An axial flow compressor comprises a tubular casing which encases a rotatable shaft, a pair of rotor segments coupled to the rotatable shaft and each comprising a bladed disc, and a banded stator segment disposed between the pair of rotor segments and comprising a plurality of stator vanes extending between an outer flowpath ring and an inner flowpath ring. A method of assembling an axial flow compressor comprises installing a rotor segment inside a tubular compressor casing, installing a vane segment adjacent the installed rotor segment, and repeating the steps of installing a rotor segment and vane segment until a desired number of rotor segment and vane segment pairs are installed.

A composite rotatable assembly for an axial flow compressor comprises a spool having a plurality of blade assemblies arranged in stages on the spool and attached thereto by a wound band. Each blade assembly comprises a blade and a base, with the base having a forward tang extending axially forward of a leading edge of the blade and an aft tang extending axially aft of a trailing edge of the blade. The band is wound over at least a portion of the forward and aft tangs of the plurality of blade assemblies to hold the blade assemblies to the spool under centrifugal loading. An abradable layer may be added over the wound band.

Disclosed embodiments relate to a combination axial fan and LED lighting system configured to fit into the footprint of a standard ceiling tile. Disclosed embodiments further include ceiling tiles with a built-in fan and/or LED lighting. The disclosed systems may include a housing container and an axial fan. The fan has a fan cavity including air diversion mechanism to direct air from the fan cavity toward the lighting and fan components. The inventions include an airflow surface to direct air existing the fan cavity along an LED light fixture. Moreover, disclosed embodiments include one or more UV light sources which irradiate contaminants as air flows through the ceiling tile.

A component for a gas turbine engine includes a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform. The outer surface of the platform can include a pocket and the cover plate is positioned relative to the pocket to establish a platform cooling channel therebetween.

The present invention provides a multi-stage compressor for a gas turbine engine. The compressor has: a first outer casing, a second outer casing radially outward of the first outer casing, and a first bleed plenum one or more second bleed plenums located between the first and second outer casings and arranged to receive, in use, bleed flows of compressed air from respective stages of the compressor and to send the bleed flows to respective ports in the second outer casing. The first bleed plenum overlaps the, or each, second bleed plenum such that the, or each, second bleed plenum fluidly communicates with its port via a respective duct which, on extending between an off-take from the second bleed plenum to the port, passes through the first bleed plenum. The, or each, duct is configured to accommodate relative movement between the first and second outer casings.

A vacuum pump includes a rotor provided with a plurality of rotor blades and a rotor cylinder portion, a driving portion, a bearing, stator blades, a thread groove stator that is disposed downstream of the stator blades and has an inner peripheral surface facing an outer peripheral surface of the rotor cylinder portion, and a heat insulating wall disposed downstream of the thread groove. The heat insulating wall includes a ring-shaped annular portion, and a substantially cylindrical wall portion extending from an inner portion of the annular portion in the radial direction to the upstream side and forming a flow path on the outer peripheral surface side. A first corner portion is formed between an upstream-side surface of the annular portion and the outer peripheral surface of the wall portion, the first corner portion being formed in an arc shape.

A heat exchanger module mountable to a vehicle frame by first and second lateral sides of the heat exchanger module. The heat exchanger module includes a fan shroud. The fan shroud is a structural fan shroud. The fan shroud includes first and second frame brackets extending from the fan shroud, one on the first lateral side and one on the second lateral side. The fan shroud is attached to at least one of a first heat exchanger and a second heat exchanger by at least one fastener that extends through the fan shroud.

A counter-rotating axial air moving device includes a front rotor and a rear rotor. The front rotor includes a front hub and a plurality of front blades, and the number of the front blades is equal to or greater than 7 and equal to or less than 11. The rear rotor is disposed on the downstream side of the front rotor. The rear rotor includes a rear hub and a plurality of rear blades, and the number of the rear blades is equal to or greater than 6 and equal to or less than 10. The front rotor and the rear rotor are stacked with each other with a total thickness and a diameter. The ratio of the total thickness to the diameter is equal to or more than 0.91 and equal to or less than 1.5.

A vane carrier assembly is provided for supporting vanes within a main engine casing of a gas turbine engine. The vane carrier assembly comprises a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly. The support panels are assembled such that the support panels expand circumferentially to minimize radial expansion of the vane support assembly during operation of the gas turbine engine. A control ring is coupled to the main engine casing, and the vane support assembly is coupled to the control ring. The control ring may be formed from a material having a coefficient of thermal expansion less than that of the material from which the vane support assembly is formed.

The present disclosure relates to a hairdryer and, more specifically, to a hairdryer wherein a ratio between dimensions of fan unit components is appropriately changed to stabilize the flow of air introduced into a fan unit and suppress occurrence of turbulence so that internal flow efficiency can be increased and the noise can be decreased.