Patent ID: 9534541
Date: 2017-01-03
CPC Classifications: F02C

Claim:
1. A gas turbine engine, comprising: a primary combustor operatively coupled between a compressor unit and a first turbine; a reheat combustor operatively coupled between the first turbine and a second turbine; and a control unit comprising: a first bypass channel operatively coupled between an outlet of the first turbine and an inlet of the second turbine and configured to bypass the reheat combustor; a second bypass channel operatively coupled between a first outlet of the compressor unit and the inlet of the second turbine and configured to bypass the reheat combustor and the first turbine; a first control valve operatively coupled to the first bypass channel and configured to direct at least a first portion of exhaust gas from the first turbine to the inlet of the second turbine via the first bypass channel; and a second control valve operatively coupled to the second bypass channel and configured to direct at least a first portion of compressed air from the compressor unit to the inlet of the second turbine via the second bypass channel, wherein the first portion of compressed air is combined with the first portion of exhaust gas at the inlet of the second turbine.