Abstract: A wind turbine (100) comprising a turbine generator (101), rotating mast (102) and a bedplate (103) which is the foundation of the turbine, and three vertical airfoils (104, 105) positioned parallel forming a diffuser, where two of them are side airfoils (104) and the third one, which is positioned in an equal distance between the side airfoils (104), is the central airfoil (105), wherein three vertical airfoils (104, 105) have cross-section diminishing upwardly and the central airfoil (105) comprises in its leeward area a mounted turbine generator (101) having at least one rotor connected to at least one electric generator, wherein said turbine generator (101) is located inside the central airfoil (105), the central airfoil (105) in its cross-section has a shape of biconvex airfoil section preferably drop-shaped.

Abstract: A fan blade support assembly for an aircraft is generally disclosed. The fan blade support assembly includes a fan assembly having a plurality of fan blades, a power shaft extending between the fan assembly and an engine of the aircraft, and a housing assembly positioned around the power shaft. The housing assembly includes a convergent housing and a sealing shroud. The convergent housing includes a cap, a base, and a middle portion extending therebetween. The base defines a first diameter, and the cap defines a second diameter less than the first diameter. The sealing shroud is positioned between the convergent housing and the power shaft. A gap is defined between the sealing shroud and the power shaft.

Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.

Abstract: Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.

Abstract: Methods and Systems for health-monitoring of a multi-channel pressure transducer of a gas turbine engine are described. The method comprises monitoring a deviation between a first channel and a second channel of a multi-channel pressure transducer over time, determining a rate of change of the deviation, extrapolating a trend over time based on the rate of change of the deviation to predict when the deviation will reach a threshold, and triggering a maintenance action for the pressure transducer based on the trend.

Abstract: An exhaust chamber of a steam turbine includes a casing, an inner flow guide portion disposed in the casing so as to define an outer boundary of a diffuser passage communicating with an outlet of a last stage blade in the steam turbine, and an outer flow guide portion disposed on an outer peripheral side of the inner flow guide portion in the casing. The exhaust chamber has an exhaust chamber outlet on a lower side thereof. The outer flow guide portion is disposed at least around an upper half region of the inner flow guide portion.

Abstract: A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.

Abstract: Method of controlling a wind turbine. A data set is obtained that includes a direction of the wind relative to the wind turbine and a pitch angle parameter representing a pitch angle of at least one of the wind turbine blades. Based on the obtained data sets, a statistical representation of the pitch angle parameter as a function of the relative wind direction is determined, which is then used in estimating a wind direction offset corresponding to the relative wind direction where the pitch angle parameter attains a maximum. The relative wind direction of the wind turbine is then adjusted as a function of the wind direction offset.

Abstract: A turbo pump vent assembly and method are disclosed. The turbo pump vent assembly comprises: a primary manual actuator operable to deliver an initial volume of air to a turbo pump; and a secondary manual actuator operable to deliver a secondary volume of air to the turbo pump, wherein the secondary volume of air is greater than the initial volume of air. In this way, an uncomplex and reliable vent is provided which can deliver initial volumes of air to slow the turbo pump initially. Thereafter, the secondary volume of air may be delivered to slow the turbo pump more rapidly than is possible just using further initial volumes of air. Having an apparatus which can deliver differing volumes of air enables the turbo pump to be slowed safely and more quickly than is possible by delivering just the same sized volumes of air.

Abstract: Systems, program products, and methods for adjusting operating limit (OL) thresholds for compressors of gas turbine systems based on mass flow loss are disclosed herein. The systems may include at least one computing device in communication with the gas turbine system, sensor(s) measuring operational characteristic(s) of the gas turbine system, and a pressure sensor measuring an ambient fluid pressure surrounding the gas turbine system. The computing device(s) may be configured to adjust operational parameters of the gas turbine system by performing processes including determining a mass flow loss between an estimated, first mass flow rate and a calculated, second mass flow rate for the compressor of the gas turbine system, and adjusting an OL threshold for the compressor of the gas turbine system based on the mass flow loss. The OL threshold for the compressor may be below a predetermined surge threshold for the compressor.

Abstract: A fan drive gear system for a turbofan engine includes a geared architecture and a gear controller supporting the geared architecture and controlling rotation of the geared architecture relative a static structure.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment including a sealing portion, and a first rail and a second rail opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces and extends in an axial direction between a leading edge and a trailing edge. Each of the first and second rails extend outwardly in a radial direction from the sealing portion to respective first and second edge faces, and the sealing portion has a sealing face dimensioned to bound a gas path and includes a backside face opposed to the sealing face. Each of the first and second rails includes at least one interface bore dimensioned to receive a retention pin such that the seal arc segment is carried by the retention pin in an installed position. The seal arc segment is radially opposed to the sealing face between the first and second edge faces establishing a first region.

Abstract: A labyrinth seal lip (5) comprises, standing on one of its lateral faces (7), a deflector (13) which channels the flow of gas tangent to the lip (5) towards the facing seal (4) so as to disturb the leakage flow (22) through the gap and decrease the flow rate.

Abstract: Embodiments of the present disclosure are directed to an inline centrifugal mixed flow fan system that includes a wheel assembly disposed within an outer housing and comprising a hub cone, a plurality of fan blades directly coupled to and extending radially outward from the hub cone, and a shroud directly coupled to and at least partially radially surrounding the plurality of fan blades. The wheel assembly is configured to receive an air flow at an inlet axial end of the outer housing axially upstream of the wheel assembly, and to redirect the air flow axially downstream relative to a central longitudinal axis, circumferentially about the central longitudinal axis, and radially outward from the central longitudinal axis.

Abstract: The invention relates to an inter-turbine casing (1) comprising: an inner shell (10), an outer shell (20), and an assembly of arms (2) extending radially between the timer (10) and outer (20) shells; and an assembly of splitter blades (30) positioned between the arms (2), each splitter blade (30) comprising an inner platform (33) and an outer platform (36). The inner shell (10) comprises at least one inner groove (11) for slidably receiving one or more inter platforms (33). The outer shell (20) comprises at least one outer groove (21) for slidably receiving one or more outer platforms (36). The inter-turbine casing further comprises locking means (4, 5) for locking the splitter blades (30) in the inner (11) and outer (21) grooves. The splitter blades are arranged using multiple tenons (39) that extend in corresponding ribs (12, 22).

Abstract: The invention relates to an intermediate case (25) for a twin spool turbomachine for an aircraft, comprising a hub (26), an outer shell (23) and outlet guide vanes (24) installed at their ends on the hub and on the outer shell, and each of at least some of the outlet guide vanes (24) performing a heat exchanger function and comprising a lubricant passage (50a, 50b) designed to be cooled by the fan flow (58) following an outer surface of the outlet guide vane. According to the invention, the case also comprises at least one lubricant duct (55) passing along a circumferential direction of the hub (26) and at least part of which is made from a single casting with the hub, the lubricant duct (55) having at least one lateral opening communicating with the lubricant passage (50a, 50b) of at least one of the vanes (24).

Abstract: A gas turbine engine for an aircraft having a centrifugal compressor including an impeller with impeller blades extending from a hub, the impeller mounted for rotation about a central longitudinal axis within an outer shroud. A main flow passage wall is located on a shroud side near the impeller exit, the main flow passage wall separating a cavity disposed on the shroud side from the main flow passage. One or more apertures are defined through the main flow passage wall and extending along a respective aperture axis between the cavity and the main flow passage. The apertures have a main flow passage side opening located radially outward from the impeller exit. The aperture axis is disposed at a radial angle relative to the central longitudinal axis.

Abstract: Disclosed is an air concentration tower for a vertical axis wind turbine. The air concentration tower has a polygonal outer perimeter, a pivot located at each vertex of the polygonal outer perimeter, and an inwardly-positioned rudder blade operatively connected at each pivot. Each inwardly-positioned rudder blade has a first wind-neutral position, and is pivotable through a plurality of angles that adjust based on an incoming wind direction, such that the incoming wind is channeled to the vertical axis wind turbine, which is located approximately at a center area of the polygonal outer perimeter. The air concentration tower is designed to provide higher wind speed to the vertical axis wind turbine than the surrounding ambient air.

Abstract: Disclosed herein is a sealing gas supply apparatus. In the sealing gas supply apparatus for supplying sealing gas to a turbomachine of a power generation system, a source comprises at least one low-temperature source for supplying a working fluid to the sealing gas supply apparatus and at least one high-temperature source for supplying a working fluid having a higher temperature than the low-temperature source to the sealing gas supply apparatus, and the working fluids are mixed in the sealing gas supply apparatus to be suitable for a sealing condition as a temperature condition required in a sealing system so as to be supplied to the sealing system of the turbomachine. In accordance with the present disclosure, since separate electric power is not consumed during normal operation by improving a turbine sealing gas source, it is possible to enhance power generation performance by a reduction in power consumption.