Abstract: A stator assembly includes a platform located on a radially inner end of a plurality of vanes that connects a first vane to a second vane. There is a platform groove on a radially inner side of the platform between the first vane and the second vane.

Abstract: A method for the positioning of a cover disk with respect to an open impeller of a pump arranged in a pump housing. An adjustment bolt is first screwed so far into a threaded bore of the cover disk until it comes into contact with the pump housing. An identifier is subsequently applied which indicates a position of a first marking of the adjustment bolt. The adjustment bolt is then screwed in further until a second marking reaches the identifier. The described steps are repeated for at least one further adjustment bolt.

Abstract: A system for monitoring the deflection of a wind turbine blade is described. The system comprises a wireless range-measurement system, having at least one wireless communication device located towards the root end of the blade and at least one wireless communication device located towards the tip end of the blade. The root end device is provided on a bracket projecting from the external surface of the blade, to provide a communication path between the root end and tip end devices which is less susceptible to interference from multipath effects, etc. There is further provided a method to derive tilt and yaw moments from measured deflections. A control method for such a system is also described, wherein the signal gain of the communication path may be varied based at least in part upon the deflection characteristics of the wind turbine blade.

Abstract: A gas turbine engine comprising a fan and an intake liner 30, the liner 30 comprising at least two acoustic absorption segments 32 forming a duct and an axially extending splice 40 at each axially extending interface 38 between segments 32, the splice 40 being located between the segments 32. At least one of the splices 40 comprises a first portion 42 and a second portion 44, the splice 40 having a greater segment 32 separating width in the second portion 44 than in the first portion 42 so that adjacent the first portion 42 the segments 32 are closer together than adjacent the second portion 44. The first portion 42 is nearer to the fan than the second portion 44.

Abstract: The presently disclosed embodiments utilize a rear bearing sleeve interposed between an inner surface of an exhaust housing of a gas turbine auxiliary power unit and the rear roller bearing supporting a turbine within the exhaust housing. In some embodiments, the rear bearing sleeve includes a lubricant supply channel formed in an outer surface thereof for receipt of a supply of lubricant, and at least one lubricant supply opening between the outer surface and an inner surface thereof, the inner surface of the bearing sleeve forming an outer race of the rear roller bearing. The at least one lubricant supply opening supplies the lubricant to a gap between the rear roller bearing and the rear bearing sleeve for formation of a squeeze film viscous damper therebetween.

Abstract: A component includes at least one thermal riser that extends from an exterior surface of the component. At least one cooling passage extends through a wall and adjoins an interior cooling passage and provides an exterior surface. At least one cooling passage is configured to direct cooling fluid through the wall adjacent to at least one thermocouple.

Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.

Abstract: In a control device for a flow-through exhaust gas guide section of a turbine for opening and closing a bypass duct to permit exhaust gas to bypass a turbine wheel arranged in a turbine wheel housing of the exhaust gas guide section comprising with an actuating device and a cover element being provided for opening or closing a flow cross-section of the bypass duct, the cover element is a hollow truncated cone with passages provided in the cone-shaped cover element which differ from one another so as to provide for a controllable efficient and quiet exhaust gas flow through the flow cross-section into the bypass duct.

Abstract: A bearing arrangement with a first bearing layer comprising a first bearing support element and a second bearing layer comprising a second bearing support element, the first and second bearing layers being glidingly interconnected by at least one intermediate gliding element, wherein at least one first gliding surface is arranged between the first bearing support element and the at least one intermediate gliding element, and wherein at least one second gliding surface is arranged between the second bearing support member and the at least one intermediate gliding element, the at least one intermediate gliding element being elastically attached to the first bearing support element by means of at least one first flexible connector and to the second bearing support element by means of at least one second flexible connector.

Abstract: A unit including an intermediate turbojet casing formed by a hub including a downstream transverse endplate having formed therein at least one first opening putting the inside of the hub into communication with a duct extending downstream from the endplate and opening out at its downstream end via a second opening formed in an outer annular shroud extending downstream from the hub for defining the inside of an annular flow space for a secondary stream, is provided. The upstream end of the duct is fastened to the downstream endplate of the hub by releasable elastic engagement.

Abstract: A system for controlling variable-pitch vanes for a turbine engine, including a control ring having an axis of revolution and, about the axis of revolution, an annular row of connecting rods for connecting the ring to the vanes, each connecting rod including a first end designed so as to be connected to one of the vanes, and a second end which is connected to an elongate shaft which is connected to s the ring. The shaft connected to each connecting rod has an axis of elongation which is inclined relative to a plane extending substantially through the axis of revolution and the connecting rod.

Abstract: A compressor includes an impeller, a housing, and a connecting shaft. An inlet for introducing gas into a suction side of the impeller, and an annular groove formed in an outer periphery of the inlet are formed in the housing. The groove communicates with the inlet on the intake passage side. The groove is blocked on the impeller side. A gas outlet of an EGR passage is connected with a middle of the groove. An inner diameter of the groove is machined to be larger than an inner diameter of an end part of the gas outlet of the intake passage (an end part on the inlet side).

Abstract: The present invention provides a pump impeller which has improved anti clogging characteristics, in particular through the use of an impeller vane having a specially profiled leading edge which, during operation of the impeller, forces rags or the like down along the leading edge, which increases in thickness along the length thereof, until the rags become re-entrained in the fluid and thus exit the impeller avoiding the clogging thereof.

Abstract: A turbine exhaust case (28) comprises a fairing (120) defining an airflow path through the turbine exhaust case, and a multi-piece frame (100). The multi-piece frame is disposed through and around the fairing to support a bearing load, and comprises an inner ring (104), an outer ring (102) disposed concentrically outward of the inner ring, a plurality of bossed covers (110), and a plurality of radial struts (106). The plurality of bossed covers are bolted to the outer ring at locations circumferentially distributed about the outer diameter of the outer ring. The plurality of radial struts pass through the fairing and are secured via non-radial connectors (112, 114) to the inner ring and the bossed covers.

Abstract: A turbofan engine includes a fan rotatable about an axis and a compressor section including a high pressure compressor and a low pressure compressor. A turbine section includes a high pressure turbine, an intermediate turbine and a fan drive turbine. The high pressure turbine is coupled to drive the high pressure compressor. A fan drive gear system is driven by the fan drive turbine for driving the fan and a compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor.

Abstract: A wind turbine is having at least one rotor blade, a blade heating system for heating at least a portion of the at least one rotor blade, at least one temperature sensor for sensing the external temperature in the region, or in the environment, of the wind turbine, at least one air humidity sensor for sensing the air humidity in the region, or in the environment, of the wind turbine, and a control unit for activating the blade heating system if the temperature falls below a temperature limit value and if an air humidity limit value is exceeded, the temperature limit value being +5° C. and the air humidity limit value being 70%.

Abstract: A rotary device, comprises a central hub; and at least one blade extending from the hub; wherein the blade comprises a blade body and a blade cap, the blade body having a blade body tip, the blade cap being arranged to cover the blade body tip; and wherein the blade cap comprises a mesh.

Abstract: A bleed valve includes a valve body, a first flapper body movable relative to the valve body between an open position and a closed position, and a second flapper body movable relative to the valve body between an open position and a closed position. A resilient member biases the first and second flapper bodies to the open position to vent bleed air. The first and second flapper bodies move to the closed position when a pressure load across the first and second flapper bodies exceeds a biasing force of the resilient member. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first surface, an outlet located at the second surface, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and having a first downstream end adjacent the outlet and spaced from the inlet by a first distance, a second lobe diverging longitudinally from the metering section and having a second downstream end adjacent the outlet and spaced from the inlet by a second distance different from the first, and a transition region positioned between the lobes, the transition region having a third downstream end adjacent the outlet.

Abstract: An airfoil includes an airfoil body extending from an inner diameter platform to an opposed outer diameter platform along a longitudinal axis. The airfoil body defines a leading edge and a trailing edge and has a cavity defined between the leading edge, the trailing edge, the inner diameter platform and the outer diameter platform. The cavity includes an airfoil protrusion extending inward from an inner surface of the airfoil body. The airfoil includes a baffle body within the cavity extending along a baffle body axis. The baffle body has a baffle protrusion extending along a central protrusion axis at an angle with respect to the baffle body axis. The end of the baffle protrusion abuts an end of the airfoil protrusion. A flow path is defined between the inner surface of the airfoil body and the outer surface of the baffle body.