United Technologies Corporation

Jeffrey D Melman

Jun Shi

Richard Sterling Tuthill

David J Bombara

Jason Lawrence

David C Jarmon

Jonathan Jeffery Eastwood

Monica Pacheco-Tougas

John J Korzendorfer

Alan J Goetschius

Aaron S Butler

Craig F Smith

Claude I Barnett

Dennis John Duhamel

Hannes A Alholm

David A Burns

Albert Veninger

Eric Herbst

David R Wiley

Randy J Danburg

Michael T Weber

Christine Blanchard

Richard S Tuthill

A combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween. An air fuel mixer and an igniter are mounted to the support assembly secured to the ceramic combustion can which receives the ignition products of the ignited fuel and air mixture.

Ceramic combustor can for a gas turbine engine

A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.

Gas turbine combustor liner cap assembly

A combustion system for an engine, such as a gas turbine engine is provided. The combustion system has a ceramic component, such as ceramic combustor liner, and at least one metal support component, such as a metal ring or a plurality of metal cones, for providing radial and axial support to the ceramic component. The at least one metal support component includes a structure, such as axial slots or radial slots, for minimizing stress and for increasing compliance of the metal support component with respect to the ceramic component.

Compliant metal support for ceramic combustor liner in a gas turbine engine

A method of repairing a turbine exhaust case strut heat shield vane includes removing a damaged portion of the vane, solution heat treating the vane, attaching a replacement section to the vane, and relieving local stresses in an attachment area between the replacement section and the vane.

Repaired turbine exhaust strut heat shield vanes and repair methods

A combustor assembly includes a metal section having an axial slot that receives a ceramic section. A clamp is received about the axial slot to secure the metal section and ceramic section together. Tabs on the metal section, a gasket between the metal section and the ceramic section, and springs within the clamp deform an amount that is greater than a thermal expansion difference between the metal section and the ceramic section to maintain a clamping force of the clamp.

Attachment of a ceramic combustor can

A premixing, tangential entry fuel injector (10) for a gas turbine engine features a secondary fuel-air injection insert (40) positively secured to a centerbody shell (38) by a braze joint (98). A secondary fuel supply tube (42), positively secured to both a centerbody base (36) and to the insert (40), is curved in at least two dimensions. In an exemplary embodiment, the tube is coiled into a spiral shape covering a single 360.degree. cycle. During engine operation, the centerbody expands axially in response to elevated temperatures in the engine's interior, causing the insert (40) to be displaced away from the base (36). The curvature of the tube allows the tube to flex slightly to accommodate the displacement. Ideally the curvature of the tube is such that the tube's natural frequency is well above the maximum vibratory frequency that the tube will experience during engine operation.

Premixing fuel injector with improved secondary fuel-air injection

A vibration damper 38 for a fuel nozzle 24 having a central axis about which are disposed an inner 34 and outer 36 concentric fuel tubes. The damper includes a sleeve 40 and at least two legs 42, each leg having a radial portion extending from the sleeve and a resilient, longitudinally extending portion 46. The sleeve engages the inner tube while the longitudinally extending portions of the legs bear against the inner surface 37 of the outer tube to dampen vibrations between the concentric tubes. Besides damping objectionable vibratory forces experienced by the fuel tubes in the fuel nozzle, the present invention offers minimal fuel flow blockage in the concentric fuel tubes.

Vibration damper for a fuel nozzle of a gas turbine engine

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Simsbury, CT, United States of America

Jeffrey D Melman