Turbine based combined cycle engine

摘要

An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression combustor engine such as a ramjet and/or scramjet. An airflow valve is provided to direct air to a downstream portion of the aircraft engine and can be positioned as a function of the aircraft operating modes. The valve can be used to cocoon the gas turbine engine.

主权项

1. An apparatus comprising:
a propulsion engine having an inlet operable to convey a working fluid for combustion and a bypass valve operable to selectively bypass a quantity of the working fluid, the propulsion engine having three thrust producing modes including:
a first thrust producing mode including a gas turbine engine having a rotating compressor, a core combustor, and a rotating turbine, wherein the bypass valve is operated to provide air flow to the gas turbine engine by positioning a leading edge of the bypass valve upstream of a forward end of an engine centerbody, wherein the forward end is forward of the compressor;a second thrust producing mode including an auto-ignition combustor operable to support an auto-ignition process, wherein the bypass valve provides an airflow to the auto-ignition combustor;a third thrust producing mode including a combustion chamber and excluding a rotating compressor of the propulsion engine, wherein at least a portion of a compression of an air flow into the combustion chamber is provided by a speed of an inlet airflow of the propulsion engine; and wherein the bypass valve is operable to be positioned to cocoon the gas turbine engine.