Abstract: An instrumented component (18, 19) for use in various operating environments such as within a combustion turbine engine (10). The component (18, 19) may have a substrate, a sensor (50, 94, 134) connected with the substrate for sensing a condition of the component (18, 19) during operation of the combustion turbine (10) and a connector (52, 92, 140) attached to the substrate and in communication with the sensor (50, 94, 134) for routing a data signal from the sensor (50, 94, 134) to a termination location (53). The component (18, 19) may include a wireless telemetry device (54, 76, 96) in communication with the connector (52, 92, 140) for wirelessly transmitting the data signal. Recesses (114, 116) may be formed with a root portion (112, 132) of components (18, 19) within which wireless telemetry device (54, 76, 96) may be affixed.

Abstract: An instrumented component (18, 19) for use in various operating environments such as the hot gas path section of a combustion turbine engine (10). The component (18, 19) may have a substrate, a sensor (50, 204, 210) connected with the substrate for sensing a condition of the component (18, 19) within the casing during operation of the combustion turbine (10) and a connector (52, 202) attached to the substrate and in communication with the sensor (50, 204, 210) for routing a data signal from the sensor (50, 204, 210) to a termination location (53). The component (18, 19) may include a wireless telemetry device (54, 202) in communication with the connector (52, 202) for wirelessly transmitting the data signal outside the casing. A transceiver (56) may be located outside the casing for receiving the data signal and transmitting it to a processing module (30) for developing information with respect to a condition of the component (18, 19) or a coating (26) deposited on the component (18, 19).

Abstract: The present invention discloses the procedure for obtaining complete spectrum of the Nadi pulses, as a time series and capable of detecting the major types and the subtypes of the Nadi pulses. The device of this invention involves three diaphragm elements equipped with strain gauge, three transmitters cum amplifiers, and a digitizer for quantifying analog signal. The system acquires the data with 12-bit accuracy with practically no electronic and/or external interfering noise. The pertaining proofs are given which clearly shows the capability of delivering the accurate spectrums, with repeatability of the pulses from the invented system. ‘Nadi-Nidan’ is a prominent method in Ayurveda (Ayurveda is a Sanskrit word derived from ‘Ayus’ and ‘vid’, meaning life and knowledge respectively. It is a holistic science encompassing mental, physical and spiritual health), which is known to dictate all the salient features of a human body.

Abstract: An integrated, self-powered, sensing and transmitting module (300) that can be placed within an operating environment, such as by being affixed to a gas turbine engine component, in order to sense the local operating environment and to deliver real-time operating environment data to a location outside of the environment. Such a module may integrate a power element (302); a sensing element 9304); and a transmitting element (308) on a single substrate (320) within a single housing (310). Both sensors and circuitry components are formed directly on or in the substrate in novel configurations to decrease the size and weight of the module.

Abstract: A printed circuit board (PCB 22) capable of withstanding ultra high G forces and ultra high temperature as in a gas turbine (11). The PCB includes a substrate having a plurality of cavities (30A, 36A) formed therein for receiving components of a circuit, and conductors embedded in the PCB for electrically connecting the components together to complete the circuit. Each of the cavities has a wall (36A?) upstream of the G-forces which supports the respective component in direct contact in order to prevent the development of tensile loads in a bonding layer (37A). When the component is an integrated circuit (50), titanium conductors (63) are coupled between exposed ends of the embedded conductors and contact pads on the integrated circuit. A gold paste (51) may be inserted into interstitial gaps between the integrated circuit and the upstream wall.

Abstract: A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel.

Abstract: A method of forming a wear resistant coating on a combustion turbine component includes melting an ingot including at least one metallic carbide to form a metallic liquid including at least one metallic carbide. The metallic liquid including at least one metallic carbide is atomized in an atmosphere to form a metallic powder including at least one metallic carbide. The metallic powder including at least one metallic carbide is milled to form a nanosized metallic powder including at least one metallic carbide. The nanosized metallic powder including at least one metallic carbide is thermally sprayed onto the combustion turbine component.

Abstract: In one embodiment, a floor tile includes a body having a top side, a bottom side, and multiple lateral sides, and an integrated flow control element extending down from the bottom side, the flow control element being configured to control the flow of air below the floor tile.

Abstract: A structure and method for instrumenting a component for monitoring wear in a coating. The method includes depositing a first thin layer of electrically insulating material, depositing a thin electrically conductive layer over the first electrically insulating layer, depositing a second thin layer of electrically insulating material over the electrically conductive layer. An overlying thickness of the coating material is deposited over the second thin layer of electrically insulating material. The thicknesses of the insulating and conducting layers is controlled to be small enough such that the overlying coating surface exposed to mechanical wear retains a desired degree of smoothness without the necessity for a separate planarization step.

Abstract: A method of making a combustion turbine component includes forming a nanosized powder including a plurality of metals and at least one rare-earth element and agglomerating the nanosized powder to form a microsized powder including a plurality of metals and at least one rare-earth element. The microsized powder is processed to form a cohesive metallic mass and a primary aging heat treating is performed on the cohesive metallic mass. A solution heat treating may be performed on the cohesive metallic mass prior to the primary aging heat treating. A secondary aging treating may be performed on the cohesive metallic mass after the primary aging treating.

Abstract: A method is for forming a wear resistant coating on a workpiece. The method includes atomizing a metallic liquid including molybdenum in an atmosphere to form a crystalline metallic powder including molybdenum. The crystalline metallic powder is milled to form a nanocrystalline metallic powder including molybdenum. Moreover, the method includes thermal spraying the nanocrystalline metallic powder including molybdenum onto the workpiece.

Abstract: A method of manufacturing a metallic component includes atomizing, in an inert atmosphere, a metallic liquid having at least one rare-earth element and at least one non rare-earth element to form a metallic powder. A series of heat treating steps are performed on the metallic powder. A first heat treating step is performed in an oxidizing atmosphere, and a second heat treating step is performed in an inert atmosphere. A third heat treating step is performed in a reducing atmosphere to form a metallic power having an increased proportion of rare-earth oxides compared to non rare-earth oxides. The metallic component is formed from the metallic powder having the increased proportion of rare-earth oxides compared to non rare-earth oxides.

Abstract: A tungsten bronze structured ceramic material as a thermal barrier coating is described wherein the tungsten bronze structured ceramic coating material has the formula AO—BvOw—CyOz where O stands for Oxygen, A stands for a 2+ or a 1+ cation, B stands for a 2+ or 3+ cation and C stands for a 4+ or a 5+ cation. The thermal barrier coating may be applied for gas turbine components.

Abstract: A circuit assembly (34) affixed to a moving part (20) of a turbine for receiving information about a condition of the part and transmitting this information external to the engine. The circuit assembly includes a high-temperature resistant package (34A) that attaches to the part. A high temperature resistant PC board (42) supports both active and passive components of the circuit, wherein a first group of the passive components are fabricated with zero temperature coefficient of resistance and a second group of the passive components are fabricated with a positive temperature coefficient of resistance. The active components are fabricated with high temperature metallization. Connectors (40) attached to the PC board pass through a wall of the package (34A) for communication with sensors (30) on the part and with an antenna (26) for transmitting data about the condition of the part to outside the turbine.

Abstract: A circuit assembly (34) resistant to high-temperature and high g centrifugal force is disclosed. A printed circuit board (42) is first fabricated from alumina and has conductive traces of said circuit formed thereon by the use of a thick film gold paste. Active and passive components of the circuit assembly are attached to the printed circuit board by means of gold powder diffused under high temperature. Gold wire is used for bonding between the circuit traces and the active components in order to complete the circuit assembly (34). Also, a method for manufacturing a circuit assembly resistant to elevated temperature is disclosed.

Abstract: A circuit affixed to a moving part of an engine for sensing and processing the temperature of the part. The circuit generates a signal representative of the temperature sensed by a thermocouple (110) and amplified by an amplifier (112). A square wave oscillator (113) with a temperature sensitive capacitor (C8) varies its frequency in response to changes of a local temperature of the circuit. A chopper (114, J27) converts the output of the amplifier into an alternating current signal. The chopper is gated by the square wave oscillator and a second input is coupled to an output of the amplifier. Thus, the chopper has an output signal having a frequency representative of the local temperature and an amplitude representative of the thermocouple temperature, whereby the combined signals represent the true temperature of the part.

Abstract: In a telemetry system for use in an engine, a circuit structure (34) affixed to a moving part (20) of the engine is disposed for amplifying information sensed about a condition of the part and transmitting the sensed information to a receiver external to the engine. The circuit structure is adapted for the high temperature environment of the engine and includes a differential amplifier (102, 111) having an input for receiving a signal from a sensor (101, 110) disposed on the part. A voltage controlled oscillator (104, 115) with an input coupled to the output of the amplifier produces an oscillatory signal having a frequency representative of the sensed condition. A buffer (105, 116) with an input coupled to the output of the oscillator buffers the oscillatory signal, which is then coupled to an antenna (26) for transmitting the information to the receiver.

Abstract: A thin-film thermocouple (12) is disclosed for use with a gas turbine component. The thermocouple may be formed on a non-planar substrate (22) having formed thereon an electrically insulating layer (34) capable of maintaining its insulating properties at gas turbine operating temperatures. A first thermocouple leg (26) made of pure platinum is then deposited on the dielectric layer (34). A second thermocouple leg (28) made of another pure metal or a transparent ceramic oxide is also formed on the dielectric layer (34) wherein the first and second thermocouple legs make ohmic contact at a first end of each leg to form a hot junction (30) for conversion of heat into an electrical signal. The thermocouple may be deposited on a surface of a thermal barrier coating or between a thermal barrier coating and an underlying metal substrate.

Abstract: A method is provided for restoring a near-wall channeled gas turbine engine component (100, 200) which has been exposed to engine operation. In a representative embodiment, a cooling channel (102) of the component (100) is filled with a polymer that solidifies to form a preform material (110) in the cooling channel (102). Then existing outer wall layers (106, 108) of the component (100) are removed, thereby exposing in part the preform material (110). New outer wall layers (106-N, 108-N) are applied over the component (100), and this may be done while a cooling flow is also applied to the component (100). Then the preform material (110) is removed without destroying the new outer wall layers (106-N, 108-N). The new outer wall layers (106-N, 108-N) may be applied by HVOF processes or by other methods.

Abstract: A component for use in a combustion turbine (10) is provided that includes a substrate (212) and an abradable coating system (216) deposited on the substrate (212). A planar proximity sensor (250) may be deposited beneath a surface of the abradable coating system (216) having circuitry (252) configured to detect intrusion of an object (282) into the abradable coating system (216). A least one connector (52) may be provided in electrical communication with the planar proximity sensor (250) for routing a data signal from the planar proximity sensor (250) to a termination location (59). A plurality of trenches (142) may be formed at respective different depths below the surface of the abradable coating system (216) with a planar proximity sensor (250) deposited within each of the plurality of trenches (142).