Device and methods for guiding bleed air in a turbofan gas turbine engine are disclosed. The devices provided include louvers and baffles that guide bleed air toward a bypass duct of the turbofan engine. The louvers and baffles have a geometric configuration that promotes desirable flow conditions and reduced energy loss.

A steam turbine has a diffuser that is configured to guide steam to an outside of a casing. The diffuser has an outer guide that gradually expands to an outer side in a radial direction and an inner guide that is disposed at intervals to an inner side in the radial direction with respect to the outer guide. The inner guide has an inner curved diameter-expanded portion that gradually expands to the outer side in the radial direction while being curved from the first side to the second side in the axial direction. The outer guide has a first diameter-expanded portion that gradually expands to the outer side in the radial direction with a first radius of curvature, and a second diameter-expanded portion that gradually expands to the outer side in the radial direction with a second radius of curvature larger than the first radius of curvature.

A turbine blade structure for improving aerodynamic efficiency of low-pressure turbine blades, including: a suction side, a pressure side, multiple dimples and a blade body. The suction side is an outer convex side of the blade body. The pressure side is an inner concave side of the blade body. The dimples are arranged on the suction side in pairs. Each dimple forms an inclination angle β with an air flow. The air flow includes a first fluid and a second fluid, and the energy of the first fluid is lower than that of the second fluid. Each dimple sucks the first fluid at a first end when the air flow passes a surface of the blade body, and allows the first fluid to spirally flow along an inclined direction in each dimple to form a spiral vortex, and discharge the first fluid through a second end.

An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected subarrays of the array responsive to a predetermined flight condition.

Apparatuses and systems are provided herein for unducted propulsion systems. The system includes an aft housing for low drag for high subsonic sustained flight. A plurality of blades are affixed to the aft housing, wherein the housing defines a flowpath curve extending from the axial extent of the aft blade root to the aft end of the aft housing. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes first point having a first radius where the radius reaches a maximum aft of the aft blade root and a second point forward of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.081.

An air-jet cooling device for a casing of a turbomachine, in particular a turbine casing, including a cooling air housing having a wall, and a tube having a first end mounted on the wall of the housing so as to put the tube into fluid communication with the housing, orifices being formed in a wall of the tube in order to eject the cooling air coming from the housing on the casing. The tube has a section at the first end with a gradual variation that defines a boss. The boss has a curved surface to be immersed in the cooling air so as to avoid a detachment of a boundary layer of the cooling air at an interface between the first end of the tube and the housing.

A turbine blade structure for improving aerodynamic efficiency of low-pressure turbine blades, including: a suction side, a pressure side, multiple dimples and a blade body. The suction side is an outer convex side of the blade body. The pressure side is an inner concave side of the blade body. The dimples are arranged on the suction side in pairs. Each dimple forms an inclination angle β with an air flow. The air flow includes a first fluid and a second fluid, and the energy of the first fluid is lower than that of the second fluid. Each dimple sucks the first fluid at a first end when the air flow passes a surface of the blade body, and allows the first fluid to spirally flow along an inclined direction in each dimple to form a spiral vortex, and discharge the first fluid through a second end.

A vane for a turbine engine turbine includes a blade and at least one platform that radially extends the blade, and a system for reducing vortices including at least one circuit including a duct extending from at least one air intake orifice formed in the platform upstream of the leading edge as far as at least one air exhaust slot formed on the trailing edge.

A combination of an airfoil, turbine blade, or compressor blade with a flow separation control device includes an airfoil and a flow separation control device. The airfoil includes a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge. The flow separation control device includes a plurality of openings on the upper surface of the body.

A turbine includes a rotor including a rotation shaft that rotates around an axis and a blade row formed on an outer surface of the rotation shaft; a casing, which covers the rotor, has a casing inner surface being expanded radially outward approaching a downstream side of the casing in a direction of the axis; and an inner member body formed to line the casing inner surface of the casing such that an extraction port is formed between an upstream side end of the inner member body and the casing inner surface. A discharge port is formed between a downstream side end of the inner peripheral member body and the casing inner peripheral surface. The extraction port and the discharge port are formed in an annular shape centered on the axis. A flow path cross-sectional area of the discharge port is smaller than that of the extraction port.