United Technologies Corporation

Raytheon Technologies Corporation

Royce E Tatton

Matthew A Turner

Kristin V Wood

Matthew R Satterwhite

George Alan Salisbury

Kristin Wood

Matthew Satterwhite

A platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, a connector configured to receive a pin and secure the platform to a rotor of the gas turbine engine, and a sidewall extending from the top wall to the connector, the sidewall having a first arm and a second arm, wherein the first arm and the second arm are curved such at a bowed sidewall extends from the top wall to the connector.

Platform for an airfoil having bowed sidewalls

A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.

Fan platform with stiffening feature

A platform for an airfoil in a gas turbine engine is provided. The platform includes a top wall configured to connect to an airfoil of the gas turbine engine, two sidewalls extending downward from the top wall a connector attached to and connecting the two sidewalls, wherein the top wall, the sidewalls, and the connector define an interior volume of the platform, and a single stiffener extending from the connector to the top wall within the interior volume between the two sidewalls. The connector defines two parallel apertures passing through the connector.

Airfoil platform having dual pin apertures and a vertical stiffener

A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.

Fan blade root integrated sealing solution

A fan section for a gas turbine engine is provided. The fan section having a fan hub with a slot and a fan blade with an airfoil extending from a root to a tip, the airfoil having a leading edge and the root is received in the slot, wherein a first platform is secured to the fan hub and arranged between adjacent fan blades of the fan section, the first platform having a first platform seal including a platform seal leading edge and a base is secured to a side of the first platform and a first winglet extends from the platform seal leading edge and contacts the airfoil leading edge.

Fan blade platform seal with leading edge winglet

An electrical connector includes an electrically insulating body having a base mating surface and a stepped mating surface offset from the base mating surface. The electrical connector either has first and second electrically conducting pins extending from the base and stepped mating surfaces, respectively, or has first and second electrically conducting sockets extending from an interior portion of the electrically insulating body to the base and stepped mating surfaces, respectively.

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Blackfoot, ID, United States of America

Royce E Tatton