General Electric Company

Thomas Ryan Wallace

Scott Alan Schimmels

Richard William Albrecht, Jr

Mark Willard Marusko

Kevin Samuel Klasing

Travis J Packer

Richard William Jendrix

Michael Alan Hile

Brandon Flowers Powell

Bradford Alan Tracey

Kenneth Jay Moore

James Hamilton Grooms, Iii

John Michael Cadman

Benjamin Johannes Seppala

Anthony Joseph Venzon

Randy Joseph Tobe

Robyn E Brands

David Fasig

Brian Matthias Schaldach

A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.

Clearance control assembly

A gas turbine engine having a fluid transfer connection is provided. The gas turbine engine includes a first component configured to channel a flow of air from a portion of the gas turbine engine; a second component configured to receive the flow of air from the first component, wherein the first component and the second component are movable relative to one another; a sleeve portion disposed between the first component and the second component; and a spoolie device disposed within the sleeve portion, the spoolie device having elliptical shaped opposing ends, wherein the spoolie device bridges the first component and the second component to channel the flow of air from the first component to the second component.

Gas turbine engine with spoolie fluid transfer connection

A fuel nozzle configured to channel fluid towards a combustion chamber is provided. The fuel nozzle includes a stem having a central passageway and at least one fuel tube disposed within the passageway. The fuel tube includes an outlet end portion having inner and outer walls separated by a cavity defined by a fixed aft face. The inner wall defines a central bore for delivering fuel to the combustion chamber. Further, the fuel nozzle includes an outer heat shield tube concentrically aligned with the outlet end portion of the fuel tube. The heat shield tube includes a circumferential outer wall having an aft face that stops upstream of the fixed aft face of the fuel tube. Thus, during operation, the heat shield tube is configured to thermally expand by sliding against the outer wall of the fuel tube.

Fuel nozzle for gas turbine engine

A clearance control apparatus for a gas turbine engine including an annular turbine case having opposed inner and outer surfaces; an annular manifold surrounding a portion of the turbine case, the manifold including: an inlet port in fluid communication with the manifold and the outer surface of the turbine case, and an exit port; and a bypass pipe having an upstream end coupled to the exit port, a downstream end coupled to a low-pressure sink, and a valve disposed between upstream and downstream ends, the valve selectively moveable between a first position which blocks flow between the upstream and downstream ends, and a second position which permits flow between the upstream and downstream ends.

Suction-based active clearance control system

A damper which, in one form, includes a damper ring having inner and outer radial surfaces, axial retainers extending radially outward from the outer radial surface, and an annular stiffener protruding radially inward from the inner radial surface, is described. The axial retainers prevent disengagement of the damper ring from the structural member. The stiffener adds mass to the damper ring such that the radial distance of the neutral axis of the damper ring from the neutral axis of the structural member is increased, thus increasing damping effectiveness. The stiffener also adds torsional and bending rigidity to the damper ring so that the damper ring is further prevented from disengaging from the structural member.

Vibration damper for a turbine engine

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Cincinnati, OH, United States of America

Thomas Ryan Wallace