Solar Turbines Inc.

Bruno Enriquez Struck

Alexander Ilich Krichever

Jonathan C Wilson

Robert F Corr

Hyun Dong Kim

Edward William Sieveking

John Preston Montague

Robert Anthony Corr, Ii

Kenneth Gregory Thomas

Peter Sykes

Peter Barker

Vu Phi

Jack Harvey Cabeen

Timothy James Caron

Eugene R Hicks

Frederick B Lorenz

Richard Braeutigam

Danny Gauce

Brian J Taylor

Rodolfo G Alonte

Eduardo Bravo

John S Bowen

Manuel Estevez, Iii

A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder. The controller obtains a sensor value from a sensor connected to the gas turbine engine and publishes a tag that includes the type of event, the sensor value, and a timestamp. The high speed recorder checks the tag for an overspeed event. If an overspeed event is detected, the high speed recorder records values provided by the tag.

Method of monitoring a gas turbine engine to detect overspeed events and record related data

A flanged component for a gas turbine engine is disclosed herein. The flanged component includes a flange body with a flange mating surface and a plurality of threaded features. Each threaded feature includes a threaded portion and a relief portion. The threaded portion has threads and extends into the flange body from the flange mating surface. The relief portion extends into the flange body from the flange mating surface located outward from the threaded portion forming a rim portion therebetween. The rim portion includes an upper rim surface having an annular shape. The relief portion includes an inner surface extending from the rim and tapering outward from the upper rim surface.

Flanged component for a gas turbine engine

A sensor assembly for a gas turbine engine is disclosed. The sensor assembly includes a bushing and a probe. The probe includes a body, an anti-vortex tip, and a tip end. The body extends from the bushing and includes a body surface. The body surface is a right circular cylinder with a first diameter. The anti-vortex tip extends from the body and includes an anti-vortex tip surface. The anti-vortex tip surface is a conical surface extending from the body surface to a second diameter at a taper angle from fourteen degrees to sixteen degrees. The tip end extends with a spherical shape from the anti-vortex tip.

Thermocouple with a vortex reducing probe

A system and method for aligning a gas turbine engine. The system and method includes installing an alignment mount, determining whether the gas turbine engine is aligned and/or in a sufficiently aligned condition, and modifying a vertical position of the gas turbine engine at the alignment mount in response. The alignment mount includes an engine attachment, a ground attachment, and an expansion member configured to allow the engine attachment and the ground attachment to move relative to each other and maintain a load path therebetween.

System and method for aligning a gas turbine engine

An air blocker ring assembly including a proximal end and a distal end, a blocker ring, and a blocker ring support cooperating with the blocker ring to form a circumferentially extending split line at an interface between the blocker ring and the blocker ring support. The proximal end of the proximal ring assembly has a circumferential leading edge, and the circumferentially extending split line is located at least one of radially inside or radially outside the leading edge.

Air blocker ring assembly with leading edge configuration

An air blocker ring assembly includes a proximal end, a distal end, a blocker ring, and a blocker ring support. The blocker ring has a first protrusion, a second protrusion, and a third protrusion. The blocker ring support has a recess. The first protrusion of the blacker ring is received in the recess. The blocker ring is circumferentially discontinuous about a circumferential slot. At least a portion of the first protrusion is located circumferentially opposite the slot, and the second and third protrusions terminate at the slot.

Air blocker ring assembly with blocker ring protrusions

A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor. The premix barrel may include a first portion at the upstream end and a second portion at the downstream end. The first portion may include a stainless steel material, and the second portion may include a nickel based superalloy material. The second portion may be coupled to the first portion by a laser clad coupling.

Laser clad fuel injector premix barrel

A fluid line clamp includes one or more blocks with holes for receiving fluid lines therein. The fluid line clamp further includes a first backing plate, a second backing plate, and a shielding plate. The first and second backing plates are spaced apart from each other to receive the blocks therebetween. The shielding plate is disposed at a distance from the blocks and includes an inner surface, and an outer surface. The inner surface of the shielding plate is rigidly attached to the backing plates. The outer surface of the shielding plate is configured to rigidly attach to a hot body of a machine.

Fluid line clamp

A combustor liner may include an annular inner liner and an annular outer liner with a plurality of air holes thereon. The outer liner may be positioned circumferentially around the inner liner such that an annular cooling space is defined between the inner and the outer liner. The combustor liner may also include at least one resonator coupled to the outer liner such that a base of the resonator is separated from the outer liner to form a gap with an external surface of the outer liner. The combustor liner may also include a throat extending from the base of the resonator penetrating the inner liner and the outer liner. The combustor liner may further include a grommet assembly that allows for relative thermal expansion between the inner liner and the outer liner proximate the throat.

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San Diego, CA, United States of America

Bruno Enriquez Struck