Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

David M Dyer

Michael Ronan

Scott Gammons

Matthew E Bintz

Mark E Simonds

John P Tirone

Michael C Firnhaber

Kevin Knechtel

Zachary J Jeske

A gas turbine engine includes a case, a stator vane, and a retainer. The case has a first surface, a second surface, a third surface extending between the first surface and the second surface, and a hook extending from the second surface and disposed opposite the third surface. The stator vane includes a shroud body and a first flange. The retainer is arranged to seat the first flange within a first slot defined between the hook and the second surface and secure the shroud body to the case.

Fixed vane pack retaining ring

A vane assembly includes a fixed airfoil portion that extends between a radially inner platform and radially outer platform and has a pressure side and a suction side. A rotatable airfoil portion is located aft of the fixed airfoil portion and has a pressure side and a suction side. A cover extends from the pressure side of the fixed airfoil portion to the pressure side of the rotatable airfoil portion.

Cover for airfoil assembly for a gas turbine engine

A vane assembly includes a rotatable airfoil that extends between a radially inner platform and a radially outer platform and has a leading edge and a trailing edge. A thrust projection is fixed relative to the rotatable airfoil. The thrust projection includes a first thrust surface for supporting radial loads in a first radial direction and a second thrust surface for supporting radial loads in a second direction.

Airfoil assembly for a gas turbine engine

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

A variable vane adjustment system for a gas turbine engine including: a vane platform having a recess, a vane opening within the recess, and a set screw opening originating at a first wall of the recess and extending into the vane platform; a trunnion carrier having a base portion located at least partially within the recess, a bushing attached to the base portion, and an orifice that extends through the base portion and bushing, wherein the orifice is aligned with the vane opening; a variable vane having a vane stem, the vane stem extending through the vane opening and the orifice; and a set screw located at least partially within the set screw opening, the set screw being configured to longitudinally traverse the set screw opening as the set screw is rotated, wherein the set screw is configured to move the trunnion carrier and variable vane.

Growing community of inventors

Glastonbury, CT, United States of America

David M Dyer