General Electric Company

David Allen Kastrup

Gilbert Farmer

Marie Ann McMasters

Jeffrey Arnold Fehrenbach

William Lee Imhoff

Stephen Charles Furbish

Bangalore Aswatha Nagaraj

Timothy James Held

David Edwin Budinger

Craig Douglas Young

Roger C Walker

Raymond William Heidorn

Douglas Marti Fortuna

Ronald Lance Galley

Thomas John Tomlinson

Eva Zielonka Lanman

David L Joyce

Deborah Anne Schorr

Scott P Reese

Ashwin Sreekant Raghavan

Deborah A Schorr

A direct metal laser sintered material including a substrate formed from a laser sintering process, the substrate having at least one surface, and a cladding material brazed onto at least a portion of the surface.

Blaze cladding for direct metal laser sintered materials

A mixer having a unitary construction is disclosed comprising an annular housing having an axis and at least a first swirler having a plurality of vanes arranged circumferentially around the axis such that circumferentially adjacent vanes form at least one flow passage that is oriented at least partially in an axial direction with respect to the axis. In another exemplary embodiment, a mixer having a unitary construction is disclosed comprising a swirler having a plurality of radial vanes arranged circumferentially around the axis and oriented at least partially in a radial direction.

Mixer for a combustor

A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section is defined between each adjacent opening; and, a mixer assembly located upstream of and in substantial alignment with each of the openings in the dome plate, with the mixer assembly including a forward portion and an aft portion. Each mixer assembly is retained in a manner so as to be movable in a radial and axial direction without obstructing the radial sections of the dome plate. A first pair of tabs are positioned on the forward surface of the dome plate adjacent each opening and a second pair of tabs are positioned on the aft portion of each mixer assembly, wherein the dome plate tabs interface with the mixer assembly tabs to prevent rotation of each mixer assembly.

Free floating mixer assembly for combustor of a gas turbine engine

A method for assembling a gas turbine engine combustor facilitates reducing costs and time required for assembly. The combustor includes a spectacle plate, a plurality of swirlers, and a plurality of deflector plates. The method includes coupling an assembly fixture to at least one swirler, coupling the assembly fixture to the spectacle plate such that the swirler is maintained in alignment with respect to the spectacle plate during assembly of the combustor, and attaching the swirler to the spectacle plate.

Apparatus for assembling gas turbine engine combustors

A method applying a thermal barrier coating to a metal substrate, or for repairing a thermal barrier coating previously applied by physical vapor deposition to an underlying aluminide diffusion coating that overlays the metal substrate. The aluminide diffusion coating is treated to make it more receptive to adherence of a plasma spray-applied overlay alloy bond coat layer. An overlay alloy bond coat material is then plasma sprayed on the treated aluminide diffusion coating to form an overlay alloy bond coat layer. A ceramic thermal barrier coating material is plasma sprayed on the overlay alloy bond coat layer to form the thermal barrier coating. In the repair embodiment of this method, the physical vapor deposition-applied thermal barrier coating is initially removed from the underlying aluminide diffusion coating.

Method for applying or repairing thermal barrier coatings

A method enables a gas turbine engine to be assembled. The method comprises coupling a fuel nozzle within the engine to inject fuel into the engine, wherein the fuel nozzle includes three independent injection circuits arranged such that the second injection circuit is between the first and third injection circuits, coupling a liquid fuel source to a first injection circuit defined within the nozzle and including an annular discharge opening, and coupling a water source to one of the second injection circuit and the third injection circuits such that the water source is coupled in flow communication to an annular discharge opening.

Methods and apparatus for reducing gas turbine engine emissions

A method of stripping coating from a portion of a coated surface of a component. The method includes fastening a mask sheet to the component over a region adjacent the portion of the coated surface. The mask sheet has a contour generally corresponding to a contour of the surface of the component. A high pressure fluid jet is sprayed from a spray head toward the portion of the coated surface after the mask sheet is fastened to the component to strip the coating from the portion of the surface. After the coating is stripped from the portion of the surface, the mask sheet is removed from the component.

Apparatus for stripping coating

Methods for assembling gas turbine engine combustors

Method and apparatus for stripping coating

The invention concerns an active clearance control for controlling clearance between a turbine and a casing in a gas turbine aircraft engine. The invention calculates the instantaneous clearance between a turbine casing and a turbine rotor, based on temperature. Two temperatures are involved. First, a steady state temperature (SSTemp) is computed for the rotor and the casing. SSTemp is a predicted, future temperature, which will be attained when the engine reaches steady state operation. Each SSTemp is computed based on presently occurring engine operating conditions, such as selected temperatures, pressures, and rotational speeds. Changes which occur in the SSTemp's indicate the second temperatures, which are the instantaneous temperatures of the casing and rotor. These changes in SSTemp are caused by changes in the present operating conditions, which occur during engine acceleration and deceleration. The instantaneous temperatures indicate the diameters of the casing and the rotor, and thus the instantaneous clearance between them. In another form of the invention, the computed instantaneous clearance is used to control air which is bled from the fan and ducted onto the casing, in order to attain a desired clearance.

Active clearance control for gas turbine engine

Growing community of inventors

West Chester, OH, United States of America

David Allen Kastrup