Solar Turbines Incorporated

A fuel injector includes a swirl pot including an outer body defining a swirling chamber having a longitudinal axis. The fuel injector also includes a swirler core disposed within the swirling chamber substantially concentric with the longitudinal axis and together with the outer body defining at least one swirl path within the swirl chamber. The swirler core is a unitary body separate and distinct from the outer body.

A method and system for detecting degradation of a lube oil temperature control valve in a gas turbine engine. The system includes temperature sensors measuring lube oil tank temperature, heat exchanger outlet temperature, and header temperature downstream of the temperature control valve. Valve position is determined based on temperature measurements and extracted contextual features describing operating conditions. The system determines valve degradation by comparing valve positions to expected positions, analyzing seasonal variations, and detecting deviations from baseline operation. The system predicts potential valve failures before peak ambient temperature periods based on detected degradation rates and historical patterns. Preventative maintenance notifications are generated with recommended timing based on the predicted valve failure timeline.

A resonator and related methods are described herein. The resonator includes a body having a front surface and a rear surface. The body defines a first chamber and a second chamber. The first chamber is configured such that fluid within the first chamber resonates at a first frequency. The second chamber is configured such that fluid within the second chamber resonates at a second frequency that is different from the first frequency. The body further defines an inlet hole and an outlet hole. The inlet hole extends from the front surface toward the rear surface to one of the first chamber and the second chamber. The outlet hole extends from the rear surface towards the front surface to one of the first chamber and the second chamber. The body is configured to be connected to a dome or liner of a combustion system.

In one instance, disclosed herein is an interchanging drive train system for driving a compressor comprising: an interchanging gearbox coupled to the compressor; a gas turbine selectively coupled to the interchanging gearbox via a first coupling mechanism; and an electric motor selectively coupled to the interchanging gearbox via a second coupling mechanism, wherein the interchanging gearbox is configured to allow the compressor to be interchangeably driven by the gas turbine and the electric motor.

An injector head for a fuel injector of an engine includes an injector body configured to be coupled with a fuel stem of the fuel injector. The injector body extends orthogonally relative to the fuel stem. The injector body extends axially along a central axis and circumferentially about the central axis. The injector head also includes a central fuel assembly. The central fuel assembly includes a tip portion disposed proximal to a downstream end of the injector body. The tip portion includes an end portion, an intermediate portion, a plurality of support pins extending between the end portion and the intermediate portion, and a plurality of fins extending radially-outward and from the intermediate portion along the central axis. The injector head is formed by additive layer manufacturing. The plurality of support pins and the plurality of fins provide support for forming the injector head by additive layer manufacturing.

During operation of a gas turbine engine, the airfoils of turbine blades are exposed to very high temperatures. Embodiments of a turbine blade may comprise an outer cooling channel, which supplies coolant to the leading edge and tip of the airfoil, and wraps around inner cooling channel(s), which supply coolant to the middle of the airfoil. These outer and inner cooling channels may merge in a merge channel with an aft cooling channel that supplies coolant to the trailing edge and tip of the airfoil. In an embodiment, discrete pressure-side and suction-side inner cooling channels may provide a flow path for coolant in opposing directions to thereby reduce temperature gradients within the airfoil. Embodiments may also comprise other cooling features, including cooling holes, trip strips, and/or pins.

A method for detecting errors in temperature readings at a section of a gas turbine engine is described. The method includes obtaining a plurality of first average temperatures and a plurality of second average temperatures respectively from a first module and a second module for multiple time intervals. The method further includes determining a drift in values of one of the plurality of first average temperatures and the plurality of second average temperatures in comparison to corresponding values of the other of the plurality of first average temperatures and the plurality of second average temperatures over the multiple time intervals to detect that one of the first module or the second module is erroneous.

Large industrial machines, such as gas turbine engines, typically have a control room or control panel, acting as a single local control point from which the machine is operated. However, this prevents technicians from controlling the machine at locations that are distant from the control point, as may be necessary during servicing or operation. Accordingly, a system is disclosed that enables a wireless human-machine interface to be used to control the machine, in addition to a local human-machine interface. The system may ensure that only a single human-machine interface is able to control the machine at any given time, as well as prevent unauthorized devices from controlling the machine.

A system for delivering a fuel to a gas turbine engine, having a combustor defining first zones (located proximal to the ignition source of the gas turbine engine) and second zones (located distal from the ignition source), and a plurality of injectors circumferentially arranged about the combustor, is disclosed. The system includes a start fuel circuit and a main fuel circuit. The start fuel circuit is fluidly coupled to first injectors of the plurality of injectors to facilitate injection of a first quantity of the fuel by the first injectors into the first zones upon activation of the ignition source. The main fuel circuit is fluidly coupled to second injectors of the plurality of injectors to facilitate injection of a second quantity of the fuel by the second injectors into the second zones in response to a light-off of the first quantity of the fuel.

A vane assembly for directing airflow through an elbow section of an air duct associated with a gas turbine engine includes a plurality of first vanes and at least two second vanes intersecting the plurality of first vanes. Each first vane includes a first plate and a first vibration inhibition device. An upstream end of the first plate is coupled to the first vibration inhibition device. The first plate has a first thickness and the first vibration inhibition device has a first dimension that is greater than the first thickness. Each second vane includes a second plate and a second vibration inhibition device. An upstream end of the second plate is coupled to the second vibration inhibition device. The second plate has a second thickness and the second vibration inhibition device has a second dimension that is greater than the second thickness.