Abstract: A turbine component has a plurality of cooling passages each extending through a body of a structure between opposite hot and cold surfaces of the structure. According to one embodiment, at least one of the cooling passages includes a plurality of upstream paths defining respective inlet openings on the cold surface and merging into a number of downstream paths defining respective outlet openings on the hot surface.

Abstract: A method for controlling an inlet-adjustment mechanism in an air inlet for a compressor so as to switch the mechanism in a binary fashion between open and closed positions for adjusting a flow area of the inlet. The method includes identifying a threshold line on a compressor map of pressure ratio versus corrected flow rate for the compressor, at which the inlet-adjustment mechanism is switched from one of its positions to the other. A fixed switch band straddling the threshold line can be used for determining when to initiate the switch of positions so as to time the switch to coincide with the operating point reaching the threshold line. Alternatively, a time to reach the threshold line can be instantaneously computed and compared to the actuator/mechanism response time.

Abstract: A sealing system for a rotary machine is provided. The sealing system includes a pair of circumferentially adjacent rotary components. Each of the rotary components includes a platform, a shank, and a radial seal. The shank extends radially inwardly from the platform and includes a radially extending first side channel and an opposite radially extending second side channel. The radial seal includes a first leg received in the first side channel of a first of the pair of rotary components, a second leg received in the second side channel of a second of the pair of rotary components (201), and a resiliently deformable body extending therebetween, the body including a U-shaped portion located generally centrally between the first leg and the second leg.

Abstract: A propeller pitch control system for a turboprop engine of an aircraft includes an engine control unit and a pitch control unit. The engine control unit is operable to determine a phase of flight of the aircraft and is configured to supply control commands. The pitch control unit is coupled to receive the control commands from the engine control unit and includes a housing, a beta piston, a position sensor, a beta tube, and an electrohydraulic valve. The engine control unit only commands the electrohydraulic valve to move the beta piston from the fully retracted position when the engine control unit determines the aircraft is conducting pre-takeoff roll taxiing operations or is conducting post landing touchdown operations.

Abstract: An exhaust diffuser includes: an internal cylinder; an external cylinder that forms an exhaust passage between the internal cylinder and the external cylinder, the exhaust passage expanding from front to rear; and at least one tubular strut that couples the internal cylinder and the external cylinder together. The external cylinder includes: a front conical portion that is positioned forward of the tubular strut; and an outer flaring portion that starts flaring at a positon forward of the tubular strut at an inclination angle that is greater than an inclination angle of the front conical portion. The internal cylinder includes: a front straight portion that faces the front conical portion and the outer flaring portion; and an inner flaring portion that starts flaring at a position between a maximum width portion and a trailing edge of the tubular strut.

Abstract: A method of assembling and disassembling a gas turbine, and a gas turbine assembled thereby, improves work efficiency and reduces time and cost by carrying out various disassembly and reassembly processes depending on circumstances. In one process, a turbine section is disassembled from a gas turbine by sequential steps of disassembling an upper turbine case; disassembling a rear diffuser assembly and a rear bearing assembly; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. In another process, first-stage to fourth-stage blade assemblies and first-stage to fourth-stage vane assemblies in a turbine section are disassembled from the gas turbine by sequential steps of disassembling an upper turbine case; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly.

Abstract: Disclosed is a vane assembly fixed to a turbine casing of a turbine and configured to guide the flow of combustion gas having passed by a turbine blade airfoil. The vane assembly comprises a vane airfoil configured to guide the flow of the combustion gas, a platform portion combined with an end of the vane airfoil, carrier hook portions formed at respective periphery portions of the platform portion and provided with a thermal stress prevention slot on a surface facing the turbine casing, and a seal plate installed in the thermal stress prevention slot, thereby preventing a portion of compressed air produced by a compressor and supplied to the platform portion between the carrier hook portions from leaking out of the platform portion through the thermal stress prevention slot.

Abstract: A cantilevered vane, for use with a rotary disc of a gas turbine, includes a root supported in a dovetail slot formed in a circumferential surface of the rotary disc; and an airfoil protruding a predetermined height from the root and having a J-shaped cross-section throughout a front-wing portion and a rear-wing portion of the airfoil. The airfoil includes a straight portion vertically extending upward from the root by a predetermined height; and a curved portion integrally formed with an upper end of the straight portion to cantilever toward one side of the airfoil, the curved portion being inclined at a predetermined angle with respect to the straight portion. Cooling fluid flows through a first channel formed in the straight portion and a second channel formed in the curved portion. The first channel includes front-wing and rear-wing channels for guiding the cooling fluid to the front-wing and rear-wing portions.

Abstract: A wind turbine blade includes: a blade body extending from a blade root along a blade longitudinal direction toward a blade tip; and a metal strip provided to cover at least a leading edge at the blade tip side of the blade body so as to suppress erosion at the leading edge of the blade body.

Abstract: This disclosure relates to a buffer system for a gas turbine engine. An exemplary gas turbine engine includes, among other features, a buffer manifold in an intershaft region. The buffer manifold is configured to direct a flow of air between a first air seal and a first oil seal, and to direct another flow of air between a second air seal and a second oil seal.

Abstract: Airfoils, additively manufactured airfoils, and methods of manufacturing airfoils are provided. For example, an airfoil comprises opposite pressure and suction sides that extend axially from a leading edge to a trailing edge and radially spaced apart inner and outer ends. The airfoil also comprises an outer wall defining the pressure and suction sides and leading and trailing edges. A rib extends within the airfoil from the pressure side to the suction side of the outer wall and radially from the inner to the outer end. The airfoil further comprises a first pre-impingement chamber surrounded by a first post-impingement chamber and a first dividing wall segment separating the first pre-impingement and first post-impingement chambers and having a plurality of cooling holes defined therein. The outer wall, rib, and first dividing wall segment are integrally formed as a single monolithic component.

Abstract: A blast fan includes: a tubular frame having a first opening and a second opening to pass airflow through between the first opening and the second opening. The first opening has a first reverse tapered portion expanding from inside to outside of the frame, and the first reverse tapered portion has a surface having first convex portions projecting to the inside of the frame.

Abstract: An example rotating swashplate ring to rotor mast connection includes a polygon-shaped drive tube secured to the rotor mast and a gimbal joint connected between the rotating swashplate ring and the polygon-shaped drive tube, wherein the gimbal joint rotates with the rotor mast and can translate axially along the polygon-shaped drive tube.

Abstract: An expansion joint for use between a turbine duct and a diffuser duct includes a first flange coupled to the turbine duct, a second flange coupled to the diffuser duct, and a flexible element positioned between and coupled to the first flange of the turbine duct and the second flange of the diffuser duct. The flexible element defines a trough for receiving a liquid therein. The trough includes a drain pipe configured to channel the liquid away from the trough.

Abstract: The present disclosure is directed to methods for manufacturing wind turbine rotor blades and components thereof, e.g. using 3D printing. In one embodiment, the method includes forming a rotor blade structure having a first surface and an opposing, second surface, the first and second surfaces being substantially flat. Another step includes printing a leading edge segment of the rotor blade onto the first surface, wherein heat from the printing bonds the leading edge segment to the first surface. The method also includes rotating the rotor blade structure having the leading edge segment attached thereto. A further step includes printing a trailing edge segment of the rotor blade onto the second surface, wherein heat from the printing bonds the trailing edge segment to the second surface. Another step includes securing one or more fiber-reinforced outer skins to the leading and trailing edge segments so as to complete the rotor blade.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a tower shaft rotatable about an axis, an engine component rotatable with the tower shaft about the axis, and a seal assembly. The engine component extends axially along the axis to an end surface. The seal assembly includes a carbon seal element, where the carbon seal element circumscribes the tower shaft and axially engages the end surface.

Abstract: A method for determining sufficiency of compressive residual stresses in region below cold worked surface covered by a polished surface. Method includes obtaining surface height data along scanning passes over unpolished surface of the cold worked surface and the polished surface, determining region of surface height data with low and high points, and calculating step height by calculating difference between low and high points. Determining average height of the polished surface and peak height of the unpolished surface for the low and high points respectively. Cold worked surface may be peened surface. Confocal scanning microscope may be used for obtaining surface height data. Method may be used for qualifying a cold working or peening and polishing process for an airfoil which may include at least one feature from group consisting of camber, twist, curve away from the span, and lean away from the span.

Abstract: The present disclosure is directed to a lift system for a rotor blade of a wind turbine. The lift system includes a lifting device having at least one cradle. The cradle has a profile that corresponds to at least one of the exterior surfaces of the rotor blade so as to support at least a portion of the rotor blade. Further, the lift system includes a positioning assembly having at least one distance sensor mounted to the hub and at least one visual sensor mounted to the lifting device. Thus, the distance sensor is configured to identify a distance from the hub to the lifting device and the visual sensor is configured to identify a position of the rotor blade in the cradle.

Abstract: The rotatable machine includes a compressor and an inner annular casing circumscribing at least a portion of the compressor. The inner annular casing includes an outer surface in a radial direction, an upper portion in a vertical direction, and a lower portion in a vertical direction. The clearance control system includes a manifold system including at least one conduit extending circumferentially around the lower portion of the inner annular casing. The clearance control system includes a header system including at least one header extending circumferentially around only the lower portion of the inner annular casing. The at least one header configured to receive a flow of cooling fluid from the at least one conduit. The at least one header configured to channel the flow of cooling fluid to the lower portion of the outer surface of the inner annular casing.

Abstract: The present disclosure provides a method for manufacturing a middle frame for mobile terminal and a mobile terminal with a middle frame. The method may include: providing a metal plate; forming a number of elongated protrusions arranged in parallel on the plate, the elongated protrusions each extending along a length direction of the metal plate; forming a tubular blank by bending the metal plate such that each of the elongated protrusions extends around the tubular blank; and cutting the tubular blank into a number of annular pieces, wherein each of the annular pieces includes one of the elongated protrusions.