A damping link assembly for a bleed valve of a gas turbine engine. The damping link assembly having: a bleed valve ring having a link aperture; a mechanical fastener disposed in the link aperture; and a damping guide link operatively coupled to the mechanical fastener at one end for rotation about a first axis of the mechanical fastener and the damping guide link being operatively coupled to an idler bracket at an opposite end for rotation about a second axis, the damping guide link being capable of twisting about a third axis different from the first axis and the second axis when the bleed valve ring is rotated from a first position to a second position.

A centrifugal compressor includes a rotary shaft of a compressor impeller, a gas bearing structure that supports the rotary shaft, a motor that rotates the rotary shaft, a motor housing that houses the motor, a compressor housing that houses the compressor impeller and includes an intake port and a discharge port, a gas bleed port that is provided closer to the discharge port than the compressor impeller in a flow direction in the compressor housing, a bearing cooling line that connects the gas bleed port to the gas bearing structure, and a heat exchanger that is disposed on the bearing cooling line. The heat exchanger is mounted on at least one of the motor housing and the compressor housing.

This invention relates to a turbocharger (210). More specifically, the invention relates to an axial-entry type turbocharger, where the exhaust gases are directed to meet the turbine wheel at least front-on, having a variable volume for controlling pressure, allowing for a substantially uniform pressure and uniform velocity to act simultaneously on and around the turbine wheel, while enabling the volume of the turbocharger to be adjusted under predetermined set pressure conditions. The turbocharge includes: a turbine housing defining a substantially axial primary flow duct, a primary turbine wheel (216) mounted along such primary flow duct (214), and a diverter (218) for diverting flow passing thereover into a primary annular flow path directed to impinge the primary turbine wheel (216). The turbine housing of the turbocharger defines a secondary flow duct (222) for directing some flow to: (i) impinge the primary turbine wheel (216); and/or (ii) bypass the primary turbine wheel (216). A secondary flow duct gate (223) controls flow through the secondary flow duct (222) and is movable between a closed position, wherein under low pressure conditions flow is restricted from flowing through the secondary flow duct (222), and an open position, wherein flow though the secondary flow duct (222) is enabled such that operative flow passes through both the primary and the secondary flow ducts (216, 222) under high pressure conditions. The turbocharger further includes at least one compressor coupled to the primary turbine wheel (216) via a primary transmission thereby to transmit drive from the primary turbine wheel (216) to the compressor.

Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.

A pressure regulating valve assembly includes: a valve having an upstream side receiving an input flow and a downstream side providing an output flow, an actuator for opening and closing the valve, including partially opening the valve, and a regulator controlling the actuator to open, close or partially open the valve. The regulator includes a sense pressure port, wherein pressure at the port is maintained constant by the regulator. A chamber has a first entry orifice, a second entry orifice and an exit orifice. The first entry orifice is connected to the upstream side, the second entry orifice is connected to the downstream side, and the exit orifice is connected to the port. The exit orifice provides that the pressure at the exit orifice lies between the pressure at the first entry orifice and the pressure at the second entry orifice.

A variable geometry turbocharger (VGT) is provided. The VGT includes a unison ring that rotates a plurality of vanes disposed in a nozzle ring and a sagging prevention mechanism. The sagging prevention mechanism is installed to support the unison ring in a direction opposite to a direction in which a self-weight of the unison ring acts. In particular, the sagging prevention mechanism includes a support pulley that is installed to provide an elastic pressure on an outer circumferential surface of the unison ring in rolling contact therewith.

A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.

An exhaust turbocharger includes an air-guiding section. A spiral channel is formed downstream of a wheel chamber in the air-guiding section. Between the wheel chamber and the spiral channel, a diffuser channel is formed in the air-guiding section. Upstream of the wheel chamber, an inlet channel is formed in the air-guiding section for the inflow of fluid to be compressed. In the inlet channel, a cross-section-changing unit. The cross-section-changing unit comprises an operating element with at least two movable element parts to produce a baffle which can protrude, with the aid of an adjusting unit, into the inlet cross-section rotationally and/or in a translational manner or can be removed from the inlet cross-section. The two element parts are fixedly disposed at one element end jointly in the air-guiding section. A relative movement of the element parts can be brought about in particular in an opposing direction.

A powered augmented fluid turbine for generating electricity from a fluid in motion comprising: a central annular ducted channel extending between an inlet distribution header and an outlet distribution header, the channel comprising a converging section configured to accelerate the fluid received at the inlet distribution header, a turbine assembly for generating electricity, and a diffuser section configured to decelerate the fluid before it exits at the outlet distribution header; a recycle line for transporting the exiting fluid to the inlet distribution header in a closed-loop configuration, the recycle line comprising a recycle line propulsor controllable by a recycle line controller and a recycle line heat exchanger; and a compressed fluid distribution line configured to pressurize the fluid in motion by transporting a compressed fluid from a compressed fluid source to the inlet and outlet distribution headers, the compressed fluid distribution line controllable by at least one pressure controller.

An orifice assembly includes a first member defining an orifice having a first dimension in a compressed state and a thermally-sensitive material arranged adjacent to the first member. The thermally-sensitive material has a rigid, first state that applies force to the first member so as to maintain the first dimension of the orifice in the compressed state and a flexible, second state configured to release the force applied to the first member. As such, when subjected to temperatures above a predetermined temperature threshold, the thermally-sensitive material changes from the rigid, first state to the flexible, second state to allow the first dimension of the first member in the compressed state to passively expand to a decompressed, second dimension, the second dimension being larger than the first dimension.