A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.

A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.

A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.

A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.

A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

A gas turbine engine comprises at least a power output turbine unit (POT), which is rotatably arranged inside an outer housing unit, and a compressor-turbine unit (CTU), which is rotatably arranged inside the POT, and the CTU, POT and outer housing unit are arranged about a common axis of rotation (CL). The POT and the CTU are arranged in such close proximity (d) that a dynamic friction coupling is generated between the POT and the CTU.

A gas turbine engine comprises at least a power output turbine unit (POT), which is rotatably arranged inside an outer housing unit, and a compressor-turbine unit (CTU), which is rotatably arranged inside the POT, and the CTU, POT and outer housing unit are arranged about a common axis of rotation (CL). The POT and the CTU are arranged in such close proximity (d) that a dynamic friction coupling is generated between the POT and the CTU.

A turbine blade ring segment includes an inner panel mounted to an inner surface of a turbine casing, the inner panel including a plurality of flow holes for supplying cooling air from an outside of the turbine casing; and an outer panel disposed on one surface of the inner panel, the outer panel including a plurality of air passages communicating with the flow holes formed in the inner panel. The passages include a first flow passage formed in a central portion of the outer panel to guide the supplied cooling air in a flow direction of the combustion gas, a second flow passage formed in the outer panel separately from the first flow passage to guide the supplied cooling air in the flow direction of the combustion gas, and a third flow passage communicating with the second flow passage to feed the supplied cooling air to the second flow passage.