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

Claim 12:
13. A computing system for an aircraft propulsion system, the computing system comprising one or more processors and one or more memory, wherein the memory is configured to store instructions that, when executed by the processor, cause the propulsion system to perform operations, the operations comprising:
flowing liquid fuel to a combustion section of the propulsion system;
generating first combustion gases at the combustion section corresponding to 85% or less of a rated power output of the propulsion system; and
modulating rotational speed of a low pressure (LP) spool including a LP turbine via modulating a flow of gaseous fuel to an inter-turbine burner defined by a frame strut disposed upstream from the LP turbine and downstream from a high pressure (HP) turbine to generate second combustion gases, wherein the flow of gaseous fuel flows from an outlet opening of the inter-turbine burner, wherein the outlet opening is defined along a trailing edge of the strut, and wherein the outlet opening is disposed upstream of the LP spool.