Abstract: Systems and methods that include providing, e.g., obtaining or preparing, a material that includes a hydrocarbon carried by an inorganic substrate, and exposing the material to a plurality of energetic particles, such as accelerated charged particles, such as electrons or ions.

Abstract: Apparatuses, methods, and systems are described herein for automating toolface control of a drilling rig. Such apparatuses, methods, and systems may change operating parameters of the drilling rig responsive to detected toolface orientations. Thus, if a toolface orientation of the drilling tool is determined to be outside an advisory sector, updated operating parameters may be determined and provided to the drilling tool. The updated operating parameters may change at least one of a clockwise rotation target or counterclockwise rotation target of the drilling tool.

Abstract: Apparatuses, methods, and systems are described herein for automating toolface control of a drilling rig. Such apparatuses, methods, and systems may determine an average drilling resistance function during a rotary drilling segment and, based on the average drilling resistance function during the rotary drilling segment, determine a target set of oscillation values to be used during a slide drilling segment.

Abstract: A method may include drilling a deviated wellbore penetrating a subterranean formation according to bottom hole assembly parameters and surface parameters; collecting real-time formation data during drilling; updating a model of the subterranean formation based on the real-time formation data and deriving formation properties therefrom; collecting survey data corresponding to a location of a drill bit in the subterranean formation; deriving a target well path for the drilling based on the model of the subterranean formation; deriving a series of trajectory well paths based on the formation properties, the survey data, the bottom hole assembly parameters, and the surface parameters and uncertainties associated therewith; deriving an actual well path based on the series of trajectory well paths; deriving a deviation between the target well path and the actual well path; and adjusting the bottom hole assembly parameters and the surface parameters to maintain the deviation below a threshold.

Abstract: The Mill-Right system is a hydraulic control system that optimizes drilling performance by controlling speed and force at the drill bit. It controls 3 drilling parameters through integrated software. 1) Weight on Bit (WOB); 2) Rate of Penetration (ROP); and 3) Differential Pressure (DP).

Abstract: A drill bit analysis and optimization system for use in a wellbore is provided. The system includes a drill bit including a cutter, a sensor that collects a data signal on a surface of the drill bit proximate to the cutter, and a signal processor unit that receives the data signal from the sensor and receives the expected drilling properties from the data reservoir. The processor analyzes the data signal to detect a resistivity profile from the sensor through a formation and optimizes a drilling parameter by comparing actual drilling properties with expected drilling properties.

Abstract: A monitoring system can include a dashboard including a graphical user interface display space. The monitoring system can also include a digital twin validation (DTV) system. The DTV system can be configured to perform operations including rendering, in the graphical user interface display space, a visual representation of an output value of a digital model of an oil and gas industrial machine, and an interactive graphical object characterizing an input value of the digital model. The operations can also include receiving data characterizing user interaction with the interactive graphical object. The data characterizes the user interaction indicative of the input value of the digital model. The operations can also include updating the digital model to generate an updated output value representative of an operational characteristic of the oil and gas industrial machine.

Abstract: A sensor system for the measurement of a physical parameter, such as temperature or pressure comprises a first, fixed module (5), and a second module (20) positionable proximate to the first. The first module has a measurement coil (6) and a reference coil (7), where the measurement coil forms part of an electrical circuit that is subject to variation by the physical parameter, and the reference coil forms part of a circuit not subject to the physical parameter being measured. The second module has a pair of reading coils (22, 23), each arranged to couple to respective measurement and reference coils, where the reading coils are connectable to signal generation and measurement equipment, and the system is arranged to measure electrical characteristics of the measurement and reference coils via the coupling. It has particular utility in harsh environments such as in wells, where the first module may be fixed, and the second module may be lowered adjacent the first.

Abstract: A sensing and communication system for a gas lift well is provided. The gas lift well includes a casing, production tubing positioned within the casing, and a gas lift valve coupled to the production tubing. The sensing and communication system includes a turbine configured to rotate in response to an injected gas stream flowing through the turbine, wherein the turbine is positioned one of i) within an annulus defined between the production tubing and the casing and ii) within the gas lift valve, an alternator coupled to the turbine and configured to generate electrical power from rotation of the turbine, and at least one sensor coupled to the alternator and configured to operate using the generated electrical power.

Abstract: A gap joint for use with a gap sub for electromagnetic telemetry. The gap joint has a replaceable uphole shoulder on the male gap joint component, which may be composed of a sacrificial material, to extend gap joint useful life where there is electrolysis of the component outside diameter. The gap joint also has a thicker outside diameter seal to reduce the risk of underlying O-ring extrusion and failure, again extending gap joint useful life. The thicker seal may also be able to withstand higher pressures before collapsing or experiencing punctures in unsupported areas. The replaceable shoulder and outside diameter seal can be used separately or together in a gap joint.

Abstract: A drilling system including a sensor configured to monitor at least one drilling parameter, and configured to generate a signal based on the at least one drilling parameter. An encoder is in communication with the sensor, and the encoder is configured to convert the signal into a modulation signal. A flow modulator is configured to channel drilling fluid therethrough. The flow modulator includes at least one stator element and a rotor element configured to freely rotate relative to the at least one stator element as the drilling fluid flows past the rotor element. A braking system is in communication with the encoder, and the braking system is configured to selectively decrease a rotational speed of the rotor element based on the modulation signal such that an encoded acoustic signal is emitted from the flow modulator through the drilling fluid.

Abstract: The present approach includes implementations for generating thermos-hydraulic data via a simulation and evaluating the thermo-hydraulic data pertaining to one or more parameters of a production system. The approach includes receiving operating parameters and receiving coefficients of polynomials for constructing a plurality of pump performance curves. The approach includes performing a selection step. The selection step includes selecting a pump from a plurality of pump types, and sizing the pump based in part on the thermo-hydraulic data, the operating parameters, and the coefficients of polynomials. The approach includes repeating the selection step until each pump of the plurality of pump types has been considered to generate a subset of pumps from the plurality of pump types. The approach includes performing an optimization step on the subset of pumps. The approach includes generating a visual display to identify the set of preferred pumps.

Abstract: A triaxial test system and method including a core sample, high temperature-resistant drains disposed around the core sample, and at least one and optionally two high temperature-resistant elastomeric sealing membranes disposed about the drains and sample. Preferred for use is a shear-resistant and high temperature-resistant sealing membrane such as a Viton membrane, optionally in combination with a silicone high temperature-resistant sealing membrane. The system and methods can be used to test core samples in compliance with ASTM standard test methods for triaxial compression tests, at temperatures of between about 100° C. and 200° C., optionally between about 175° C. and 200° C., for extended periods of time, for example several days or longer.

Abstract: The embodiments herein relate to sensors having reactive filter materials for detecting analytes in wellbores. The sensor includes at least one reactive filter material arranged in a flow line, wherein the reactive filter material sorbs an analyte in a wellbore fluid in the flow line; and at least one detector that detects a sorption signal specific to the analyte at at least a first location and a second location of the reactive filter material, wherein the first location is upstream in the flow line relative to the second location. The detector either (1) calculates a balanced measurement corresponding to the presence of the analyte in the wellbore or (2) relays the measurements to a signal processing unit to calculate a balanced measurement corresponding to the presence of the analyte in the wellbore.

Abstract: A method includes deploying a fluid sampling tool string downhole, the fluid sampling tool string including a control module and a plurality of fluid sampling modules. The method also includes receiving, by the control module, a telemetry signal from a surface interface. The method also includes transmitting, by the control module, a downlink acoustic signal based at least in part on the received telemetry signal. The method also includes initiating a fluid sampling operation, by at least one of the plurality of fluid sampling modules, in response to the downlink acoustic signal.

Abstract: The present disclosure relates to a downhole packer assembly that includes an inner packer and a drain coupled to the inner packer. The drain includes a sample inlet, a guard inlet, and a seal disposed between the sample inlet and the guard inlet.

Abstract: A tool for removing a portion of a rotor blade including a bracket; a mounting member slidably coupled to the bracket; and a heating element coupled to the mounting member, the heating element configured to heat and slide underneath a portion of a rotor blade to be removed. An embodiment provides a method for removing a portion of a rotor blade positioning a tool adjacent to a rotor blade with a portion of the rotor blade to be removed, heating at least some of the portion of the rotor blade to be removed with the heating element; slidably moving the mounting member such that the heating element moves between the rotor blade and the portion of the rotor blade to be removed; and disengaging a portion of the rotor blade to be removed from the rotor blade.

Abstract: A turbine wheel for a turbocharger is provided. The turbine wheel includes a plurality of blades and a mid-plane is defined between a pressure side and a suction side of adjacent blades. Each of the blades has a leading edge, and is coupled to the wheel hub along a respective blade hub camber line. The wall has a first radii at the leading edge that extends for a first circumferential distance adjacent to the suction side. The first circumferential distance is at least 12% of a circumferential distance that extends between adjacent blades. The wheel hub includes a plurality of scallops defined through the wall. Each of the scallops is asymmetrical about the mid-plane. For each of the scallops, the wall has a second minimum radii defined offset from the mid-plane toward the suction side and a third minimum radii defined offset from the mid-plane toward the pressure side.

Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, an axial centerline extended along the longitudinal direction, an upstream end and a downstream end opposite of the upstream end along the longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes a high speed turbine rotor coupled to a high pressure (HP) shaft and HP compressor, a low speed turbine rotor comprising an axially extended hub, and a first turbine bearing disposed radially between the low speed turbine rotor and the high speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit through the high speed turbine rotor. The low speed turbine rotor includes a rotating nozzle adjacent to the turbine cooling conduit. The first turbine bearing defines an outer air bearing and an inner air bearing. The first turbine bearing defines a stationary nozzle adjacent to the rotating nozzle of the first turbine rotor.

Abstract: A method of fabricating an airfoil includes imaging a second end of the body portion to obtain image data, casting the tip portion utilizing the image data of the second end of the body portion and coupling a first end of the tip portion to the second end of the body portion. One or more features of the tip portion align with one or more features of the body portion. The method also includes additively manufacturing a core of the tip portion utilizing the image data and forming a casting mold about the core. The tip portion is cast in the casting mold. The coupling of the tip portion to the body portion including depositing a bonding material on a first end of the tip portion. An airfoil formed by the method is also disclosed.

Abstract: An airfoil damping assembly includes an airfoil defining a hollow interior. Also included is an airfoil plurality of ribs disposed within the hollow interior. Further included is a plurality of cavities, each of the cavities defined by at least one of the plurality of ribs. Yet further included is a damping fluid disposed in one of the cavities to damp vibratory stresses of the airfoil during operation.

Abstract: In one embodiment, a component for a gas turbine engine is provided. The component including: an airfoil having a tip portion; a tip shelf located in the tip portion; a first plurality of cooling openings located in an edge of the tip shelf that extends along at least a portion of a pressure side of the airfoil; and a second plurality of cooling openings located in an edge of the tip portion proximate to the tip shelf that extends along at least a portion of a pressure side of the tip portion.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage extending between a root and a tip of the airfoil. The airfoil further defines a pocket positioned between the cooling passage and an exterior surface of the airfoil and spaced apart from the cooling passage and the exterior surface. The pocket provides a thermal impediment between the cooling passage and the exterior surface of the airfoil.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core.

Abstract: A ceramic matrix composite (CMC) turbine blade assembly includes a rotor, a CMC turbine blade, and at least one dovetail sleeve. The rotor has a blade slot with at least one slot surface. The slot surface is at a slot angle. The CMC turbine blade is received in the blade slot. The CMC turbine blade includes a dovetail root having at least one root surface. The root surface is at a root angle. The root angle is at least 5 degrees greater than the slot angle. The dovetail sleeve is received in the blade slot of the rotor. The dovetail sleeve has at least one inner surface contacting at least one root surface and at least one outer surface contacting at least one slot surface to radially retain the CMC turbine blade in the blade slot. A dovetail sleeve and a method of mounting a CMC turbine blade are also disclosed.

Abstract: A turbine vane adapted for use in a gas turbine engine is described in this application. The turbine vane illustratively includes ceramic matrix composite components adapted to be coupled to metallic components.

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly defining a flow path through a gas turbine engine, as well as axial and radial directions that are orthogonal to one another and a circumferential direction extending about the axial direction, comprises a nozzle airfoil having a first end opposite a second end and a wall defining a flow path boundary. The wall has an opening therein through which the second end of the nozzle airfoil protrudes such that the second end extends outside of the flow path. The flow path assembly further comprises a cap extending over the second end of the nozzle airfoil and an attachment member extending through the second end and the cap to attach the second end to the cap. Other embodiments of a flow path assembly having nozzle airfoils decoupled from the flow path boundary also are provided.

Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an assembly axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. A retention clip has an intermediate portion connecting a first leg portion and a second leg portion. The intermediate portion is compressible to position the first and second leg portions in the pair of airfoil openings such that the retention clip limits movement of the airfoil relative to the first shroud.

Abstract: Disclosed is a vane assembly. An outer ring segment surrounds a rotor extending through an inner central portion of a casing. Vanes are fitted into the outer ring segment in a direction perpendicular to an axial direction of the rotor. A fixing portion is fitted into the outer ring segment to fix the vanes to the outer ring segment.

Abstract: The gas turbine has a plurality of inlet guide vanes each having a blade having a leading edge, a trailing edge, a span extending along the leading edge, and pivot members at opposite ends of the leading edge, and being pivotally mounted across the radial-to-axial intake via the pivot members, the pivot axis extending axially across a radial portion of the radial-to-axial intake. The plurality of inlet guide vanes include a plurality of first inlet guide vanes, and a plurality of second inlet guide vanes, the second inlet guide vanes having a trailing edge recess differing from the corresponding portion of the first inlet guide vanes. During operation, when the inlet guide vanes are pivoted past a given angle toward the tangential orientation, a radial flow of gas is allowed through the trailing edge recesses to avoid or impede vortex whistle.

Abstract: The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.

Abstract: A spring guide for use in a seal housing including a first body portion, a second body portion, and a flange portion, including a flange width, extending circumferentially between the first body portion and the second body portion. The flange width being less than or equal to approximately 2.1 millimeters.

Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

Abstract: A turbomachine includes a compressor, a combustor, and a turbine. The turbine includes a nozzle, a shroud, and an axial cavity defined between the nozzle and the shroud. The nozzle includes an inner platform, an outer platform spaced apart from the inner platform along a radial direction, and an airfoil extending therebetween. The outer platform extends axially between a forward sidewall and an aft sidewall. The nozzle also includes an aft hook radially outward of the outer platform and axially forward of the aft sidewall of the outer platform. The shroud includes a forward end adjacent to the aft sidewall of the outer platform. A sealing interface is positioned within the cavity, radially outward of the outer platform of the nozzle and axially forward of the aft sidewall of the outer platform of the nozzle.

Abstract: A seal assembly for a turbine engine having a shaft with a rotary axis and a housing surrounding the shaft; the seal assembly being disposed between the shaft and the housing, the seal assembly comprising: an outer labyrinth seal having multiple outer fins in opposing sealing engagement with a concentric outer seal runner, one of: the outer labyrinth seal fins; and the outer seal runner, engaging the housing, and the shaft engaging an opposing one of: the outer seal runner; and the outer labyrinth seal fins; an inner labyrinth seal, disposed radially inwardly concentric to and axially overlapping the outer labyrinth seal and the outer seal runner, the inner labyrinth seal having multiple inner fins in opposing sealing engagement with a concentric inner seal runner, one of: the inner labyrinth seal fins; and the inner seal runner, engaging the housing, and the shaft engaging an opposing one of: the inner seal runner; and the inner labyrinth seal fins; and an intermediate plenum, defined between the outer fins,

Abstract: A turbine shroud adapted for use in a gas turbine engine is disclosed in this paper. The turbine shroud includes a blade track segment comprising ceramic matrix composite materials and an attachment unit comprising metallic materials. The attachment unit is coupled to the blade track segment and is configured to interface with other metallic components in the gas turbine engine.

Abstract: An optical fiber probe includes a probe body, an optical fiber, and a position regulating member. The probe body has a first bottom plate with an outer surface, a second bottom plate opposite to the first bottom, and an internal space. The optical fiber is housed in the internal space. The position regulating member is attached to the probe body. The optical fiber includes a small-diameter portion and a large-diameter portion. The first bottom plate has an inner surface in the internal space and a through hole for communicating the outer surface and the inner surface. The small-diameter portion is inserted into the through hole. The large-diameter portion is arranged such that a first end face thereof is in contact with the inner surface while being bent by the position regulating member in contact with a second end face thereof.

Abstract: An arrangement for a gas turbine engine that includes a turbine blade configured to rotate about an axis, a casing radially outside of the turbine blade, and a carrier segment mounted to the casing so as to define a first impingement space therebetween. The carrier segment is positioned radially outside the turbine blade and includes a first impingement carrier wall, a main carrier wall, and a cooling chamber. The first impingement carrier wall is adjacent to and radially inside of the first impingement space, and the first impingement carrier wall includes a first aperture. The main carrier wall is radially inside of the first impingement carrier wall. The cooling chamber is radially inside of the main carrier wall. Additionally, an intermediate chamber is disposed radially between the cooling chamber and the first impingement space. A second aperture is configured to allow ingress of air into the intermediate chamber.

Abstract: A steam turbine includes a turbine main body supplied with steam from a steam supply unit and a steam valve for controlling an amount of steam to be supplied from the steam supply unit to the turbine main body. The turbine main body includes a first connection unit; and pluralities of guide rods and threaded rods, each extending from the first connection unit. The steam valve includes a second connection unit configured to be coupled to the first connection unit; and a flange disposed around the second connection unit, to receive the guide rods and threaded rods through corresponding through-holes respectively formed in the flange. The first connection unit includes an inner circumference and an end surface provided around the inner circumference, and the guide rods and threaded rods are arranged symmetrically around the inner circumference of the first connection unit and are fixed to the first connection unit.

Abstract: A device that measures turbomachine aerodynamic flow parameters is presented. The device includes the information collection elements relating to the flow parameters, and a body that includes the information collection elements. The body features a portion that is elongated in the longitudinal direction and configured to form the leading edge of a turbomachine vane, and a first side portion that laterally extends portion in an axial direction, wherein the information collection elements protrude from the leading edge of the portion and the portion includes internal channels that route the information and individually communicate with at least one information collection elements, wherein the first side portion features a first surface configured to fit, at least partially, onto a second surface of an intrados or extrados wall of a turbomachine vane.

Abstract: A gas turbine engine component includes a metal substrate and a coating system disposed on the metal substrate. The coating system includes at least one layer of aluminum-chromium oxide.

Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor including a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor including a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; and a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit extended within the high speed turbine rotor.

Abstract: A bolted joint apparatus includes: a first component including a first row of first bolt holes extending therethrough; a second component including a second row of second bolt holes extending therethrough wherein the second bolt holes are aligned coaxially with the first bolt holes, a plurality of fasteners, each of fasteners disposed through aligned pairs of the first and second bolt holes to couple together the first and second components, each of the fasteners including a shank; and crushable spacers disposed around the shanks of the fasteners, the crushable spacers clamped in compression between the fasteners and one of the components, wherein each of the crushable spacers has a tubular body interconnecting first and second enlarged ends, the tubular body being defined by a peripheral wall which incorporates at least one weakening feature.

Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud that extends about an axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body that extends from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. At least one retention clip has an intermediate portion connecting a pair of elongated leg portions. The pair of elongated leg portions are received in the pair of airfoil openings such that the at least one retention clip limits movement of the airfoil relative to the first shroud. A method of assembling a stator assembly is also disclosed.

Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines at least one airfoil opening. At least one retention clip has an arcuate portion extending from a first elongated leg portion. The first elongated leg portion and the arcuate portion are received through the at least one airfoil opening such that the at least one retention clip limits movement of the airfoil relative to the first shroud.

Abstract: Systems and methods are provided for controlling the pressure of a working fluid at an inlet of a main pressurization device of a heat engine system. The heat engine system may include a control system and a working fluid circuit including a waste heat exchanger, an expansion device, a recuperator, a main pressurization device, and a heat exchanger assembly. The heat exchanger assembly may include a plurality of gas-cooled heat exchangers configured to transfer thermal energy from the working fluid to a cooling medium, a plurality of fans configured to direct the cooling medium into contact with the gas-cooled heat exchangers, and a plurality of drivers, each driver configured to drive a respective fan. The control system may be communicatively coupled to the heat exchanger assembly and configured to modulate a rotational speed of at least one fan to regulate a pressure of the working fluid at the inlet.

Abstract: The present disclosure relates to power plants. Various embodiments thereof may include a method for operating a gas-and-steam combined-cycle power plant. For example, some embodiments may include a method for operating a gas-and-steam combined-cycle power plant including: providing exhaust gas from a gas turbine to a steam generator; generating steam by means of the exhaust gas; driving a generator with the steam via a turbine installation to provide an electric current; removing the exhaust gas from the steam generator; and using at least a portion of heat contained in the exhaust gas downstream from the steam generator to affect an endothermic chemical reaction.

Abstract: The invention provides a method of generating power using a combined cycle, comprising operating a first power system in which fuel is burned to generate primary power and a flue gas stream at a flue gas temperature greater than 450° C., and operating a second power system to generate secondary power from the heat comprised by the flue gas stream, the second power system comprising a waste heat recovery heat exchanger. The method further comprises passing the flue gas stream through the waste heat recovery heat exchanger, passing a pressurized waste heat recovery fluid through the waste heat recovery heat exchanger to receive heat from the flue gas stream thereby obtaining a pressurized vaporous waste heat recovery fluid having a temperature in the range of 350° C.-500° C. The waste heat recovery fluid comprises more than 75 mol % of fluorinated ketones.

Abstract: A combined cycle power plant is capable of improving power output and power generation efficiency by cooling intake air supplied to a gas turbine. The plant includes a gas turbine power generation system, an operating fluid power generation system, and a cooling system. The gas turbine power generation system includes an air compressor for compressing air supplied through an air incoming path, a gas turbine for generating rotary power by burning a mixture of fuel and the air compressed by the air compressor, and a first generator for generating electricity by using the rotary power of the gas turbine. The operating fluid power generation system heats an operating fluid by using combustion gas discharged from the gas turbine and generates electricity using the heated operating fluid. The cooling system cools air supplied from the air compressor by supplying the operating fluid to an upstream side of the air compressor.

Abstract: The present invention is directed to methods and systems for utilizing supercritical carbon dioxide in an open thermodynamic cycle in which no compressors are used. In some embodiments, a method for utilizing supercritical carbon dioxide includes combusting oxygen, fuel, and heated recycled supercritical carbon dioxide to produce a gas that is fed to a turbine to generate power; using the exhaust gas from the turbine to preheat the recycled supercritical carbon dioxide that is fed to the turbine; and pass the exhaust gas through a series of two sets of condensers and separators to provide a carbon dioxide stream from which the recycled supercritical carbon dioxide is generated using a pump. Power for the pump is provided by the turbine, which also provides power to an electric generator.