Abstract: An internally-cooled turbomachine component, having: a main body with a first end wall, a second end wall spaced apart from the first end wall, and a sidewall which extends between the first end wall and the second end wall such that the first end wall, the second end wall and the sidewall define a cooling passage extending between a fluid inlet and a fluid outlet, a pedestal bank with a plurality of pedestals which span the cooling passage between the first end wall and the second end wall, wherein the pedestal bank is spaced from the sidewall to define a flow channel therebetween; and a flow guide for directing cooling flow away from the flow channel, the flow guide extending from the flow channel into the pedestal bank.

Abstract: A turbomachine component has an aerofoil that includes a suction side wall and a pressure side wall bordering an aerofoil cavity. The turbomachine component has at least one cooling channel, for flow of a cooling fluid, extending inside the aerofoil cavity. The cooling channel has an inlet for receiving the cooling fluid and a series of turbulators positioned inside the cooling channel. The turbomachine component includes at least one vortex generating element positioned at the inlet of the cooling channel upstream of the turbulators or positioned adjacent to and upstream of the inlet of the cooling channel. The cooling fluid flows about and contiguous with the vortex generating element before the cooling fluid reaches the turbulators. The vortex generating element generates a swirl in the cooling fluid before the cooling fluid reaches the turbulators.

Abstract: An internally-cooled turbomachine component, having: a main body with a first end wall, a second end wall spaced apart from the first end wall, and a sidewall which extends between the first end wall and the second end wall such that the first end wall, the second end wall and the sidewall define a cooling passage extending between a fluid inlet and a fluid outlet, a pedestal bank with a plurality of pedestals which span the cooling passage between the first end wall and the second end wall, wherein the pedestal bank is spaced from the sidewall to define a flow channel therebetween; and a flow guide for directing cooling flow away from the flow channel, the flow guide extending from the flow channel into the pedestal bank.

Abstract: A turbomachine component having film cooling arrangement includes a cooling passage, an external wall having an outer surface to be positioned in a hot gas path and an inner surface forming a part of the cooling passage, film cooling holes formed through the external wall, and a flow guide arrangement having a flow guide corresponding to one of the film cooling holes. Each film cooling hole has an inlet at the inner surface and an outlet at the outer surface. The inlet receives a cooling fluid from the cooling passage and the outlet releases it over the outer surface. The flow guide positioned at the inlet of the corresponding film cooling hole on the inner surface redirects within the cooling passage a flow of the cooling fluid such that the flow makes a U-turn before entering the inlet of the corresponding film cooling hole in a reversed flow.

Abstract: The present invention relates to a turbine assembly having an aerofoil and/or an end wall each having an outer surface with a structure for directing a flow of a cooling medium at the outer surface. The structure at the outer surface has at least a first groove and a second groove extending in the outer surface from a leading to a trailing edge and being oriented in at least two different directions with a deflection angle (?) towards each other, with the deflection angle (?) having a component in a span wise direction of the aerofoil. The structure at the outer surface of the end wall has at least a first groove and a second groove extending in an axial direction of the turbine assembly, matching an outer profile of the aerofoil and oriented in at least two different directions with a deflection angle (?) towards each other.

Abstract: The present invention relates to a turbine assembly having an aerofoil and/or an end wall each having an outer surface with a structure for directing a flow of a cooling medium at the outer surface. The structure at the outer surface has at least a first groove and a second groove extending in the outer surface from a leading to a trailing edge and being oriented in at least two different directions with a deflection angle (?) towards each other, with the deflection angle (?) having a component in a span wise direction of the aerofoil. The structure at the outer surface of the end wall has at least a first groove and a second groove extending in an axial direction of the turbine assembly, matching an outer profile of the aerofoil and oriented in at least two different directions with a deflection angle (?) towards each other.

Abstract: A flow channel with a branch channel perpendicular to a main channel including an edge defining an inlet opening of the branch channel is provided. A chamfer is disposed at the upstream edge of the inlet opening and a straight edge is disposed at the downstream edge of the inlet opening, perpendicular to the main channel.

Abstract: A turbine arrangement with a rotor and a stator surrounding the rotor forming a flow path for hot and pressurized combustion gases between the rotor and the stator is provided. The rotor defines a radial direction and a circumferential direction and includes turbine blades extending in the radial direction through the flow path towards the stator. The turbine blades have shrouds located at their tips and the stator includes a wall section along which the shrouds move when the rotor is turning. A supersonic nozzle is located in the wall section and is connected to a cooling fluid provider. The supersonic nozzle provides a supersonic cooling fluid flow towards the shroud. The supersonic nozzle is angled with respect to the radial direction towards the circumferential direction in such an orientation that the supersonic cooling fluid flow has a flow component parallel to the moving direction of the shroud.

Abstract: A damping device for damping pressure oscillations within a combustion chamber of a turbine is provided. The damping device has a radially extending damping device body. The damping device body has a radially inner circumferential edge portion and a radially outer circumferential edge portion. A through hole is formed in the damping device body and has a tapered shape.

Abstract: A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.

Abstract: A turbomachine is provided. The turbomachine includes a rotor, a stator and a plurality of blade discs mounted on the rotor. The rotor includes a turbulator cylinder where a plurality of turbulators are provided on a curved surface of the turbulator cylinder and the stator includes an annular shroud extending around the turbulator cylinder. The plurality of turbulators increase a heat transfer to a coolant flowing between the adjacent opposed surfaces of the turbulator cylinder and the annular shroud.

Abstract: A flow machine is described having a first space adapted to contain a hot fluid and delimited by a wall. The wall having a first wall surface facing the first space and a second wall surface turned away from the first space. Cooling is provided for a region of the wall by supplying a relatively cool fluid onto the second wall surface. The cooling means includes a supply chamber containing the second fluid, a cavity adjacent the second wall surface, at least one duct, which has an inlet opening at the supply chamber and an outlet opening at the cavity for conveying the cool fluid to the cavity, and a deflection surface facing the cavity.

Abstract: A turbine arrangement with a rotor and a stator surrounding the rotor forming a flow path for hot and pressurised combustion gases between the rotor and the stator is provided. The rotor defines a radial direction and a circumferential direction and includes turbine blades extending in the radial direction through the flow path towards the stator. The turbine blades have shrouds located at their tips and the stator includes a wall section along which the shrouds move when the rotor is turning. A supersonic nozzle is located in the wall section and is connected to a cooling fluid provider. The supersonic nozzle provides a supersonic cooling fluid flow towards the shroud. The supersonic nozzle is angled with respect to the radial direction towards the circumferential direction in such an orientation that the supersonic cooling fluid flow has a flow component parallel to the moving direction of the shroud.

Abstract: A flow channel with a branch channel perpendicular to a main channel including an edge defining an inlet opening of the branch channel is provided. A chamfer is disposed at the upstream edge of the inlet opening and a straight edge is disposed at the downstream edge of the inlet opening, perpendicular to the main channel.

Abstract: A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.

Abstract: A flow machine is described having a first space adapted to contain a hot fluid and delimited by a wall. The wall having a first wall surface facing the first space and a second wall surface turned away from the first space. Cooling is provided for a region of the wall by supplying a relatively cool fluid onto the second wall surface. The cooling means includes a supply chamber containing the second fluid, a cavity adjacent the second wall surface, at least one duct, which has an inlet opening at the supply chamber and an outlet opening at the cavity for conveying the cool fluid to the cavity, and a deflection surface facing the cavity.