United Technologies Corporation

Kenneth L Allard

Robert E Peters

Dwayne E Messerschmidt

Larry W Spires

J Axel Glahn

Roger M Barnsby

Hsianmin Jen

Hslanmin F Jen

Harvey I Weiner

Axel J Glahn

An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.

Bifurcated oil scavenging bearing compartment within a gas turbine engine

Method of scavenging oil within a gas turbine engine

Bifurcated oil scavenge system for a gas turbine engine

The present invention is a bi-directional tapered roller bearing having a first cone rib ring thrust face &ldquo;C&rdquo; adjacent and facing the small diameter end faces of the roller elements, a second cone rib ring thrust face &ldquo;B&rdquo; adjacent and facing the large diameter end faces of the roller elements, and a cup rib ring thrust face &ldquo;A&rdquo; adjacent and facing the large diameter end faces of the roller elements. The bearing components are arranged such that, during primary thrust load operation, there is a gap between thrust face C and the small diameter end faces of the roller elements, a gap between thrust face A and the large diameter end faces of the roller elements, and contact between thrust face B and the large diameter end faces of the roller elements. With this arrangement, bearing roller element centrifugal loads act to reduce the contact forces between the roller elements and the bearing races.

High load capacity bi-directional tapered roller bearing

The bore of the compressor for a gas turbine engine is heated by selectively bleeding compressor air from downstream stages so that heating only occurs at discreet times during the engine operating envelope. The bled air is admitted into the bore at the mid-stage station of the compressor wherein the compressor disks are scrubbed so as to expand and close the gap between the outer air seal and tips of the compressor blades during cruise of the aircraft and prevented from heating the disks during the high powered operations of the engine.

Active clearance control

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Wilbraham, MA, United States of America

Kenneth L Allard