Abstract: An airfoil includes an airfoil section and a platform from which the airfoil section extends. The platform defines a shelf that extends from the airfoil section to a platform edge. The shelf includes a plenum and a plurality of cooling orifices extend from the plenum toward the platform edge. Each of the cooling orifices has a first orifice end that opens to the plenum and a second, closed orifice end adjacent the platform edge.

Abstract: A gas turbine engine for an aircraft, includes: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan assembly located upstream of the engine core; and a gearbox receiving an input from the core shaft and outputs drive to the fan assembly so as to drive the fan assembly at a lower rotational speed than the core shaft, wherein the fan assembly has fan blades mounted around a hub, the fan blades having blade tips defining an outer diameter of the fan assembly of from around 220 cm to around 400 cm, the hub having slots located around a rim of the hub, each slot receiving a root of a corresponding fan blade, wherein a ratio of a mass of the hub to a total mass of the fan blades is within the range of around 0.45 to around 0.7.

Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

Abstract: A seal land includes a seal land body that extends circumferentially about an axis and radially between an inner seal land side and an outer seal land side. The seal land body is configured with a plurality of fluid passages arranged about the axis. A first of the fluid passages includes an inner passage segment and an outer passage segment fluidly coupled with the inner passage segment. The inner passage segment extends along a first trajectory within the seal land body towards the outer passage segment. The outer passage segment extends along a second trajectory within the seal land body away from the inner passage segment and towards the outer seal land side. The second trajectory is different than the first trajectory and includes a radial component and a circumferential component.

Abstract: A passive heat exchanger includes an evaporator section including a heat exchange surface formed complementary to a surface of a gas turbine engine component to be cooled. The heat exchange surface is configured to be thermally coupled in conductive contact to the component surface. The heat exchanger further includes a condenser section coupled in passive convective flow communication with the evaporator section, and a working fluid contained within the evaporator section and the condenser section and configured to passively convect heat from the evaporator section to the condenser section.

Abstract: A turbine blade includes an airfoil body having an outer tip and a platform; and a part-span shroud positioned between the outer tip and the platform of the airfoil body. The part-span shroud has a first opening extending through the airfoil body and having a first inner surface. The airfoil body includes a second opening extending radially from the first opening and having a second inner surface. A first elongated vibration-damping element is disposed in the first opening, and a second elongated vibration-damping element disposed radially in the second opening. The second elongated vibration-damping element includes a free radially outer end and a radially inner end coupled to the first elongated vibration-damping element. The first elongated vibration-damping element frictionally damps vibration, and the second elongated vibration-damping element damps vibration using impact within the second opening.

Abstract: A compressor blade of a gas turbine includes a root member; an airfoil that is disposed on the root member and includes a first interior wall and a second interior wall forming a hollow space defined between the first and second interior walls; and an organic vibration stiffener (OVS) formed on at least one of the first interior wall and the second interior wall. The OVS is formed by 3D printing performed with respect to a surface of the at least one of the first interior wall and the second interior wall and includes an uneven surface formed on at least part of the at least one of the first interior wall and the second interior wall. The OVS may include a protruded or recessed portion protruding from or recessed into at least part of the at least one of the first interior wall and the second interior wall.

Abstract: A support unit for a power unit reliably absorbs thermal deformation of the power unit due to thermal deformation of a casing and enables the center of the casing to be effectively maintained at a correct position. The support unit includes a supporting unit and a stress supporting unit. The supporting unit includes a first support configured to support a front part of the casing of the power unit, and a second support configured to support a rear part of the casing and provided with an auxiliary support configured to receive and support a weight of the casing. The stress supporting unit is disposed under the rear part of the casing and receives heat from the casing and primarily absorb stress resulting from thermal expansion of the casing. Stress in the casing resulting from the thermal expansion is secondarily damped by the second support via the stress supporting unit.

Abstract: A turbofan engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path. A plurality of vanes are circumferentially spaced around the inlet, each of the vanes extending radially inwardly from the inlet wall, a maximum radial distance between a tip of each of the vanes and the inlet wall defining a maximum height of the vane. The maximum height of the vane is at most 50% of the downstream height of the flow path. In another embodiment, the maximum height of the vane is at most 50% of the maximum fan blade span. A method of reducing a relative Mach number at fan blade tips is also discussed.

Abstract: Disclosed is a system and method for both consumer and utility scale energy extraction from flow-based energy sources. The passive system may utilize directing perforations on a surface in order to create and air jet vortex generators. Alternatively the system may provide for flow through discrete orifices aligned with the span of an aerodynamic assembly in a co-flow direction, utilizing a Coanda effect. Further additional configurations include directing flow through a perforated surface skin that is near the trailing edge on the suction side. Even further are embodiments for blowing air directly out of the trailing edge of an airfoil. The disclosed systems and methods support a wide variety of scenarios for fluid flow energy extraction, such as wind or water flow, as well as for related products and services.

Abstract: A nacelle for a wind power installation, a rotor for a wind power installation, a wind power installation, use of a planetary-gearbox-free electric actuator drive, a method for wind direction tracking of a nacelle, and a method for rotor blade adjustment of rotor blades of a rotor are provided. Provided is a nacelle for a wind power installation, in particular a wind power installation having a nominal output of more than 3000 kilowatts (kW), having at least one azimuth drive which is used for the wind direction tracking of the nacelle and which is configured as a planetary-gearbox-free electric actuator drive.

Abstract: A blade outer air seal includes a base portion. A first wall and a second wall extend from the base portion. The first wall is circumferentially spaced from the second wall. The first and second walls extend at an angle less than 90° from the base portion. The first and second walls extend towards one another.

Abstract: A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.

Abstract: A turbine blade for a gas turbine engine having an airfoil to platform fillet, wherein the fillet is contoured in accordance with the coordinates of Table 1.

Abstract: This invention, the “Internal Combustion Boundary Layer Turbine Engine” (BLTE), embodies the description of a “flat-disk radial flow turbine engine”. The BLTE uses the effects of “working fluid” or “exhaust” drag to convert the pressure of fuel combustibles to kinetic output energy in the form of a driven shaft. The BLTE application of “differentially sized flat blades” solves the problem of internal combustion and multi-stage operation for this new category of engine. This engine offers the light weight and high power output capability of a continuous or pulsed burn-mode of a radial turbine engine. Relative to conventional radial flow turbine engines, this engine provides reduced exhaust flow, reduced emissions and offers simple, inexpensive construction with commonly available machine tools.

Abstract: There is presented a method for damping an edgewise vibration of a rotor blade of a wind turbine, wherein the method comprises measuring at the rotor blade a motion parameter of the edgewise rotor blade vibration, generating based on said motion parameter a blade pitch angle control signal, and damping the edgewise vibration of the rotor blade by pitching the rotor blade according to the blade pitch angle control signal, wherein the blade pitch angle control signal is arranged so that a resulting force on a rotor blade pitched according to the blade pitch angle control signal, in a direction of the edgewise vibration of the rotor blade in a coordinate system, which rotates with a rotor of the wind turbine, is opposite and proportional to the edgewise rotor blade vibration velocity.

Abstract: Turbine blades for use in gas turbine engines are disclosed herein. Each blade includes an airfoil and a protective crown. The airfoil includes ceramic matrix composite materials. The protective crown includes ceramic-containing materials and is mounted to a radially-outer end portion of the airfoil.

Abstract: A scroll casing forms a scroll flow passage of a centrifugal compressor, and provided that, in a cross section of the scroll flow passage, Ei is an inner end of the scroll flow passage in a radial direction of the centrifugal compressor, and Mh is a middle point of a maximum flow-passage height Hmax of the scroll flow passage in the axial direction of the centrifugal compressor, the scroll flow passage has a separation suppressing cross section in which the inner end Ei is disposed on an inner side, in the radial direction, of a diffuser outlet, and the inner end Ei is disposed on a back side, in the axial direction, of the middle point Mh, in a section disposed at least partially in an upstream region of a connection position of a scroll start and a scroll end.

Abstract: An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower surface cavity (C2) being adjacent to the lower surface wall (22), each of the first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) including a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.

Abstract: This method is for orientating the blades (40) of a turbine (4) past a non-reachable range of positions (?1, ?2) in a power plant (2), said blades (40) being rotatable around orientation axes (X40) distinct from a rotation axis (X) of the turbine (4), the turbine (4) comprising means (42, 44, 46) for orientating the blades (40), said means being adapted to exert an adjustable torque on the blades (40).