Abstract: The present invention relates to a wind turbine blade (10) comprising an aerodynamic shell (83) having an outer surface (84) forming at least part of an exterior surface of the wind turbine blade and an inner surface (85). An access window (80) extends through the shell (83). A panel (87) is arranged within a recessed portion (86) at the inner surface of the shell adjacent to the access window (80) for closing the access window (80).

Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.

Abstract: The proposed solution relates, in particular, to an engine component having at least one first loading zone, which is designed for dynamic loads arising at the engine component when the engine component is correctly built into an engine and when the engine is operating, and a second loading zone, which is provided spaced at a distance from the first loading zone on the engine component and likewise is designed for dynamic loads arising at the engine component when the engine component is correctly built into an engine and when the engine is operating. The proposal is, in particular, that at least one spatially delimited modification zone with introduced internal tensile stress is formed on the engine component, via which zone a crack propagating in the engine component is guided to the and/or within the second loading zone.

Abstract: Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.

Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

Abstract: A fan blade comprises interleaved plies, where interleaving comprises distributing wide plies within narrow plies and short plies within long plies in the fan blade; wherein the interleaving is defined as an actual intersection of a plurality of plies of different variable dimensions that extend in the chordwise direction with another plurality of plies of different variable dimensions that extend in the spanwise direction such that their respective longitudinal axes intersect with one another at angles of 5 to 175 degrees.

Abstract: The present invention relates to a turbomachine rotary-fan blade (2), comprising a body (20) made of a composite material, a metal reinforcement part (3) comprising a metal upstream nose (31), characterised in that the metal upstream nose (31) comprises, at least on the metal part (27b) of the blade tip, a recess (4) of longitudinally tapering thickness (AX), delimiting on the metal part (27b) over a height (H) at least one metal projection (5) with prescribed wear, which has a longitudinally tapering thickness and which is configured to detach at least partially in the presence of tangential friction in the second thickness direction (EP) against the metal part (27b), the recess (4) and the metal projection (5) with prescribed wear extending the first metal fin (32) and/or the second metal fin (33) and/or the upstream edge (22) of the body (20) made of composite material.

Abstract: Undershot turbines with dynamic blades are disclosed for improving energy capture from a flowing stream. The blades are provided on respective rotatable swing arm assemblies attached to the circumference of a turbine support. In operation, the blades are uniquely adjusted as a function of rotation of the support wheel for improved efficiency and energy capture.

Abstract: A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.

Abstract: In a clearance control system for a gas turbine, a control device operates an adjustment device such that a first flow rate is greater than a second flow rate when a load stable state is entered in which a fluctuation range of a load shifts within a preset range, and operates the adjustment device such that the second flow rate is greater than the first flow rate when a load fluctuation state is entered in which the load falls outside the range.

Abstract: An exemplary pitch link centering tool includes a rod having a longitudinal axis, a front face, a rear face, a first rod end and a second rod end, the first rod end having a first aperture with a first rotational axis, the second rod end having a second aperture with a second rotational axis, a first connector coupled to the first rod end, the first connector having a first slot extending in a first radial direction relative to the longitudinal axis and a second connector coupled to the second rod end, the second connector having a second slot extending in a second radial direction relative to the longitudinal axis different from the first radial direction.

Abstract: A head mounted fan includes: a main blowing tube configured to be mounted on an upper portion of a head of a user, the main blowing tube having an air inlet through which air is introduced and including a main flow path through which air flows therein; a sub blowing tube connected to the main blowing tube, wherein the sub blowing tube includes a plurality of sub flow paths branching from the main flow path to extend in one direction of the head when the head mounted fan is worn on the head, and wherein air is discharged toward a scalp of the head through a plurality of air outlets communicating with the sub flow paths; and a wind generating unit configured to provide air pressure for causing the air to flow in the main flow path.

Abstract: An airfoil includes an airfoil wall that has a span between first and second radial ends and that defines leading and trailing edges, pressure and suction sides each joining the leading and trailing edges, and an internal cavity. The internal cavity is divided into at least first and second sub-cavities extending over the span. The first sub-cavity defines a venturi tube.

Abstract: An airfoil assembly includes first and second fiber-reinforced composite airfoil rings. Each ring is comprised of inner and outer platform sections, a suction side wall that extends between the inner and outer platforms, and a pressure side wall that extends between the inner and outer platforms. the first ring mates at an interface with the second ring such that the suction side wall of the first ring and the pressure side wall of the second ring together form an airfoil that circumscribes an internal cavity. The interface along the airfoil includes a gap that is configured to emit cooling air from the internal cavity.

Abstract: An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.

Abstract: An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.

Abstract: An impeller apparatus includes a housing, an impeller, and a heat generation member. The housing includes an air duct formed in the housing. The air duct includes a first air duct and a second air duct successively connected to each other. The second air duct has a non-blocking area. The impeller is arranged in the first air duct. The heat generation member is rotatably arranged in the second air duct and has a blocking state and a non-blocking state. In the blocking state, the heat generation member blocks the second air duct, in the non-blocking state, the heat generation member is accommodated in the non-blocking area and does not block the second air duct.

Abstract: A blower housing comprises first and second blower housing pieces for surrounding a blower fan. The first blower housing piece comprises a blower discharge section comprising an inner tubular portion, an outer tubular portion, and a drain hole. The inner tubular portion defines a blower discharge passage. The inner and outer tubular portions define an exhaust pipe cavity adapted to receive an end margin of an exhaust pipe. The tubular portions are adapted to enable condensate water that forms on the inner surface of the exhaust pipe to flow into the exhaust pipe cavity. The drain hole extends through the outer tubular portion. The drain hole is configured to enable condensate water flowing into the exhaust pipe cavity to drain from the blower housing. The first blower housing piece is a molded one-piece member.

Abstract: A blower assembly for an HVAC system includes a blower wheel, which includes a plurality of blades. A laminated insert is concentric with the blower wheel and radially inward of the plurality of blades. A shaft is coupled to the blower wheel through the laminated insert.

Abstract: A wind turbine nacelle configured for mounting on a wind turbine tower and for supporting a rotor-supporting assembly, the nacelle comprising a main unit, and at least one auxiliary unit. The auxiliary unit accommodates at least one operative component, e.g. a converter, a transformer, an electrolysis cell, or a battery. An operative component having a similar function is accommodated in another auxiliary unit which thereby facilitate shared operation, and easy and fast maintenance or replacement of the operative component.