Gas turbine engine

Abstract

A gas turbine engine (10) comprises: a low pressure compressor (18) comprising a centrifugal compressor stage (24); a low pressure turbine (44) configured to drive a load (12), the low pressure turbine (44) being provided rearwardly of the low pressure compressor (18); a high pressure turbine (42) provided rearwardly of the low pressure turbine (44); a combustor (40) provided rearwardly of the high pressure turbine (42); a high pressure compressor (32) provided rearwardly of the combustor (40); and an intercooler heat exchanger (28) configured to exchange heat between core airflow (B) exiting the low pressure compressor (18) and fan airflow (A), wherein the high pressure turbine (42) and high pressure compressor (32) are coupled by a high pressure shaft (46), and the low pressure turbine (44), low pressure compressor (18) and load (12) are coupled by a low pressure shaft (22).

Dependencies are inferred from the claim text.