A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.

A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed.

A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed.

An aerospace turbofan engine that injects oxygen-enriched gas from an inlet includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a first afterburner outer ring. An aerospace turbofan engine that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a second afterburner outer ring. The aerospace turbofan engines which fully utilize oxygen in the atmosphere for combustion and work in various flight altitude ranges adopt regenerative cooling-type afterburners with acoustic cavity and baffle plates, so that an aircraft can fly to an altitude of 20-50 km and reach a speed of Mach 2-5. Variants of the aerospace turbofan engines are disclosed.

An aerospace turbofan engine that injects oxygen-enriched gas from an inlet includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a first afterburner outer ring. An aerospace turbofan engine that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a second afterburner outer ring. The aerospace turbofan engines which fully utilize oxygen in the atmosphere for combustion and work in various flight altitude ranges adopt regenerative cooling-type afterburners with acoustic cavity and baffle plates, so that an aircraft can fly to an altitude of 20-50 km and reach a speed of Mach 2-5. Variants of the aerospace turbofan engines are disclosed.

A gas turbine engine includes an inner annular combustor radially inboard of an outer annular combustor. An outer variable turbine vane array is downstream of the outer annular combustor and an inner variable turbine vane array downstream of the inner annular combustor.

An assembly is provided for a turbofan engine. This turbofan engine assembly includes a cowling, a door and an actuation mechanism configured to actuate movement of the door in response to receiving a control signal. The cowling is configured to form a compartment at least partially around a case of the turbofan engine. The cowling includes an exhaust port that is fluidly coupled with the compartment. The door is configured to at least partially open and close the exhaust port. This variable exhaust port may be opened in case increased airflow is needed through the compartment, such as when increased cooling airflow is needed through an environmental air precooler that cools compressed air for the aircraft cabin and the precooler exhausts its cooling air into the compartment.

An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.

A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.

A diffusion cone for the rear part of a jet engine has a base and, on an opposite side, a truncated tip defining an annular trailing edge, and comprises a flame-holder ring with a cross section comprising an external branch and an internal branch which are connected to one another on the base side and such that the external branch extends around the internal branch, whereby the external and internal branches delimit between them an internal space opening on the opposite side to the base. One of the branches is made up of the annular trailing edge. The flame-holder ring comprises at least one fuel inlet designed to let fuel into the internal space. Such a flame-holder ring makes it possible to ensure and to control the propagation of the flame within the afterburner channel.