Abstract: An air cycle machine includes a turbine wheel, a turbine inlet nozzle, a valve body, and a poppet member. The turbine wheel is mounted to rotate within the air cycle machine and the turbine inlet nozzle is positioned to direct airflow thereto. The poppet member selectively extends into the turbine inlet nozzle and the valve body controls a pressure on the poppet member to move the poppet member relative to the turbine inlet nozzle to vary the size of the turbine nozzle directing airflow to the turbine wheel.

Abstract: A supersonic compressor rotor that includes a rotor disk that includes a body that extends between a radially inner surface and a radially outer surface. A plurality of vanes are coupled to the body. The vanes extend outwardly from the rotor disk. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends between an inlet opening and an outlet opening. At least one supersonic compression ramp is positioned within the flow channel. The supersonic compression ramp is configured to condition a fluid being channeled through the flow channel such that the fluid includes a first velocity at the inlet opening and a second velocity at the outlet opening. Each of the first velocity and the second velocity being supersonic with respect to said rotor disk surfaces.

Abstract: A method for controlling at least two turbocompressors (1.1, 2.1), each having a control device (1.2, 2.2) for maintaining a distance relative to a surge limit curve (P1, P2) of the respective turbocompressor; wherein a first distance (A1.1, A2.1) is determined for each turbocompressor from its surge limit curve; wherein the distance to be maintained can be trimmed relative to this first distance in the control devices; and wherein the distance (A2.2) of a control device (2.2) to be maintained is trimmed relative to its first distance (A2.1) based on a trimming (A1.1?A1.2) of another control device (1.2) in such a way that a total process variable (dV/dt) remains substantially constant.

Abstract: A gas turbine compressor is disclosed. The compressor includes a compressor housing, guide vanes, rotor blades, and valve-controlled blow-in openings for stabilizing the compressor flow by air that is blown in. The air flow is detected by pressure sensors and the valves are controlled as a function thereof.

Abstract: A fan comprises a fan housing which includes a fan inlet, a motor which is connected to the fan housing, and an impeller which is removably connected to the motor. The impeller includes an impeller hub, a number of impeller blades which extend radially outwardly from the impeller hub, an impeller leading edge, an impeller trailing edge and an impeller tip. The fan housing includes an inlet shroud which is positioned over the impeller. The inlet shroud comprises an upstream end portion within which the fan inlet is formed and a downstream end portion which is removably connected to a separate portion of the fan housing. The inlet shroud further includes a first section which extends axially from the upstream end portion to approximately the impeller leading edge, a second section which extends axially from the first section to approximately the impeller trailing edge, and a third section which extends axially from the second section to approximately the downstream end portion.

Abstract: A damping structure for a turbomachine rotor. The damping structure includes an elongated snubber element including a first snubber end rigidly attached to a first blade and extending toward an adjacent second blade, and an opposite second snubber end defining a first engagement surface positioned adjacent to a second engagement surface associated with the second blade. The snubber element has a centerline extending radially inwardly in a direction from the first blade toward the second blade along at least a portion of the snubber element between the first and second snubber ends. Rotational movement of the rotor effects relative movement between the first engagement surface and the second engagement surface to position the first engagement surface in frictional engagement with the second engagement surface with a predetermined damping force determined by a centrifugal force on the snubber element.

Abstract: A compressor includes a shaft assembly including a thrust disk disposed on a main shaft and a housing having a first portion and a second portion, the first and second portions adapted to receive the shaft assembly and enclose the shaft assembly therebetween, wherein the shaft assembly is rotatably disposed within the housing, and wherein at least one of the first portion and the second portion includes a shaft assembly retention feature for receiving the thrust disk to regulate a motion of the shaft assembly.

Abstract: A turbine stator vane with a cooling circuit that improves the cooling effectiveness of the airfoil as well as collects any dirt particles before passing the clean cooling air through the cooling circuit. The airfoil includes a 3-pass aft flowing serpentine circuit with a first leg located along the airfoil leading edge and connected to a showerhead arrangement for film cooling discharge. A cooling air supply channel is located between the first leg and the second leg of the serpentine flow circuit, and the cooling supply channel includes ribs arranged to produce a vortex flow within the cooling air that collects the dirt particles within a center of the vortex flow and deposits the dirt particles at the bottom of the channel. The vortex flow cooling air flows through impingement holes to produce impingement cooling on the backside wall of the leading edge with clean cooling air.

Abstract: A bidirectional water turbine including: an upstream rotor and a downstream rotor, wherein the upstream rotor and downstream rotor are contra-rotating and each rotor includes a plurality of blade, the blades of the upstream and downstream rotors having substantially the same profile.

Abstract: A support system for at least one water drivable turbine (1) that when in operation is immersed in a column of flowing water, characterized in that the system includes a deck or raft (3) for supporting said at least one turbine when immersed, the deck or raft (3) having an inherent buoyancy which is such as to enable the deck or raft (3) to rise through the column of water upon reduction of the buoyancy, the arrangement being such that the associated turbine or turbines (1) can be raised above the surface of said column in order to access the turbine for maintenance purposes.

Abstract: The fan rotor blade (73) has a root (73a) located at an end at the side of a rotary disk (75), and a tip (73b) located at an outer end in a radial direction of the rotary disk (75), and extends from the root (73a) to the tip (73b). The root (73a) has an attached part (93) attached to a rotor blade fixing part (75a) of the rotary disk (75), and an extension part (95) extending from the attached part (93) toward the upstream side. An upstream end of the extension part (95) is a free end.

Abstract: A gas turbine engine is provided that includes a low pressure spool, a high pressure spool, a stationary support frame, and at least one support arch. The low pressure spool extends between a low pressure compressor and a low pressure turbine. The high pressure spool extends between a high pressure compressor and a high pressure turbine. The spools are rotatable about a center axis of the engine. The support arch has a stationary support mount disposed between a low spool mount and a high spool mount. The support arch is disposed relative to the spools and the stationary support frame so that a load from each spool caused by the rotation of that spool can be transferred to the stationary support frame through the support arch. The support arch can freely rotate about the center axis of the engine relative to the spools and the stationary structural frame.

Abstract: An outlet plate of an impeller pump is provided, the outlet plate having an outlet port disposed in the outlet plate, the outlet port being defined by a first outlet port and a second outlet port each extending through the outlet plate; a separator wall located in the outlet port, the separator wall separating an inlet of the first outlet port from an inlet of the second outlet port; and a groove located only on a first surface of the outlet plate, the groove having a first distal end and a second distal end, the first distal end terminating at the first outlet port, wherein the separator separates the groove from the second outlet port.

Abstract: A cycloidal rotor system having airfoil blades travelling along a generally non-circular, elongated and, in most embodiments, dynamically variable orbit. Such non-circular orbit provides a greater period in each revolution and an optimized relative wind along the trajectory for each blade to efficiently maximize lift when orbits are elongated horizontally, or thrust/propulsion when orbits are vertically elongated. Most embodiments, in addition to having the computer system controlled actuators to dynamically vary the blade trajectory and the angle of attack, can also have the computer system controlled actuators for dynamically varying the spatial orientation of the blades; enabling their slanting motion upward/downward and/or backsweep/forwardsweep positioning to produce and precisely control a variety of aerodynamic effects suited for providing optimum performance for various operating regimes, counter wind gusts and enable the craft to move sideways.

Abstract: A multistage high-pressure pump according to the present invention includes a rotational shaft (1), impellers (3) secured to the rotational shaft, a casing (2) configured to house the impellers therein, a mechanical seal (20), a seal chamber (25) that houses the mechanical seal therein, an oil reservoir (30) configured to store oil therein, an oil supply line (26) providing fluid communication between the oil reservoir (30) and the seal chamber (25), an oil pump (31) configured to pressurize the oil from the oil reservoir (30) and supply the oil to the seal chamber (25), a pressure retaining mechanism (32, 34, 35) configured to retain pressure of the oil in the seal chamber (25), and an oil outlet line (27) for discharging the oil from the seal chamber (25). The pressure of the oil in the seal chamber (25) is higher than pressure of the fluid.

Abstract: A damping structure for a turbomachine rotor. The damping structure including an elongated snubber element including a first snubber end rigidly attached to a first blade and extending toward an adjacent second blade, and an opposite second snubber end positioned adjacent to a cooperating surface associated with the second blade. The snubber element has a centerline extending radially inwardly in a direction from the first blade toward the second blade along at least a portion of the snubber element between the first and second snubber ends. Rotational movement of the rotor effects relative movement between the second snubber end and the cooperating surface to position the second snubber end in frictional engagement with the cooperating surface with a predetermined damping force determined by a centrifugal force on the snubber element.

Abstract: An insertion/extraction system and method for a compressor casing and a compressor bundle. The system includes a cradle extending from a first axial end of the compressor casing and configured to provide support for the compressor bundle during insertion, and an extension assembly coupled to a first axial end of the compressor bundle and extending therefrom into the compressor casing during insertion of the compressor bundle into the compressor casing, during extraction of the compressor bundle from the compressor casing, or both. The system further includes a support member that engages the extension assembly and the compressor casing to support the first axial end of the compressor bundle via the extension assembly, the support member configured to allow relative movement between the support member and the extension assembly during insertion of the compressor bundle into the compressor casing, extraction of the compressor bundle from the compressor casing, or both.

Abstract: A fan frame for a heat dissipation apparatus is provided. The fan frame includes an outer frame, an inner frame sleeved in the outer frame and slidable relative to the outer frame, a latching mechanism for mechanically securing the inner frame to the outer frame. The latching mechanism includes one or more resilient latches, one or more receiving portions capable of receiving the resilient latches in a first latched position and a second latched position, and an actuator mechanism connected to the outer frame and capable of resisting the resilient latch to cause elastic deformation of the resilient latch, thereby withdrawing the resilient latch from the receiving portion.

Abstract: A wind turbine generator generates power through rotation of a rotor to which a plurality of blades are pivotally coupled and includes a pitch-angle control section that outputs a pitch-angle command value that indicates the amount of change in the pitch angle of each of the blades, hydraulic cylinders each of which changes the pitch angle of the corresponding blade based on the corresponding pitch-angle command value output from the pitch-angle control section, and load measurement sections that measure blade-root loads. A set value indicating that wind received by the wind turbine generator has a biased wind speed distribution is set in advance in the pitch-angle control section. Only when a calculated pitch-angle command value exceeds the set value, the pitch-angle control section outputs a pitch-angle command value beyond pitch command limit values.

Abstract: A rotor (1) of a gas turbine compressor comprises a multiplicity of welded-together rotor disks (3a, 3b, 4, 5), of which two or more rotor disks (3a, 3b), in a radially outer region (9?), are welded together, and, in a radially inner central region (9), are abutment-joined together. Via the abutment-joining of two rotor disks (3a, 3b), a heat flow (8) radially outward from the center of the rotor (1) is achieved so that the material temperature of the rotor (1) can be kept below a predetermined level during operation. As a result, the service life of the rotor (1) can be increased. In one embodiment, one rotor disk (3a), on its surface, additionally has a recess (7) which can be cooled from outside. The rotor disks (3a, 3b) according to the invention, which are welded and abutment-joined together, can especially be used at the last point in the flow direction of the compressor.