Propulsion system using ramjet bleed air for gas turbine combustion

A propulsion system comprising:

• a turbine engine including a turbine engine inlet, a compressor section, a turbine engine combustor, and a turbine section;
• a ramjet engine including a ramjet inlet portion and a ramjet combustor, the ramjet inlet portion having at least one ramjet bleed air passage in airflow communication with the turbine engine combustor, the at least one ramjet bleed air passage being arranged axially downstream of a last compressor stage of the turbine engine and upstream of the turbine engine combustor, wherein the at least one ramjet bleed air passage directs a ramjet inlet bleed airflow from the ramjet inlet portion upstream of the compressor section to the turbine engine combustor downstream of the last compressor stage;
• a turbine engine inlet section restriction device arranged to permit an inlet airflow to the turbine engine inlet in a first operating state of the propulsion system, and to restrict the inlet airflow to the turbine engine inlet in a second operating state of the propulsion system;
• a combustor inlet flow control device in airflow communication with the at least one ramjet bleed air passage and the turbine engine combustor, the combustor inlet flow control device being axially aligned with the at least one ramjet bleed air passage such that the combustor inlet flow control device is arranged axially downstream of the last compressor stage of the turbine engine and upstream of the turbine engine combustor, the combustor inlet flow control device comprising a movable flow control device that is movable between an open position that allows the ramjet inlet bleed airflow to flow from the at least one ramjet bleed air passage to the turbine engine combustor and a closed position that restricts the ramjet inlet bleed airflow from flowing from the at least one ramjet bleed air passage to the turbine engine combustor,
• wherein, in the first operating state, the combustor inlet flow control device positions the movable flow control device in the closed position to restrict the ramjet inlet bleed airflow from flowing from the at least one ramjet bleed air passage to the turbine engine combustor through the combustor inlet flow control device while allowing a flow of compressed air from the compressor section to the turbine engine combustor, and, in the second operating state, positions the movable flow control device in the open position to provide the ramjet inlet bleed airflow from the at least one ramjet bleed air passage to the turbine engine combustor through the combustor inlet flow control device;
• and
• at least one accessory gearbox drivingly connected with the compressor section and including at least one accessory component that is driven by the at least one accessory gearbox.