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 gas turbine engine includes a high-pressure compressor having an impeller and an impeller baffle having a generally annular body, the impeller baffle spaced apart from a back face of an impeller to create an airspace therebetween, the airspace communicating between an impeller exit and an apparatus to be pressurized, the impeller baffle including a plurality of generally radially-disposed ribs extending into the airspace for diminishing the velocity of air swirling in the airspace.

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 includes a high-pressure compressor having an impeller and an impeller baffle having a generally annular body, the impeller baffle spaced apart from a back face of an impeller to create an airspace therebetween, the airspace communicating between an impeller exit and an apparatus to be pressurized, the impeller baffle including a plurality of generally radially-disposed ribs extending into the airspace for diminishing the velocity of air swirling in the airspace.