Patent ID: 11859539
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. An aircraft propulsion system, the propulsion system comprising:
a low pressure (LP) spool comprising a fan section, a LP compressor, and an LP turbine;
a core engine comprising a high pressure (HP) compressor, a combustion section, and an HP turbine, wherein the HP compressor and the HP turbine together form a rotatable HP spool;
a frame positioned in serial flow arrangement between the HP turbine and the LP turbine, wherein the frame comprises a strut defining an inter-turbine burner, the inter-turbine burner comprising an outlet opening defined along a trailing edge of the strut, wherein the outlet opening is in fluid communication with a core flowpath of the propulsion system;
a first fuel system comprising a first conduit in fluid communication with a fuel nozzle at the combustion section, wherein the first fuel system is configured to flow a liquid fuel to the combustion section for generating first combustion gases;
a second fuel system comprising a second conduit in fluid communication with the core flowpath via the outlet opening at the inter-turbine burner, wherein the second fuel system is configured to flow a gaseous fuel to the core flowpath downstream from the HP turbine for generating second combustion gases;
wherein the LP compressor, the HP compressor, the combustion section, the HP turbine, the inter-turbine burner, and the LP turbine are in serial flow arrangement; and
wherein the propulsion system comprises a rated power output ratio of the core engine and the inter-turbine burner with the LP spool between 1.5 and 5.7.