Patent ID: 7877980
Filing Date: 2011-02-01
Classification: F02K

Abstract:
1. A gas turbine engine, comprising: (a) a first turbomachinery core; (b) a second turbomachinery core adjacent to the first core; (c) a low pressure turbine disposed downstream of the first and second cores and in flow communication with at least one of the first and second cores; (d) a rotating fan disposed upstream of the first and second cores and in mechanical communication with the low pressure turbine; (e) at least one inlet control flap disposed downstream of the fan and upstream of the first and second cores, the at least one inlet control flap having at least two positions, wherein: a first position permits flow communication between the fan and the first core and prevents flow communication between the fan and the second core; and a second position permits flow communication between the fan and the second core and prevents flow communication between the fan and the first core; and (f) at least one outlet control flap disposed downstream of the first and second cores and upstream of the low pressure turbine, the at least one outlet control flap having at least two positions, wherein: a first position permits flow communication between the first core and the low pressure turbine; and a second position permits flow communication between the second core and the low pressure turbine.