US 12,129,787 B2
Inter-turbine burner in recuperation cycle engine
Joseph B. Staubach, Colchester, CT (US); Joseph E. Turney, Amston, CT (US); and Neil J. Terwilliger, Cheshire, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jan. 27, 2023, as Appl. No. 18/102,356.
Prior Publication US 2024/0254913 A1, Aug. 1, 2024
Int. Cl. F02C 3/30 (2006.01)
CPC F02C 3/30 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/35 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A turbine engine assembly comprising:
a compressor section where a core airflow is compressed;
a combustor section where the compressed core airflow from the compressor section is mixed with fuel and ignited to generate an exhaust gas flow;
a turbine section including at least two turbine stages through which the exhaust gas flow expands to generate a mechanical power output;
an inter-turbine burner disposed between the at least two turbine stages, wherein in the inter-turbine burner an additional amount of fuel is mixed with the exhaust gas flow to generate a reheated gas flow;
a condenser where water is extracted from the reheated gas flow exhausted from the turbine section; and
an evaporator system disposed between a turbine stage of the at least two turbine stages and the condenser, the evaporator system configured for generating a steam flow from at least a portion of water extracted by the condenser for injection into the core airflow, wherein the evaporator system includes a first evaporator disposed between a first turbine stage and a second turbine stage of the at least two turbine stages and a second evaporator disposed between the turbine section and the condenser.