposed radially outward of the high spool for directing output of the rearward-flow low pressure compressor to the forward-flow high pressure compressor such that the output reverses flow to pass through the high spool; exhaust ducting disposed radially outward of the reverse ducting for receiving exhaust gas from the forward-flow low pressure turbine and fan air from the turbofan: and an intercooling and recuperating heat exchanger mounted adjacent the reverse ducting between the rearward-flow low pressure compressor and the forward-flow high pressure compressor; wherein flow through the engine extends sequentially through the rearward-flow low pressure compressor in a downstream direction, and through the forward-flow high pressure compressor, the combustor, the forward-flow high pressure turbine and the forward-flow low pressure turbine in a forward direction.