United Technologies Corporation

Raytheon Technologies Corporation

Andrew G Alarcon

William Bogue

Matthew A Turner

James Glaspey

Charles W Brown

Christopher M Quinn

Shari L Bugaj

Barry M Ford

Charles R Watson

Renee J Jurek

David J Hyland

Brian Green

Renee J Behlman

In a featured embodiment, a fan rotor includes a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.

Fan blade platform spacer mounting

A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.

Contoured flowpath surface

A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed.

Fan platform with leading edge tab

Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.

T-shaped platform leading edge anti-rotation tabs

A seal for sealing a gap between adjacent first and second components, includes a first portion for attaching to the first component and a second portion extending at an angle from the first portion, the second portion having a top extending therealong that is flat in an uninstalled position, a thickened portion beneath the top and a hinge wherein the thickened portion is disposed between the hinge and an end of the top.

Fan blade platform flap seal

A fairing assembly includes an outer wall, a first side wall, a second side wall, and a saddle. The first side wall and the second side wall extend from opposing sides of the outer wall. Together the first side wall, the second side wall, and the outer wall form a cavity within the fairing assembly. The saddle is positioned within the cavity and extends between the first side wall and the second side wall. The saddle has a first rib adapted to connect to the first side wall and a second rib adapted to connect to the second side wall. The first rib and the second rib connect together at a central hub.

Fairing assembly

An anti-torsion assembly for positioning and securing a thermally conforming liner within a fan containment case is provided. The anti-torsion assembly minimizes the amount of machining that must be done prior to assembly. The anti-torsion assembly comprises a torque block with outwardly-opposing side surfaces and a pair of L-brackets. Each L-bracket has a bracket surface that faces one of the outwardly-opposing side surfaces of the torque block. A wear pad is affixed to each bracket surface. The L-brackets are positioned onto the thermally conforming liner using a spacer having a spacer width within a predetermined tolerance. A method of assembling a fan case assembly is also provided.

Growing community of inventors

Manchester, CT, United States of America

Andrew G Alarcon