Myers, SC
Abbey G. Myers, Hilton Head, SC US
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20080269618 | Non-Invasive In-Situ Detection Of Malignant Skin Tissue And Other Abnormalities Using Laser Plasma Spectroscopy - Disclosed is a system and method for a non-invasive method for determining the presence or absence of cancerous cells in the skin and deeper tissue levels. The system includes a portable handheld laser coupled with a spectroscopy system to produce real-time material analysis of the presence of cancerous cells without sample preparation. The system focuses a high peak power laser pulse onto a targeted material to produce a laser spark or micro-plasma. Elemental line spectra emission is created, collected and analyzed by a spectrophotometer. The line spectra emission data is quickly displayed on a laptop computer. “Eye-safe” Class I lasers provide for practical in-situ laser plasma spectroscopy applications such as detection of cancerous skin tissues. The emission data can be used to detect changes in the levels of a series of elements that are associated with cancerous cells versus normal skin cells. The system also finds use during excisional biopsy procedures to ensure that all cancerous cells have been removed. | 10-30-2008 |
David K. Myers, Rock Hill, SC US
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20100071721 | Masonry Mold Cleaning Apparatus And Method - A mold cleaning apparatus and method is provided for removing debris from an advancing masonry mold product. At least one rotatable tire is arranged at an acute angle to the masonry mold product and engages the mold product to provide a cleaning or scraping force to remove debris from the mold product. The cleaning force of the tire can be adjusted by changing the angle of the tire, the air pressure of the tire or the height of the tire relative to the mold surface. Multiple tires can be employed, while being rotated periodically to evenly distribute wear or replaced as needed. | 03-25-2010 |
Geoffrey Myers, Simpsonville, SC US
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20100220182 | SYSTEM AND METHOD FOR ADJUSTING ENGINE PARAMETERS BASED ON FLAME VISUALIZATION - In one embodiment, a system includes an engine that includes a combustion chamber and a viewing port into the combustion chamber. The engine also includes a camera configured to obtain an image of a flame in the combustion chamber through the viewing port and a controller configured to adjust a parameter of the engine based on the image of the flame. | 09-02-2010 |
20110197591 | AXIALLY STAGED PREMIXED COMBUSTION CHAMBER - A combustor for a gas turbine includes a plurality of radially outer nozzles arranged in an annular array, each of the radially outer nozzles having an outlet end located to supply fuel and/or air to a first combustion chamber. A center nozzle has an outlet end located axially upstream of the outlet ends of the radially outer nozzles, and is configured and arranged to supply fuel and air to a second combustion chamber axially upstream of the first combustion chamber. The second combustion chamber opens into the first combustion chamber and has a length sufficient to maintain a center nozzle flame confined to the second combustion chamber. | 08-18-2011 |
Geoffrey D. Myers, Simpsonville, SC US
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20090050710 | Fuel nozzle and diffusion tip therefor - A fuel nozzle having a dedicated circuit to cool the diffusion tip with lower part count and reduced complexity. More specifically, the proposed design uses an independent circuit to cool the tip with diffusion fuel or purge air. An impingement plate may be provided to augment the cooling effect. | 02-26-2009 |
20090211255 | GAS TURBINE COMBUSTOR FLAME STABILIZER - A gas turbine combustor is presented, which includes a combustion chamber that is positioned downstream of a premixing chamber. The premixing chamber includes at least one opening for ingesting air. At least one primary fuel nozzle is disposed to discharge fuel into the premixing chamber. The fuel discharged from the primary fuel nozzle mixes with the ingested air in the premixing chamber to provide a fuel air mix. A secondary fuel nozzle is disposed proximate the combustion chamber to discharge fuel at the combustion chamber. A stabilizer is disposed at the secondary fuel nozzle so as to be positioned in close proximity to a flame when fuel at the secondary fuel nozzle is ignited. The stabilizer is composed of a material having the ability to absorb heat from a heat flux generated within the combustor and maintaining a temperature sufficient to sustain ignition of the flame. A method of stabilizing a flame in a gas turbine combustor is also presented. The method including discharging fuel at a combustion chamber of the gas turbine combustor and positioning a stabilizer in close proximity to a flame when the fuel at a combustion chamber is ignited. The stabilizer absorbing heat from a heat flux generated within the combustor and maintaining a temperature sufficient to sustain ignition of the flame. | 08-27-2009 |
20100107639 | FUEL NOZZLE ASSEMBLY FOR USE WITH A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING SAME - A fuel nozzle configured to channel fluid toward a combustion chamber within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a first hollow tube fabricated from a first material that has a first coefficient of thermal expansion and a second tube fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, and the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation. | 05-06-2010 |
20100132364 | FUEL NOZZLE DETACHABLE BURNER TUBE - A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation. | 06-03-2010 |
20100170266 | METHOD AND APPARATUS FOR CONTROLLING A HEATING VALUE OF A LOW ENERGY FUEL - In an embodiment, a method includes determining a first heating value of a low BTU fuel, determining a target fuel quality level based on a state of a turbine system, controlling a second heating value of a high BTU fuel, and injecting the high BTU fuel into the low BTU fuel to achieve the target fuel quality level. | 07-08-2010 |
20100180599 | Insertable Pre-Drilled Swirl Vane for Premixing Fuel Nozzle - A swirl vane is independently connectable to a central hub assembly of a gas turbine. The swirl vane includes a structural body and at least one fuel delivery passage including a corresponding at least one fuel port defined within the structural body. At least one connecting tab is cooperable with the structural body and is connectable to the central hub assembly. | 07-22-2010 |
20100287943 | METHODS AND SYSTEMS FOR INDUCING COMBUSTION DYNAMICS - Methods and systems are provided for inducing combustion dynamics within turbine engines to remove combustion deposits within the turbine engine during operation of the turbine engine. | 11-18-2010 |
Geoffrey D. Myers, Greenville, SC US
Patent application number | Description | Published |
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20130186094 | Axial Flow Fuel Nozzle with a Stepped Center Body - An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings. | 07-25-2013 |
20150059352 | DUAL FUEL COMBUSTOR FOR A GAS TURBINE ENGINE - The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel, injection system positioned within the head end plenum and upstream of the premixer. The injection system may be configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel. The injection system also may be configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. The present application and the resultant patent also provide a related method of operating a dual fuel combustor. | 03-05-2015 |
Geoffrey David Myers, Greenville, SC US
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20150239046 | SYSTEM HAVING LAYERED STRUCTURE AND METHOD OF MAKING THE SAME - A system includes a layered structure. The layered structure includes first and second coalesced layers and an intermediate layer disposed between the first and second coalesced layers. The first and second coalesced layers have a higher degree of coalescence than the intermediate layer. | 08-27-2015 |
Jamie B. Myers, Greer, SC US
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20120190780 | ADDITIVE COMPOSITIONS AND THERMOPLASTIC POLYMER COMPOSITIONS COMPRISING THE SAME - A method for producing a thermoplastic polymer composition comprises the steps of separately providing a thermoplastic polymer and an additive composition and then mixing the thermoplastic polymer and additive composition. The additive composition comprises a clarifying agent and a coloring agent. Another method for producing a thermoplastic polymer composition comprises the steps of separately providing a thermoplastic polymer, a clarifying agent, and a coloring agent and then mixing the thermoplastic polymer, the clarifying agent, and the coloring agent. The coloring agent is present in the composition in an amount to yield a composition exhibiting CIE L*, a*, and b* values falling within a defined color space. An additive composition contains a clarifying agent and a coloring agent. The coloring agent is present in the composition in such an amount that when the additive composition is added to a thermoplastic polymer composition, the thermoplastic polymer composition exhibits CIE L*, a*, and b* values falling within a defined color space. | 07-26-2012 |
Jeffrey A. Myers, Hilton Head, SC US
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20080269618 | Non-Invasive In-Situ Detection Of Malignant Skin Tissue And Other Abnormalities Using Laser Plasma Spectroscopy - Disclosed is a system and method for a non-invasive method for determining the presence or absence of cancerous cells in the skin and deeper tissue levels. The system includes a portable handheld laser coupled with a spectroscopy system to produce real-time material analysis of the presence of cancerous cells without sample preparation. The system focuses a high peak power laser pulse onto a targeted material to produce a laser spark or micro-plasma. Elemental line spectra emission is created, collected and analyzed by a spectrophotometer. The line spectra emission data is quickly displayed on a laptop computer. “Eye-safe” Class I lasers provide for practical in-situ laser plasma spectroscopy applications such as detection of cancerous skin tissues. The emission data can be used to detect changes in the levels of a series of elements that are associated with cancerous cells versus normal skin cells. The system also finds use during excisional biopsy procedures to ensure that all cancerous cells have been removed. | 10-30-2008 |
John D. Myers, Hilton Head, SC US
Patent application number | Description | Published |
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20080269618 | Non-Invasive In-Situ Detection Of Malignant Skin Tissue And Other Abnormalities Using Laser Plasma Spectroscopy - Disclosed is a system and method for a non-invasive method for determining the presence or absence of cancerous cells in the skin and deeper tissue levels. The system includes a portable handheld laser coupled with a spectroscopy system to produce real-time material analysis of the presence of cancerous cells without sample preparation. The system focuses a high peak power laser pulse onto a targeted material to produce a laser spark or micro-plasma. Elemental line spectra emission is created, collected and analyzed by a spectrophotometer. The line spectra emission data is quickly displayed on a laptop computer. “Eye-safe” Class I lasers provide for practical in-situ laser plasma spectroscopy applications such as detection of cancerous skin tissues. The emission data can be used to detect changes in the levels of a series of elements that are associated with cancerous cells versus normal skin cells. The system also finds use during excisional biopsy procedures to ensure that all cancerous cells have been removed. | 10-30-2008 |
Melbourne Myers, Duncan, SC US
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20120213626 | EXPLOSION-WELDED GAS TURBINE SHROUD AND A PROCESS OF FORMING AN EXPLOSION-WELDED GAS TURBINE - An explosion-welded turbine shroud and a process of forming an explosion-welded gas turbine shroud are disclosed. The explosion-welded gas turbine shroud includes a first alloy explosion welded to a second alloy. In the explosion-welded gas turbine shroud, the first alloy forms at least a portion of a hot gas path or an expansion region of the gas turbine shroud includes the first alloy. The process includes explosion welding a first alloy to a second alloy to form the gas turbine shroud. | 08-23-2012 |
Melbourne J. Myers, Duncan, SC US
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20110095000 | WORKPIECE AND WELDING PROCESS FOR PREVENTING POROSITY IN A FORMED WELD - An article and method of forming the article are disclosed. The method includes positioning a first workpiece, positioning a second workpiece, and applying energy to the first workpiece and the second workpiece to form a weld. The article includes the first and second workpiece. The first workpiece includes a first weld surface, which includes at least one porosity reducing channel. The second workpiece includes a second weld surface positioned to be welded to the first weld surface. The application of energy generates gas that is directed by the at least one porosity reducing channel. | 04-28-2011 |
20140099194 | BIMETALLIC TURBINE SHROUD AND METHOD OF FABRICATING - A bimetallic ring for use as a turbine shroud in a gas turbine engine. The bimetallic ring forms a sealing surface as a hot gas flow path boundary in the engine. The ring is comprised of two materials. The first material, a wrought, oxidation resistant metal alloy comprises a first portion, which is the hot gas flow path sealing surface. The second material, a low cost low alloy steel, comprises a second portion that may be at least a pair of supporting side plates. A dissimilar weld joint joins the sealing surface to the second portion, the at least pair of supporting side plates. | 04-10-2014 |
Melbourne James Myers, Duncan, SC US
Patent application number | Description | Published |
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20090053045 | Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud - A gas turbine assembly includes a shroud that includes a plurality of interconnected shroud segments, wherein each one of the shroud segments comprises an arcuate base formed of a first metal material. The arcuate base is made up of an annular member having an axial component and a pair of upstanding ribs having flanges, wherein the arcuate base further comprises a high temperature capable material layer disposed on a surface of the arcuate base so as to define an inner diameter of the shroud segment (i.e., the hot gas path side or environmental side). | 02-26-2009 |
20120087798 | TURBINE BUCKET LOCKWIRE ROTATION PREVENTION - A retention system for a plurality of turbine buckets located in respective mating slots in a turbine rotor wheel includes a plurality of first circumferentially-oriented retention slots formed in outer peripheral portions of the turbine wheel; a plurality of second circumferentially-oriented retention slots formed in wheel mounting portions of said buckets, the first and second circumferentially-oriented retention slots aligned to form an annular lockwire retention slot; and a lockwire located within the annular lockwire retention slot. A first surface feature on one or both of the turbine rotor wheel and one or more of said plurality of turbine buckets is adapted to engage a second surface feature on the lockwire for preventing rotation of the lockwire beyond predetermined limits. | 04-12-2012 |
20150040582 | CROSSOVER COOLED AIRFOIL TRAILING EDGE - A cooling circuit for a turbine bucket having an airfoil portion includes a trailing edge cooling circuit portion provided with a first radially outwardly directed inlet passage intermediate leading and trailing edges of the airfoil portion of the bucket, extending from a platform portion of the bucket to a location adjacent a radially outer tip of the bucket, and connecting to a second radially inwardly directed passage extending from a location adjacent the radially outer tip to a location adjacent the platform portion. The second radially inwardly directed passage connects to a third trailing edge region passage, and a plurality of crossover passages connect a radially outer half of the second radially inwardly directed passage to a radially outer half of the third trailing edge region passage. | 02-12-2015 |
20150064010 | Turbine Bucket Tip Shroud - The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface. | 03-05-2015 |
Melbourne James Myers, Greenville, SC US
Patent application number | Description | Published |
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20140147283 | METHOD FOR MODIFYING A AIRFOIL SHROUD AND AIRFOIL - According to one aspect of the invention, a method is provided for modifying an airfoil shroud located at a tip of an airfoil of a airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location being proximate a seal rail extending circumferentially from the substantially horizontal surface and forming a relief cut in the airfoil shroud to remove the reference location, wherein a modifying of the airfoil shroud is complete following forming of the relief cut. | 05-29-2014 |
Michael J. Myers, Hilton Head, SC US
Patent application number | Description | Published |
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20080269618 | Non-Invasive In-Situ Detection Of Malignant Skin Tissue And Other Abnormalities Using Laser Plasma Spectroscopy - Disclosed is a system and method for a non-invasive method for determining the presence or absence of cancerous cells in the skin and deeper tissue levels. The system includes a portable handheld laser coupled with a spectroscopy system to produce real-time material analysis of the presence of cancerous cells without sample preparation. The system focuses a high peak power laser pulse onto a targeted material to produce a laser spark or micro-plasma. Elemental line spectra emission is created, collected and analyzed by a spectrophotometer. The line spectra emission data is quickly displayed on a laptop computer. “Eye-safe” Class I lasers provide for practical in-situ laser plasma spectroscopy applications such as detection of cancerous skin tissues. The emission data can be used to detect changes in the levels of a series of elements that are associated with cancerous cells versus normal skin cells. The system also finds use during excisional biopsy procedures to ensure that all cancerous cells have been removed. | 10-30-2008 |
Thomas Myers, Florence, SC US
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20140361055 | Hands-Free User Transport Harness - A harness is provided for transporting an injured, incapacitated or disabled individual. The harness is designed to enable a single user to transport a person on their back, thereby freeing up the hands of the user while evenly distributing the weight of the person being carried. The device comprises panel having a proximal section, a mid-section, and a distal end. The panel includes first and second pairs of interconnecting straps. The first pair of interconnecting straps is located along the vertical plane of the proximal and distal ends of the harness, whereby the distal end of the panel is capable of folding upward and being connected to the straps of the distal end, thereby securing an individual therein. The proximal end also comprises a second pair of securement straps, whereby the second pair of straps wraps horizontally around the individual to further secure them within the harness. | 12-11-2014 |
Thomas R. Myers, Summerville, SC US
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20150234373 | PROPORTIONAL JOG CONTROLS - The invention described herein generally pertains to proportional jog controls for a controller of a machining apparatus. The jog controls generate a variable signal proportional to a degree to which the jog controls are engaged by an operator. The controller, in turn, generates a motor drive signal proportional to the variable signal from the jog controls. Accordingly, the operator can jog the machining apparatus at a variable feed rate based on the degree of engagement with the jog controls which allows fine jogging control near a terminus of a jog operation. | 08-20-2015 |
20150239059 | METHODS AND SYSTEM FOR ENHANCED PLASMA TORCH CONTROL - A cutting system that utilizes an inertial sensor to control movement of a cutting device is provided. The system includes a cutting device for cutting operation, a controller, and at least one inertial sensor. The controller controls movement of the cutting device during cutting operation. The inertial sensor(s) is included in an inertial data module coupled to the cutting device and communicates inertial measurement data to the controller. The controller controls movement of the cutting device based on the inertial measurement data from the inertial sensor(s). | 08-27-2015 |