Abstract: There is provided an air filter for use in a heating, ventilation, and air conditioning (HVAC) system, the air filter including: a front portion comprising a molded filtering material, the molded filtering material defining a plurality of pockets arranged over a front face of the front portion; and a rear portion joined to the front portion, the rear portion defining a plurality of holes therethrough.

Abstract: A tube is thermally insulated for protecting a fluid flowing therethrough from a high includes temperature surrounding environment of a gas turbine engine. The tube includes a conduit, an insulating layer wrapped around the conduit, and an elongated contractible braided sleeve for preventing a separation of the insulating layer from the rigid conduit. The contractible braided sleeve is flexible along a longitudinal axis thereof and removably pulled over the insulating layer to snugly surround and maintain the insulating layer around the conduit.

Abstract: A method for routing data packets in a network including a plurality of nodes (2); the method comprises the operations of arranging in each node (2) transceiver units (4, 6, 8, 10) to transmit and receive the data packets and arranging processing means to process message data comprising attributes for identifying at least one transmitter node (20) and at least one receiver node (22). The method further comprises the operations of defining for each node (2) a plurality of static criteria, indicative of nominal configuration parameters for the nodes (2), and dynamic criteria, indicative of current operational conditions of the nodes (2), and sending from the transmitter node (20) to a plurality of intermediate receiver nodes (2) query data to search for at least one transmission route.

Abstract: An integral tandem bearing assembly for supporting a main shaft in a gas turbine engine is provided. The tandem bearing assembly comprises two bearing assemblies connected by integrated inner ring.

Abstract: A tube is thermally insulated for protecting a fluid flowing therethrough from a high temperature surrounding environment of a gas turbine engine. The tube comprises a conduit, an insulating layer wrapped around the conduit, and an elongated contractible braided sleeve for preventing a separation of the insulating layer from the rigid conduit. The contractible braided sleeve is flexible along a longitudinal axis thereof and removably pulled over the insulating layer to snugly surround and maintain the insulating layer around the conduit.

Abstract: A method of insulating an article including at least a portion of the article with an insulating layer, inserting the article portion surrounded by the insulating layer into an outer protective sleeve, and shrinking the outer protective sleeve around the insulating layer to compress and hold the insulating layer around the portion of the article by applying tension on the outer protective sleeve along a longitudinal direction thereof.

Abstract: A gas turbine engine having at least a rotor shaft operatively connecting a compressor apparatus and a turbine apparatus, comprises an auxiliary gear box and a phonic wheel apparatus. The auxiliary gear box is drivingly connected to the rotor shaft and the phonic wheel apparatus includes an oil pump having toothed gear and a sensor mounted to the oil pump for sensing a rotational speed of the toothed gear.

Abstract: The electric machine comprises a rotor configured and disposed to be attached at the free end of a shaft of another device, which free end is adjacent to at least one bearing coaxially mounted around the shaft and positioned intermediate opposite radial sides of the rotor.

Abstract: A method and apparatus for cooling a fluid in a bypass gas turbine engine involves directing the fluid to the bypass duct of the engine to allow for heat exchange from the fluid to bypass air passing through the bypass air duct.

Abstract: An integral tandem bearing assembly for supporting a main shaft in a gas turbine engine is provided. The tandem bearing assembly comprises two bearing assemblies connected by integrated inner ring.

Abstract: A gear shaft for a gearbox, the gear shaft having a spiral bevel gear integral and concentric therewith with portions of the gear shaft extending from each side of the spiral bevel gear, the spiral bevel gear having a negative helix angle.

Abstract: In a gas turbine engine, a fuel inlet tube comprising a body, a channel defined in the body and in fluid communication with a manifold, and a side inlet in fluid communication with the channel, such that fuel entering the side inlet is delivered to the manifold through the channel with a pressure generally directed along a radial axis of the body. Also, a fuel inlet tube comprising a heat shield surrounding at least part of a body, a chamber defined between the heat shield and the body and in fluid communication with fuel leak sources, a drain channel defined in the body in fluid communication with the chamber, and a drain hole defined in the body in fluid communication with the drain channel, such that a leak produces fuel received in the chamber and safely directed through the channel and the hole to allow detection of the leak.

Abstract: A gas turbine engine having at least a rotor shaft operatively connecting a compressor apparatus and a turbine apparatus, comprises an auxiliary gear box and a phonic wheel apparatus. The auxiliary gear box is drivingly connected to the rotor shaft and the phonic wheel apparatus includes an oil pump having toothed gear and a sensor mounted to the oil pump for sensing a rotational speed of the toothed gear.

Abstract: A method of insulating an article comprising: surrounding at least a portion of the article with an insulating layer, inserting the article portion surrounded by the insulating layer into an outer protective sleeve, and shrinking the outer protective sleeve around the insulating layer.

Abstract: A gas turbine diffuser assembly and a method for assembling same, includes providing a loose fit between the diffuser body and the diffuser pipes. Damper members provide a snug attachment.

Abstract: A bypass duct sealing grommet, for sealing between an opening in a gas turbine engine bypass duct wall and an external surface of a projection extending through the opening, where the grommet has an annular body with a central aperture having an internal periphery adapted to sealingly engage the external surface of the projection. A first flange and a second flange define an external slot about an exterior periphery of the body adapted to receive and seal the bypass duct wall between the flanges.

Abstract: A multi-position pressurized fluid actuator is mounted for movement in a casing. The actuator includes at least one selectively openable opening at a location corresponding to an intermediate position through which pressurized fluid can be selectively bled from the actuator to permit the actuator to remain in the intermediate position.

Abstract: A gas turbine diffuser assembly and a method for assembling same, includes providing a loose fit between the diffuser body and the diffuser pipes. Damper members provide a snug attachment.

Abstract: The electric machine comprises a rotor configured and disposed to be attached at the free end of a shaft of another device, which free end is adjacent to at least one bearing coaxially mounted around the shaft and positioned intermediate opposite radial sides of the rotor.

Abstract: The present invention includes a gas turbine engine exhaust centerbody comprising a forward portion having at least one flap at a downstream end thereof to induce a local low pressure zone in the exhaust gas flow without significantly impeding it, a tailcone partially inserted into the forward portion so that at least part of the at least one flap overlaps a portion of the tailcone, a centerbody cavity containing gas at a pressure higher than the local low pressure, and at least one opening between the forward portion and the tailcone adjacent to and upstream of one of the local low pressure zones and providing fluid communication between the cavity and the exhaust gas flow. A ventilation flow out of the centerbody cavity through each opening is induced by a positive difference between the pressure of the gas in the centerbody cavity and the low pressure of the adjacent zone.