United Technologies Corporation

Rtx Corporation

Raytheon Technologies Corporation

Michael C Firnhaber

Colin G Amadon

Enzo DiBenedetto

Matthew E Bintz

Fadi S Maalouf

Mark E Simonds

John P Tirone

Michael Ronan

David M Dyer

Victor G Filipenco

Scott Gammons

Brittany Travis

Zachary J Jeske

A stator configuration for a gas turbine engine including: a splitter segment, the splitter segment extending from a forward end to a rearward end, the splitter segment being configured to split an incoming fluid flow into a first, radially outer stream and a second, radially inner stream; a forward most first stator extending radially outwardly from the splitter segment, the forward most first stator being completely located downstream from the forward end of the splitter segment; a forward most second stator extending radially inwardly from the splitter segment, the splitter segment, the forward most first stator and the forward most second stator being formed as a single, integrally formed structure, the forward most first stator positioned closer to the forward end relative to a distance between the forward most second stator and the forward end and the forward most second stator positioned closer to the rearward end relative to a distance between the forward most first stator and the rearward end, wherein the splitter segment defines a radially outward boundary of the second, radially inner stream such that an outer tip of a rotor passes in close proximity to the splitter segment at the radially outward boundary of the second, radially inner stream defined by the splitter segment; and a sacrificial rub layer located within a pocket formed in a radially inner surface of the splitter segment that faces the outer tip of the rotor at the radially outward boundary of the second, radially inner stream defined by the splitter segment.

Stator configuration for gas turbine engine

A stator configuration for a gas turbine engine including: a splitter segment, the splitter segment extending from a forward end to a rearward end; a forward most first stator extending radially outwardly from the splitter segment, the forward most first stator being completely located downstream from the forward end of the splitter segment; and a forward most second stator extending radially inwardly from the splitter segment, the splitter segment, the forward most first stator and the forward most second stator being formed as a single, integrally formed structure, the forward most first stator positioned closer to the forward end relative to a distance between the forward most second stator and the forward end and the forward most second stator positioned closer to the rearward end relative to a distance between the forward most first stator and the rearward end.

A stator configuration for a gas turbine engine including a splitter segment. Also included is a first stator extending radially outwardly from the splitter segment. Further included is a second stator extending radially inwardly from the splitter segment, the splitter segment, the first stator and the second stator being a single, integrally formed structure.

A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.

Integral half vane, ringcase, and id shroud

An inlet section for a gas turbine engine according to an example of the present disclosure includes, among other things, an outer case extending about a rotor that is rotatable about an engine axis. The rotor carries a plurality of airfoils. A plurality of guide vanes are operable to guide flow from an engine inlet toward the plurality of airfoils relative to the engine axis. A plurality of spokes are mechanically attached to the outer case. Each of the plurality of spokes is received in a respective one of the plurality of guide vanes, and at least one of the plurality of spokes define a fluid passage in flow communication with a bearing assembly.

Guide vane arrangement for gas turbine engine

Airfoils () are molded of material (), such as silicon rubber, which is fluent during molding, becoming solid and compliant at temperatures of use, with rigidly fixed vanes () and rotatable vanes (), as inserts which are co-molded within the airfoil. The inserts are pre-prepared of either stiff or semi-stiff material to suit the intended needs of the airfoil. Then, with inserts in place within a mold, the airfoil is molded of compliant material. At least one of the inserts () is rotatable so as to force at least some portion of the compliant airfoil to alter camber, the compliant material between the inserts smoothing out the surface of the airfoil. The airfoils thus molded are then inserted between the inner hub () and the outer ring () of the rotary machine in which a fan or compressor is being constructed. Rods of the movable vanes extend to a unison ring connected () to rotate the vanes.

Rigid and rotatable vanes molded within variably shaped flexible airfoils

The present disclosure relates generally to a guide vane assembly including a first airfoil, including a first airfoil trailing edge, a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween, and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge.

Seal assembly for a guide vane assembly

A seal is positioned radially outwardly of a compressor blade. The seal has a seal hook facing in a downstream direction. A seal mount has a mount hook for receiving the seal hook in a gap. The hook face in an upstream direction. The seal mount has an upstream portion extending from an upstream end into the gap. The mount hook extends into a web which extends in a downstream direction. A thermal barrier coating on the upstream portion of the seal mount extends to a downstream end. There is a thermal barrier coating on a radially inner surface of the mount hook, and along the web to a downstream coating end. An upstream end of the coating on the inner surface of the hook being formed axially upstream of the downstream end of the coating on the upstream portion.

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East Hampton, CT, United States of America

Michael C Firnhaber