公开(公告)号：EP2591219B1

公开(公告)日：2016-05-11

申请号：EP11743295.5

申请日：2011-07-05

申请人： Turbomeca

发明人： BEDRINE, Olivier ,  MARCONI, Patrick ,  PUERTO, Alphonse

IPC分类号： F02C6/02

CPC分类号： F02C6/00 ,  F02C1/04 ,  F02C6/02 ,  F02C7/10 ,  F02C7/36 ,  Y02E20/14 ,  Y02T50/671

公开(公告)号：EP2591219A1

公开(公告)日：2013-05-15

申请号：EP11743295.5

申请日：2011-07-05

申请人： Turbomeca

发明人： BEDRINE, Olivier ,  MARCONI, Patrick ,  PUERTO, Alphonse

IPC分类号： F02C6/02

CPC分类号： F02C6/00 ,  F02C1/04 ,  F02C6/02 ,  F02C7/10 ,  F02C7/36 ,  Y02E20/14 ,  Y02T50/671

摘要： The invention aims to get around the problems of size, mass or reliability. To do this, energy is recovered in the exhaust nozzle, converted and recirculated using mechanical and/or electrical power recombining means. An example of an architecture of a turbomachine according to the invention includes a main turbine engine (1) and a heat exchanger (18) positioned in the exhaust nozzle (70) and coupled, via pipes (18a and 18b), to an independent system (16) that converts thermal energy into mechanical energy. This independent system (16) is connected to localized (Z1) mechanical recombination means (20) via a power shaft (15) to supply power to a power transmission shaft (80) according to aircraft requirements.