A gas turbine engine including: a turbomachine coupled to a propeller of the gas turbine engine, the turbomachine being in fluid communication with an external environment through an air inlet; and an electric motor coupled to the propeller, wherein the air inlet is in fluid communication with a bypass duct having a selectively variable geometry.

A gas turbine engine including: a turbomachine coupled to a propeller of the gas turbine engine, the turbomachine being in fluid communication with an external environment through an air inlet; and an electric motor coupled to the propeller, wherein the air inlet is in fluid communication with a bypass duct having a selectively variable geometry.

A rotor, a turbine, and a gas turbine including the same are provided. The rotor includes a pair of disks rotating about an imaginary central axis and arranged parallel to each other in an axial direction, a replaceable self-locking sealing assembly interposed between the pair of disks, and a fastening section disposed on the sealing assembly to fasten the sealing assembly to the disks. The disk includes a sealing slot disposed on an opposite surface to another adjacent disk and a head slot disposed outward from the sealing slot with respect to a radial direction of the to disk. The sealing assembly includes a main body with one end inserted into the sealing slot through the head slot from an outside of the disk and a sealing head disposed on another end of the main body to be seated on an inner wall of the head slot to restrict the main body from being moved.

A rotor, a turbine, and a gas turbine including the same are provided. The rotor includes a pair of disks rotating about an imaginary central axis and arranged parallel to each other in an axial direction, a replaceable self-locking sealing assembly interposed between the pair of disks, and a fastening section disposed on the sealing assembly to fasten the sealing assembly to the disks. The disk includes a sealing slot disposed on an opposite surface to another adjacent disk and a head slot disposed outward from the sealing slot with respect to a radial direction of the to disk. The sealing assembly includes a main body with one end inserted into the sealing slot through the head slot from an outside of the disk and a sealing head disposed on another end of the main body to be seated on an inner wall of the head slot to restrict the main body from being moved.

An engine system is provided that includes a compressor section, a combustor section, a turbine section, a flowpath and a flow regulator. The combustor section includes a combustion chamber. The flowpath extends sequentially through the compressor section, the combustor section and the turbine section. The flow regulator is configured to open the flowpath between the compressor section and the combustion chamber during a first mode of operation. The flow regulator is configured to at least substantially close the flowpath between the compressor section and the combustion chamber during a second mode of operation.

A system includes a bleed system configured to direct a bleed flow from a compressor section to an exhaust section of a gas turbine engine. The bleed system includes a first bleed conduit section configured to couple to the compressor section, a second bleed conduit section configured to couple to the exhaust section, and a first rotatable joint coupling together adjacent conduits of the first and second bleed conduit sections. The second bleed conduit section has components configured to rotate between a plurality of configurations relative to the first bleed conduit section and the compressor section via the first rotatable joint. The plurality of orientations corresponds to a plurality of exhaust outlet orientations of the exhaust section, and the components of the second bleed conduit section are the same in each orientation.

A system includes a bleed system configured to direct a bleed flow from a compressor section to an exhaust section of a gas turbine engine. The bleed system includes a first bleed conduit section configured to couple to the compressor section, a second bleed conduit section configured to couple to the exhaust section, and a first rotatable joint coupling together adjacent conduits of the first and second bleed conduit sections. The second bleed conduit section has components configured to rotate between a plurality of configurations relative to the first bleed conduit section and the compressor section via the first rotatable joint. The plurality of orientations corresponds to a plurality of exhaust outlet orientations of the exhaust section, and the components of the second bleed conduit section are the same in each orientation.

A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.

A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.

A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.