Abstract: A wind turbine blade bushing system for arrangement in a root end of a wind turbine blade is described. The wind turbine blade bushing system comprises a threaded element for retaining a mounting bolt for a wind turbine blade, the threaded element being formed from a first material; and an anchor element for arrangement at the root end of the wind turbine, wherein the anchor element acts to at least partly retain the threaded element in the wind turbine blade, the anchor element being formed from a second material. The first material has a higher strength and higher fracture toughness than the second material.

Abstract: A method of producing a single assembled longitudinally extending fibre layer for use in a later resin infusion process for manufacturing a fibre-reinforced composite structure is described including steps: a) providing a first fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the first fibre mat, b) providing a second fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the second fibre mat, c) arranging the first fibre mat and the second fibre mat so that unidirectional fibres of one end of the first fibre mat adjoin one end of the second fibre mat in a single plane at a common boundary, and d) splicing unidirectional fibres of the first fibre mat at one end of the first fibre mat to unidirectional fibres of the second fibre mat at one end of the second fibre mat in order to form a splicing joint.

Abstract: A wind turbine blade is described wherein at least one stall fence is provided on the blade surface, where the stall fence is arranged such that it extends at an angle to the chord of the blade. The stall fence acts to re-direct airflow over the blade, to improve wind turbine performance. The stall fence may be a provided towards the blade root end, acting to divert airflow towards the root end of the blade to prevent separation of attached airflow. Additionally or alternatively, the stall fence may be arranged as a flow diverter provided towards the blade tip end, to increase airflow in the tip region for increased performance and/or to disrupt the formation of tip vortices.

Abstract: A method of producing a single assembled longitudinally extending fibre layer for use in a later resin infusion process for manufacturing a fibre-reinforced composite structure is described including steps: a) providing a first fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the first fibre mat, b) providing a second fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the second fibre mat, c) arranging the first fibre mat and the second fibre mat so that unidirectional fibres of one end of the first fibre mat adjoin one end of the second fibre mat in a single plane at a common boundary, and d) splicing unidirectional fibres of the first fibre mat at one end of the first fibre mat to unidirectional fibres of the second fibre mat at one end of the second fibre mat in order to form a splicing joint.

Abstract: A wind turbine blade bushing system for arrangement in a root end of a wind turbine blade is described. The wind turbine blade bushing system comprises a threaded element for retaining a mounting bolt for a wind turbine blade, the threaded element being formed from a first material; and an anchor element for arrangement at the root end of the wind turbine, wherein the anchor element acts to at least partly retain the threaded element in the wind turbine blade, the anchor element being formed from a second material. The first material has a higher strength and higher fracture toughness than the second material.

Abstract: A wind turbine blade is described wherein at least one stall fence is provided on the blade surface, where the stall fence is arranged such that it extends at an angle to the chord of the blade. The stall fence acts to re-direct airflow over the blade, to improve wind turbine performance. The stall fence may be a provided towards the blade root end, acting to divert airflow towards the root end of the blade to prevent separation of attached airflow. Additionally or alternatively, the stall fence may be arranged as a flow diverter provided towards the blade tip end, to increase airflow in the tip region for increased performance and/or to disrupt the formation of tip vortices.

Abstract: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.

Abstract: An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface to the exterior surface; and a concave trench extending from the cooling hole at the exterior surface of the body in a downstream direction.

Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body. At least one of the cooling holes has cross-sectional shape with a first concave portion and a first convex portion.

Abstract: A turbine engine component includes a wall, a main opening, and two clusters of two or more auxiliary openings. The wall includes cool and hot air sides. The main opening extends between the cool air side and the hot air side and has an inlet and an outlet. The inlet is formed on the cool air side, and the outlet is formed on the hot air side. The first cluster of two or more auxiliary openings extends from the main opening to the hot air side. The second cluster of two or more auxiliary openings extends from the main opening to the hot air side. The main opening may be cylindrical or conical with a converging passage extending from the cool air side to the hot air side. The converging main opening may enhance flow through the auxiliary openings especially at high blowing ratios.

Abstract: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.

Abstract: An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface to the exterior surface; and a concave trench extending from the cooling hole at the exterior surface of the body in a downstream direction.

Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body. At least one of the cooling holes has cross-sectional shape with a first concave portion and a first convex portion.

Abstract: A turbine engine component includes a wall, a main opening, and two clusters of two or more auxiliary openings. The wall includes cool and hot air sides. The main opening extends between the cool air side and the hot air side and has an inlet and an outlet. The inlet is formed on the cool air side, and the outlet is formed on the hot air side. The first cluster of two or more auxiliary openings extends from the main opening to the hot air side. The second cluster of two or more auxiliary openings extends from the main opening to the hot air side. The main opening may be cylindrical or conical with a converging passage extending from the cool air side to the hot air side. The converging main opening may enhance flow through the auxiliary openings especially at high blowing ratios.

Abstract: Turbine engine components are provided for use with a plurality of blades, where each blade has an attachment portion defined by a wall and a surface. The components include a disk having a first side, a second side, and an outer radial section with a rim and an overhang. Disk slots extend radially inwardly from the disk rim, and each is configured to receive the attachment portion of a corresponding blade such that when the blade is disposed therein, the wall of the blade attachment portion is substantially flush with an adjacent portion of the first side of the disk and each disk slot defines a cooling air passage with the surface of the blade attachment portion, where the cooling air passage extends axially from the disk first side to the disk second side. A cooling air slot is formed in the disk first side and extends radially outward from the overhang of the disk to the cooling air passage.

Abstract: Labyrinth seals and methods of manufacturing the seals are provided. In an embodiment, the seal includes a seal base and a first annular tooth. The seal base has an outer peripheral surface. The first annular tooth extends radially from the seal base outer peripheral surface. The first annular tooth includes a forward wall, an aft wall, and a tip wall, and the forward wall and the aft wall each include bottom sections that contact the seal base and angle upwardly toward or substantially parallel to each other. The forward wall has a notch formed therein defined by a shelf wall and a side wall, the shelf wall and side wall join the forward wall to the tip wall, and the aft wall is formed without a notch. The side wall and the aft wall extend substantially parallel to each other.

Abstract: Labyrinth seals and methods of manufacturing the seals are provided. In one embodiment, and by way of example only, the labyrinth seal includes a land including a plurality of cells, each cell including a first half of a geometric shape and a second half the geometric shape, the first half laterally offset relative to the second half.