Propulsion system using ramjet bleed air for gas turbine combustion

Abstract

A propulsion system includes a turbine engine and a ramjet engine. A turbine engine inlet section restriction device permits an inlet airflow to a turbine engine inlet in a first (low speed) operating state of the propulsion system, and restricts the inlet airflow to the turbine engine inlet in a second (high speed) operating state of the propulsion system. A combustor inlet flow control device, in the first operating state, provides an airflow from a compressor to the turbine engine combustor, and restricts an airflow from a ramjet bleed air passage, and, in the second operating state, provides a ramjet inlet bleed airflow to the turbine engine combustor, while restricting airflow from the compressor. In the second operating state, the turbine engine drives at least one accessory gearbox to drive at least one accessory component.