Abstract: A system for vibration damping a fuel nozzle within a combustor includes a support plate, a fuel nozzle passage that extends through the support plate and a cylindrical damping insert that is coaxially aligned within the fuel nozzle passage and at least partially defines the fuel nozzle passage. The damping insert may include a metallic-mesh liner.

Abstract: A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes a platform portion that is disposed radially between the mounting portion and the airfoil. The platform portion includes a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls. A cooling plenum that at least partially defines the cooling circuit is defined within the platform portion. The cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls.

Abstract: A process of depositing a ceramic coating on an airfoil component and the component formed thereby is provided. The process includes depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes. A ceramic coating is then deposited on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes. The ceramic coating within the holes is selectively removed without completely removing the ceramic coating on the trailing edge region and the lands between the holes.

Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.

Abstract: A system includes a controller including a processor configured to execute a program stored in a memory of the controller to generate and transmit a first output comprising a total flow demand value to a plurality of valves communicatively coupled to the controller. Each of the plurality of valves is configured to receive a respective portion of the total flow demand value. The processor is configured to receive an input indicative of a decoupling of a first valve of the plurality of valves and to generate a second output based at least in part on the first output and a first operational characteristic of the first valve. The second output is configured to vary a second operational characteristic of a second valve of the plurality of valves to maintain the total flow demand value.

Abstract: Ultrasonic detection methods are disclosed. The method includes providing an ultrasonic detection system having a transmitting phased array device and a receiving phased array device. A phased array wave is transmitted through a revolutionary body from the transmitting phased array device to the receiving phased array device, thereby obtaining ultrasonic detection information about the revolutionary body. In another embodiment, the method includes positioning the transmitting phased array device and the receiving phased array device on a periphery of a turbine rotor, transmitting a phased array wave into the turbine rotor, the phased array wave not reflecting off of a reflecting feature, adjusting the positioning of the transmitting phased array devices on the periphery of the turbine rotor, and transmitting the phased array wave into the turbine rotor, the phased array wave reflecting off of a reflecting feature. The reflected phased array wave is received by the receiving phased array device.

Abstract: Articles for use at high temperatures, for example as gas turbine engine components, are described. The article includes a substrate and a coating disposed over the substrate. The coating includes a silicate phase that has a composition in accordance with the formula (A(1-x)Dx)2Si2O7, where x is a number at least 0.03 and up to 1; wherein A includes yttrium and D includes a Group 13 element, such as indium, gallium, and/or aluminum. Various combinations of other coatings may be included with the silicate-containing coating to enhance protection.

Abstract: A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple fuel injectors. Each fuel injector is configured to extend into a respective premixing tube of a plurality of mixing tubes. Each fuel injector includes a body, a fuel passage, and multiple fuel ports. The fuel passage is disposed within the body and extends in a longitudinal direction within a portion of the body. The multiple fuel ports are disposed along the portion of the body and coupled to the fuel passage. A space is disposed between the portion of the body with the fuel ports and the respective premixing tube.

Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.

Abstract: A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid circuit extends at least partially through the main body. An axially extending inner body extends within the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid circuit. A retractable igniter extends linearly outward from the inner chamber when the fluid circuit is charged.

Abstract: A sealing member, a component including a sealing member, and a method of sealing a hole are disclosed. In an embodiment, the sealing member includes a plug member for occluding a hole in a wall of a passageway. The plug member includes at least one cooling feature disposed on a distal end of the plug member exposed to the passageway.

Abstract: A system is provided with a utility meter. The utility meter includes a memory storing a table, wherein the table specifies modifiable data that may be modified when the utility meter is sealed and non-modifiable data that may not be modified when the utility meter is sealed. The utility meter also includes a processing device configured to access the table stored on the memory or another memory to determine whether specific data stored on the memory or another memory may be modified when the utility meter is sealed.

Abstract: The present disclosure provides a method for improving the performance of a membrane for use in a membrane distillation process, and a membrane produced by the method. The method includes subjecting the membrane to a pressure difference across the membrane in order to open closed pores in the membrane.

Abstract: A method for the assisted manipulation of an instrument in an assistive assembly for instrument manipulation, comprising: a medical imaging system comprising a support to immobilize at least one part of a patient intended to be imaged or already imaged by said system, an assistive device for assisted manipulation of an instrument intended to be used in said patient, said device comprising: a mobile mechanical structure operable by an operator, on which at least one instrument can be fixed, said method being characterized in that it comprises the step to calibrate the position of the assistive device relative to the position of the imaging system, thereby allowing the position of the patient part to be known within a reference frame related to the assistive device, to assist the operator in manipulating the instrument in the patient.

Abstract: A casting method, cast article and casting system are disclosed. The casting method includes providing a base material in a mold, directing a fluid material into the mold, and solidifying the base material and the fluid material to form a cast article. The base material has a first density and first composition. The fluid material has a second density and a second composition. The first density differs from the second density, the first composition differs from the second composition, or the first density differs from the second density and the first composition differs from the second composition. The cast article includes a first material solidification from the base material, and a second material solidification from the fluid material. The casting system includes a mold for containing a base material and an input configuration, with flow control feature, for directing a fluid material into the mold containing the base material.

Abstract: A core tie having a varying cross sectional diameter, a component including such a core tie, and a method of casting a hot gas path component for a turbomachine are provided herein. In an embodiment, the core tie includes a tie member having an axial length; and a cross sectional diameter which varies along the axial length of the tie member. A variation in the cross sectional diameter of the tie member positively secures a position of the core tie relative to the core.

Abstract: A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple tubes. Each tube includes a first end, a second end, and an annular wall disposed about a central passage. The first end is configured to be disposed about a fuel injector. Each tube also includes an air flow conditioner having multiple air ports disposed adjacent the first end. The multiple air ports extend through the wall into the central passage.

Abstract: Methods for modifying a turbine buckets include removing at least an original outer edge for an entire length of the slash face of the turbine bucket and adding a new material to the slash face to build a new outer edge, wherein the new outer edge extends the entire length of the slash face.

Abstract: A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple mixing tubes. Each mixing tube includes an annular wall disposed about a central passage and an air inlet region configured to be disposed about a fuel injector extending into the central passage. The central passage extends from an upstream end to a downstream end of the annular wall relative to a direction of flow through the central passage. The air inlet region includes an air entry surface of the annular wall that gradually decreases in diameter in the direction of flow.

Abstract: A component includes magnet elements adjoined to each other to form an arced segmented magnet section that is configured to fit in an a curved rotor slot gap of an electric machine. An electric machine that employs the component and method of assembly of the component are also disclosed. The present invention has been described in terms of specific embodiment(s), and it is recognized that equivalents, alternatives, and modifications, aside from those expressly stated, are possible and within the scope of the appending claims.