Direct air capture systems and methods from a gas turbine

Abstract

A gas turbine engine includes a compressor section including a first compressor stage for compressing a fluid and a second compressor stage in flow communication with the first compressor stage and to further compress the compressed fluid. The gas turbine engine also includes a direct air capture (DAC) module in flow communication with the first compressor stage and the second compressor stage. The DAC module receives compressed fluid from the first compressor stage, adsorbs carbon dioxide from the compressed fluid to generate a filtered compressed fluid, and discharges the filtered compressed fluid to the second compressor stage.

Description

700905-WO-l(17851-1500)DIRECT AIR CAPTURE SYSTEMS AND METHODS FROM A GAS TURBINETECHNICAL FIELD

[0001] The disclosure relates generally to gas separation, and more particularly, to direct air capture systems and methods for capturing carbon dioxide from pressurized air within a gas turbine system.BACKGROUND

[0002] Direct air capture (DAC) is an advancing technology for extracting carbon dioxide from ambient air for storage and / or utilization for other processes. With DAC, ambient air is passed through a solvent or sorbent to separate carbon dioxide from the ambient air. The absorbed or adsorbed carbon dioxide is desorbed through the application of energy, such as heat. As can be appreciated, the carbon dioxide yield for a given energy input varies with the concentration of carbon dioxide in the input gas. For example, the concentration of carbon dioxide in flue gas may be significantly higher than the concentration of carbon dioxide in ambient air. The higher concentration within the flue gas generally results in a greater yield of captured carbon dioxide for a given energy input. However, the use of increased fossil fuel emissions to extract a greater percentage of carbon dioxide is counterintuitive to achieving net neutrality or a reduction in carbon dioxide concentrations in Earth’s atmosphere.

[0003] Accordingly, it would be desirable to increase a concentration of carbon dioxide within air supplied to the DAC and increase the yield of captured carbon dioxide for a given energy input.SUMMARY

[0004] In one aspect, a gas turbine engine includes a compressor section including a first compressor stage for compressing a fluid and a second compressor stage in flow communication with the first compressor stage and to further compress the compressed fluid. The gas turbine engine also includes a direct air capture (DAC) module in flow communication with the first compressor stage and the second compressor stage. The DAC module receives compressed fluid from the first compressor stage, adsorbs carbon dioxide from the compressed fluid to generate a filtered compressed fluid, and discharges the filtered700905-WO-l (17851-1500) compressed fluid to the second compressor stage.

[0005] In another aspect, a gas turbine system includes a gas turbine engine including a compressor section. The compressor section includes a first compressor stage to compress a fluid and a second compressor stage in flow communication with the first compressor stage and oriented to further compress the compressed fluid. The gas turbine engine also includes a direct air capture (DAC) module in flow communication with the first compressor stage and the second compressor stage. The DAC module receives compressed fluid from the first compressor stage, adsorbs carbon dioxide from the compressed fluid to generate a filtered compressed fluid, and discharges the filtered compressed fluid to the second compressor stage. A steam turbine is operably coupled to the gas turbine engine, and a control system is operably coupled to the gas turbine engine. The control system includes a memory' and a processor. The memory storing instructions when executed, cause the processor to regulate a temperature within the direct air capture module.

[0006] In yet another aspect, a method of operating a gas turbine engine includes channeling a fluid into a first compressor stage of a gas turbine engine, and compressing, via the first compressor stage, the fluid entering into the first compressor stage. The method also includes discharging compressed fluid, adsorbing, via a direct air capture (DAC) module, carbon dioxide from the compressed fluid to generate filtered compressed fluid, and discharging the filtered compressed fluid to a second compressor stage of the gas turbine engine.

[0007] The illustrative aspects of the present disclosure are designed to solve the problems herein described and / or other problems not discussed.BRIEF DESCRIPTION OF THE DRAWINGS

[0008] These and other features of this disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure taken in conjunction with the accompanying drawings that depict various embodiments of the disclosure, in which:

[0009] FIG. 1 is a schematic view of an exemplary' gas turbine system ;

[0010] FIG. 2A is a schematic view of a gas turbine engine used with the gas turbine system shown in FIG. 1 ;

[0011] FIG. 2B is a schematic view of another embodiment of a gas turbine engine used with700905-WO-l (17851-1500) the gas turbine system shown in FIG. 1 ;

[0012] FIG. 2C is a schematic view of yet another embodiment of a gas turbine engine used with the gas turbine system shown in FIG. 1;

[0013] FIG. 3 is a plot showing exemplary adsorbate loading versus adsorbate partial pressure in accordance with the disclosure;

[0014] FIG. 4 is a schematic view of an exemplary direct air capture module used with the gas turbine engine shown in FIG. 2;

[0015] FIG. 5 is a schematic view of an exemplary adsorption module that may be used with the direct air capture module shown in FIG. 4;

[0016] FIG. 6 is a schematic view of an exemplary control system that may be used with the gas turbine system shown in FIG. 1;

[0017] FIG. 7A is a flow diagram of an exemplary method that may be implemented to control a gas turbine system; and

[0018] FIG. 7B is a continuation of the flow- diagram of FIG. 7A.

[0019] It is noted that the drawings of the disclosure are not to scale. The drawings are intended to depict only typical aspects of the disclosure, and therefore should not be considered as limiting the scope of the disclosure. In the drawings, like numbering represents like elements between the drawings.DETAILED DESCRIPTION

[0020] In accordance with the disclosure, a direct air capture (DAC) module may be integrated and / or otherwise operably coupled to a compressor section of a gas turbine engine. As can be appreciated, compressing ambient air increases a partial pressure of carbon dioxide within a given volume, thus increasing the potential yield of carbon dioxide captured by the DAC. In this manner, the compressor section of the gas turbine engine can be utilized to deliver pressurized air or fluid to the DAC module for capturing carbon dioxide, and the filtered air or fluid discharged from the DAC module may be delivered to a second compressor stage or to subsequent compressor stages of the compressor section for additional processing.

[0021] As can be appreciated, an efficiency of the adsorption of carbon dioxide from the fluid may be at least partially dependent upon a temperature of the fluid entering the DAC module. In some embodiments, the gas turbine engine may include a first heat exchanger for cooling or otherwise reducing the temperature of the compressed fluid exiting the first700905-WO-l (17851-1500) compressor stage. The first heat exchanger may be coupled to a cooling fluid to facilitate heat exchange between the compressed fluid and the cooling fluid, thus reducing the temperature of the compressed fluid and increasing the temperature of the cooling fluid. In some embodiments, the DAC module includes a second heat exchanger in fluid and / or flow communication with the first heat exchanger, and in thermal communication with an adsorption module of the DAC module. In this manner, heated cooling fluid received from the first heat exchanger is circulated through the second heat exchanger to increase the temperature of the adsorption module and to facilitate desorbing carbon dioxide adsorbed by the adsorption module. As can be appreciated, the efficiency of desorbing the carbon dioxide may be dependent upon a temperature of the adsorption module. In some embodiments, the temperature of the adsorption module or the environment within which the adsorption module is disposed may be regulated using the second heat exchanger. The captured carbon dioxide is discharged from the DAC module to be stored or otherwise utilized by a downstream process and the filtered fluid is discharged from the DAC module to the second or subsequent compressor stages of the compressor section for further processing and operation of the gas turbine engine.

[0022] In some embodiments, the gas turbine engine may include a secondary heat exchanger in fluid and / or flow communication with the compressed fluid exiting the first compressor stage and cooled compressed fluid exiting the DAC module. The secondary heat exchanger exchanges heat between the compressed fluid exiting the first compressor stage and the cooled compressed fluid exiting the DAC module to effectuate a decrease in temperature of the compressed fluid received from the first compressor stage and an increase in temperature of the cooled compressed fluid exiting the DAC module. The cooled compressed fluid exiting the secondary' heat exchanger is received by the first heat exchanger and the heated compressed fluid exiting the secondary heat exchanger is received by the second compressor stage. In embodiments, the secondary heat exchanger may’ receive compressed fluid from a last compressor stage of the compressor section and may discharge warm compressed fluid to a combustion section of a turbine section of the gas turbine engine.

[0023] Unless otherwise indicated, approximating language, such as “generally,” “substantially,” and “about,” as used herein indicates that the term so modified may apply to only an approximate degree, as would be recognized by one of ordinary skill in the art, rather than to an absolute or perfect degree. Accordingly, a value modified by a term or terms such700905-WO-l (17851-1500) as ‘'about,” “approximately,” and “substantially” is not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value. Additionally, unless otherwise indicated, the terms “first,” “second.” etc. are used herein merely as labels, and are not intended to impose ordinal, positional, or hierarchical requirements on the items to which these terms refer. Moreover, reference to, for example, a “second” item does not require or preclude the existence of, for example, a “first” or lower-numbered item or a “third” or higher-numbered item.

[0024] In addition, several descriptive terms may be used regularly herein, and it should prove helpful to define these terms at the onset of this section. These terms and their definitions, unless stated otherwise, are as follows. As used herein, "downstream" and “upstream” are terms that indicate a direction relative to the flow- of a fluid, such as the working fluid through the turbine engine or, for example, the flow of air through the combustor or coolant through one of the turbine's component systems. The term "downstream" corresponds to the direction of flow' of the fluid, and the term “upstream” refers to the direction opposite to the flow. The terms “forward” and “aft,” without any further specificity, refer to directions, with “forward” referring to the front or compressor end of the engine, and “aft” referring to the rearward or turbine end of the engine. It is often required to describe parts that are at differing radial positions with regard to a center axis. The term “radial” refers to movement or position perpendicular to an axis. In cases such as this, if a first component resides closer to the axis than a second component, it will be stated herein that the first component is “radially inward” or “inboard” of the second component. If, on the other hand, the first component resides further from the axis than the second component, it may be stated herein that the first component is “radially outward” or “outboard” of the second component. The term “axial” refers to movement or position parallel to an axis. Finally, the term “circumferential” refers to movement or position around an axis. It will be appreciated that such terms may be applied in relation to the center axis of the turbine.

[0025] Referring now' to the drawings, FIG. 1 illustrates an exemplary gas turbine system 10 that facilitates Direct Air Capture (DAC) of carbon dioxide. The gas turbine system 10 includes a gas turbine engine 12, which in some embodiments, may be operably coupled to a control system or to a controller 14. In the exemplary embodiment, the gas turbine engine700905-WO-l (17851-1500)12 includes a fluid intake section 16, a compressor section 18, a combustor section 20, a turbine section 22, a load 24, and an exhaust section 26. The fluid intake section 16 draws or otherwise receives a fluid F to be compressed by the compressor section 18. It is envisioned that the fluid F may be any fluid or any mixture of fluids embodying any state, such as a liquid or a gas, and / or having any characteristic, such as pressure, temperature, humidity, carbon dioxide concentration, etc. In one non-limiting embodiment, the fluid F is ambient air surrounding or otherwise in fluid and / or flow communication with the fluid inlet section 16 having a carbon dioxide concentration of about 460 parts per million (0.046%).

[0026] In embodiments, the fluid intake section 16 may include one or more ducts or upstream components 16a including at least one of silencer baffle, fluid injection systems (e.g., heater fluid injection for anti-icing), filters, evaporative coolers, chillers, deicing units, and / or combinations thereof. It is envisioned that the compressor section 18 may include an upstream inlet duct 28 defining a mouth 30, which in embodiments, may have a bell-shaped profile. The inlet duct 28 may define a fluid intake path extending between an inner hub 32 and an outer wall 34, stationary vanes 36, and inlet guide vanes 38. It is contemplated that the inlet guide vanes 38 may be operably coupled to one or more actuators 40 operably coupled to. and in communication with, the control system 14. In embodiments, operation of the one or more actuators 40 may be controlled by the control system 14.

[0027] The compressor section 18 is in fluid and / or flow communication with the fluid intake section 16 and includes one or more compressor stages 42a, 42b, . . . , 42n+i, that each include a plurality of compressor blades 44. Each blade 44 is coupled to a compressor shaft 46 that is rotatably supported within a compressor casing 48. Each of the compressor stages 42 may include a plurality7of compressor vanes 50 spaced on the compressor casing 48. The compressor blades 44 and the compressor vanes 50 are arranged circumferentially about a longitudinal axis defined by the compressor shaft 46 within each compressor stage 42. It is envisioned that the compressor section 18 may include any number of compressor stages 42 depending upon the design needs of the gas turbine system 10, and in embodiments, may include between about one to about thirty or more compressor stages 42. In one non-limiting embodiment, the compressor stages 42 may alternative between sets of compressor blades 44 and sets of compressor vanes 50 in a direction of a fluid F flowing through the compressor section 18. As can be appreciated, in operation, the compressor stages 42 cooperate to progressively compress the fluid F flowing through the compressor section 18 and to deliver700905-WO-l (17851-1500) compressed fluid Fc to the combustor section 20. In the exemplary embodiment, the compressor section 18 compresses the fluid F flowing through the compressor stages 42 to a pressure of about 24 bar and a temperature of about 200° C.

[0028] With continued reference to FIG. 1, the combustor section 20 is coupled in flow communication with the compressor section 18 and includes one or more combustors 52, each of which, in embodiments, includes one or more fuel nozzles 54. Although generally illustrated as having two combustors 52, it is envisioned that the combustor section 50 may have a single combustor 52 extending circumferentially about the longitudinal axis of the gas turbine engine 12, or any number of combustors 52 circumferentially spaced about one another about the longitudinal axis without departing from the scope of the invention. The fuel nozzles 54 receive compressed fluid Fc from the compressor section 18 and fuel 56 from one or more fuel supply systems 58 coupled to the fuel nozzles 54. The fuel nozzles 54 mix the compressed fluid Fc and the fuel 56 and ignite or otherwise combust the mixture of compressed fluid Fc and fuel 56 to create hot combustion gases Cg, which are exhausted or otherwise discharged from each combustor 52 and received by the turbine section 22. It is envisioned that the fuel 56 may be any suitable fuel for use with the gas turbine system 10 without departing from the scope of the invention. In one embodiment, the fuel 56 may be natural gas. In another non-limiting embodiment, the fuel 56 may be Hydrogen gas (H2). It is contemplated that when utilizing Hydrogen gas, the gas turbine system 10 may be a negative emissions system.

[0029] The turbine section 22 may include one or more turbine stages 60, each having a plurality of turbine blades 62 spaced circumferentially about a turbine shaft 64 that is rotatably supported within a turbine casing 66. In some embodiments, each turbine stage 60 may include a plurality of turbine vanes 68 arranged circumferentially about the turbine casing 66. It is envisioned that the turbine section 22 may include any number of turbine stages 60 depending on the design needs of the gas turbine system 10. and in some embodiments, may include between about one and about ten or more turbine stages 60. It is contemplated that the turbine stages 60 may alternate between sets of the turbine blades 62 and the sets of turbine vanes 68 in the direction of the flow of the hot combustion gases Cg through the turbine section 22. As can be appreciated, as the hot combustion gases Cg flow through each subsequent turbine stage 60 of the turbine section 22, the hot combustion gases700905-WO-l (17851-1500)Cg progressively expand and effectuate rotation of the turbine blades 62 in the turbine stages 60, which in turn, causes a corresponding rotation of the turbine shaft 64.

[0030] It is envisioned that the load 24 coupled to the turbine section 22 may be, but is not limited to only being, an electrical generator, a machine, and / or combinations thereof. Although generally illustrated as being adjacent to the turbine section 22 of the gas turbine engine 12, it is contemplated that the load 24 may be at any relative location relative to the turbine section 22, such as adjacent to the compressor section 18 of the gas turbine engine 12, without departing from the scope of the invention.

[0031] The exhaust section 26 may include an exhaust duct, exhaust treatment equipment, silencers, etc., and / or combinations thereof. In one non-limiting embodiment, the exhaust section 26 may include, and / or may direct, a flow of exhaust gas Eg from turbine section 22 through a heat exchanger and / or cooling system, such as a heat recovery steam generator (HRSG) 70 configured to transfer heat from the exhaust gas Eg to a fluid. In some embodiments, the fluid may be water that is used to generate steam to drive a steam turbine 74 of a combined cycle or cogeneration power plant 76. In embodiments, the gas turbine system 10 system may include one or more coolers 72, such as a direct contact cooler, oriented to spray a fluid directly into the exhaust gas Eg to effectuate cooling of the exhaust gas Eg.

[0032] Turning to FIG. 2A, in the exemplary embodiment, the gas turbine engine 12 includes a heat exchanger 80 that is in fluid and / or flow communication with the compressor section 18 for reducing or otherwise lowering a temperature of fluid F compressed and exhausted from one or more compressor stages 42 of the compressor section 18. In one non-limiting embodiment, the heat exchanger 80 is coupled to a first compressor stage 42a exhausting compressed fluid Fc to the heat exchanger 80 and a second compressor stage 42b for receiving the compressed fluid Fc from the heat exchanger 80. In this manner, fluid F flowing through the first compressor stage 42a is compressed to a first pressure Pl and temperature Tl, which in some embodiments, may be about 5 bar and about 191° C. Alternatively, the first pressure Pl and temperature Tl of the fluid compressed and exhausted by the first compressor stage 42a may be any other suitable pressure and temperature depending upon the design needs of the gas turbine system 10. The heat exchanger 80 is in fluid and / or flow communication with a cooling fluid 82 that is in thermal communication with the compressed fluid Fc flowing through the heat exchanger 80. As can be appreciated,700905-WO-l (17851-1500) compressed fluid Fc flowing through the heat exchanger 80 exchanges thermal energy (e.g., heat) with the cooling fluid 82, which effectuates a decrease in temperature of the compressed fluid Fc and a corresponding increase in temperature of the cooling fluid 82.

[0033] As can be appreciated, the temperature of the compressed fluid Fc exiting the heat exchanger 80 and delivered to the second compressor stage 42b may impact the performance (e.g., mechanical work produced, efficiency, etc.) of the gas turbine system 10. It is envisioned that the first pressure Pl and temperature T1 may be predefined values, or alternatively, may be continuously adjusted / controlled by the control system 14 depending on the design needs of the gas turbine system 10. It is contemplated that the temperature of the compressed fluid Fc exiting the heat exchanger 80 may be controlled by varying or otherwise changing a temperature and / or flow rate of the cooling fluid 82 through the heat exchanger 80. The temperature, pressure, and / or flowrate of the cooling fluid 82 through the heat exchanger 80 may be constant (e.g., predefined values) or may be continuously varied by the control system 14 based on by the temperature of the compressed fluid Fc exiting the heat exchanger 80. In one non-limiting embodiment, the cooling fluid 82 received by the heat exchanger 80 may have a temperature of about 25° C, a pressure of about 20 bar, and a flowrate of about 1000 Ib / s. In embodiments, the compressed fluid Fc exiting the heat exchanger 80 may have a second temperature of about 32° C and the temperature of the cooling fluid 82 exiting the heat exchanger 80 may be about 1 19° C. Although generally described herein as having one heat exchanger 80, it is envisioned that the gas turbine system 10 may include any number of heat exchangers 80. one or more of which may be between any of the compressor stages 42. It is envisioned that the cooling fluid 82 may be circulated within a cooling fluid loop in fluid and / or flow7communication with a cooling fluid reservoir 84 disposed on, or remote from, the gas turbine system 10.

[0034] With reference to FIGS. 1 and 2A, the gas turbine system 10 includes a DAC module 90 in flow communication with the heat exchanger 80 and oriented to capture or otherwise separate carbon dioxide from the cooled, compressed fluid Fc exiting the heat exchanger 80 and discharge compressed fluid that has been filtered or otherwise scrubbed of carbon dioxide to the second compressor stage 42b. As opposed to the concentration of carbon dioxide in ambient air, compressing the fluid F effectuates an increase in partial pressure, and therefore, concentration, of carbon dioxide within the fluid F per unit of volume (FIG. 3). In this manner, the DAC module 90 is able to capture or otherwise separate a greater700905-WO-l (17851-1500) amount of carbon dioxide from the fluid, such as air, thus facilitating an increase in the efficiency of carbon dioxide adsorption and desorption and enabling a corresponding decrease in size of the DAC module 90 as compared to a DAC module processing ambient air at standard temperature and pressure (e.g., atmospheric conditions). As can be appreciated, due to the fluid F flowing through the DAC module 90 being compressed, little to no vacuum is needed to effectuate a differential pressure on then fluid F flowing through the DAC module 90, thus further facilitating increasing the efficiency of the DAC module 90.

[0035] With additional reference to FIG. 2B, it is envisioned that the gas turbine system 10 may include a secondary heat exchanger 80a that is disposed upstream of the heat exchanger 80. In the exemplary' embodiment, the secondary' heat exchanger 80a is in fluid and / or flow communication with the first compressor stage 42a for reducing or otherwise lowering a temperature of the compressed fluid Fc exhausted from the first compressor stage 42. The cooled compressed fluid Fc is delivered to the heat exchanger 80 for further cooling before being received by the DAC module 90. The secondary heat exchanger 80a is in fluid and / or flow communication with DAC module 90 and the second compressor stage 42b. In the exemplary embodiment, cooled compressed fluid Fc discharged from the DAC module 90 is received by the secondary heat exchanger 80a and exchanges thermal energy' (e.g. , heat) with the compressed fluid Fc discharged from the first compressor stage 42a. The temperature of the compressed fluid Fc received from the first compressor stage 42a is higher than the temperature of the cooled compressed fluid Fc received from the DAC module 90. which effectuates a decrease in temperature of the compressed fluid Fc received from the first compressor stage 42a and an increase in temperature of the cooled compressed fluid Fc received from the DAC module 90 and delivered to the second compressor stage 42b. With reference to FIG. 2C, it is contemplated that the secondary heat exchanger 80a may receive compressed fluid Fc from the last compression stage 42 of the compressor section 18 and discharge heated compressed fluid Fc to the combustor section 20. It is envisioned that the secondary heat exchanger 80a may be any suitable heat exchanger, which in embodiments may be a air-to-air heat exchanger, without departing from the scope of the disclosure.

[0036] It is envisioned that the cooling fluid 82 exiting the heat exchanger 80 may be circulated within the DAC module 90 to effectuate desorption of the carbon dioxide CO2 adsorbed by the sorption material within the DAC module 90. As described hereinabove,700905-WO-l (17851-1500) while flowing through the heat exchanger 80, the cooling fluid 82 absorbs heat from the compressed fluid Fc passing through the heat exchanger 80. In embodiments, the temperature of the cooling fluid 82 increases from an initial temperature of about 25° C to a temperature of about 119° C when exiting the heat exchanger 80. The heated cooling fluid 82 is channeled through a second heat exchanger 94 coupled to the DAC module 90, wherein heat from the heated cooling fluid 82 is transferred to the sorbent material within the DAC module 90 to desorb or otherwise release the adsorbed carbon dioxide from the sorbent material. In one non-limiting embodiment, the cooling fluid 82 exiting the second heat exchanger 94 has a temperature of about 30° C, and transfers about 166 MW to the DAC module 90. In some embodiments, the cooling fluid 82 exiting the second heat exchanger 94 is returned to the cooling fluid reservoir 84, although it is contemplated that the cooling fluid 82 may be discharged to any suitable location and may be part of an open loop. It is envisioned that the flow of the cooling fluid 82 through the second heat exchanger 94 may be controlled or otherwise regulated by the control system 14. As can be appreciated, regulating the flow of the cooling fluid 82 through the second heat exchanger 94 controls or otherwise regulates a temperature within the DAC module 90 and as a result, controls or otherwise facilitates increasing an efficiency or an amount of carbon dioxide desorbed from the sorbent material.

[0037] The carbon dioxide CO2 captured from the compressed fluid Fc and desorbed by the DAC module 90 is transferred or otherwise transported to a storage tank (not shown) for storage and / or is utilized for one or more processes involving the use of carbon dioxide CO2. In one non-limiting embodiment, the DAC module 90 captures about 3,192 Ib / h or 12,683 tonne / y of carbon dioxide CO2 from fluid F passing through the first compressor stage 42a at a mass flowrate of about 2,140 Ib / s with a carbon dioxide CO2 concentration of about 0.046% (resulting in a carbon dioxide CO2 mass flowrate of about 0.98 Ib / s). In some embodiments, the DAC module 90 includes about a 90% carbon dioxide CO2 capture rate. As can be appreciated, the amount of carbon dioxide CO2 captured by the DAC module 90 and the efficiency of the DAC module 90 may depend upon the operating conditions of the gas turbine system 10, such as the characteristics of the fluid F drawn into the compressor section 18, the characteristics of the cooling fluid 82 flowing through the heat exchanger 80 and into the DAC module 90, the characteristics of the compressed fluid Fc entering the DAC module 90, etc.700905-WO-l (17851-1500)

[0038] With reference to FIGS. 4 and 5, it is envisioned that the gas turbine system 10 may include and / or utilize any suitable DAC module or system without departing from the scope of the invention, such as, but not limited to, a solvent-based DAC, a sorbent-based DAC, etc., a sliding cartridge DAC. and / or combinations thereof. In one non-limiting embodiment, the DAC module 90 includes a plurality of movable adsorption assemblies 92 that may selectively move adsorption modules 93 between a first duct 96 and a second duct 98. In one non-limiting embodiment, the adsorption modules 93 may include one or more selectively removable sorbent cartridges (not shown). In this manner, a sorbent cartridge may be selectively removed from the adsorption module 94 for service, inspection, and / or replacement, for example.

[0039] The DAC module 90 is configured to translate the adsorption modules 93 in a staggered arrangement within the first duct 96 and the second duct 98 to position one or more of the adsorption modules 93 in the first duct 96 to adsorb carbon dioxide from the compressed fluid Fc while one or more of the adsorption modules 93 are positioned in the second duct 98 to desorb the carbon dioxide captured by the adsorption modules 93. In some embodiments, the adsorption modules 93 are translatable in a direction that is substantially transverse to a longitudinal axis defined by the first duct 96 and the second duct 98, while also translating in a direction that is substantially parallel to one another.

[0040] In embodiments, the adsorption modules 93 may be coupled entirely within the first duct 96 and / or the second duct 98 during operation of the gas turbine system 10. The first duct 96 defines a flow path 100 that extends longitudinally between an inlet 102 and an outlet 104. The second duct 98 defines a flow path 106 that extends longitudinally between an inlet 108 and an outlet 110. It is envisioned that the first duct 96 and the second duct 98 may be coupled adjacent to one another, sharing a common wall 112, or alternatively, may be in a spaced relation to one another without departing from the scope of the invention. The inlet 102 of the first duct 96 is in fluid and / or flow communication with one or more coolers 114, which in some embodiments, may be the heat exchanger 80, or alternatively, may be in addition to the heat exchanger 80. As can be appreciated, the one or more coolers 114 facilitate cooling or otherwise reducing the temperature of the compressed fluid Fc received by the inlet 102 to facilitate enhancing the adsorption ability of the sorbent material of the adsorption modules 93.700905-WO-l (17851-1500)

[0041] In operation, the compressed fluid Fc is received by the inlet 102 of the first duct 96, flows through the first duct 102 including the one or more coolers 114 and the one or more adsorption modules 93 positioned within the first duct 102. The compressed fluid Fc is discharged from the outlet 104 of the first duct 96, wherein is it directed or otherwise transferred to the second compressor stage 42b or to one or more other downstream components of the gas turbine system 10. As can be appreciated, when one or more of the adsorption modules 93 are within the first duct 96, the compressed fluid Fc flows through, or otherwise about, the adsorption modules 93 where carbon dioxide CO2 is captured or otherwise adsorbed from the compressed fluid Fc by the sorbent material of the adsorption modules 93. The scrubbed or otherwise filtered compressed fluid Fc is discharged through the outlet 104 of the first duct 96 and received by the second compressor stage 42b or one or more other downstream components of the gas turbine system 10. As described hereinabove, it is envisioned that the filtered compressed fluid Fc may be received by the secondary heat exchanger 80a (FIG. 2B) to heat or otherwise increase a temperature of the filtered compressed fluid Fc before being received by the second compressor stage 42b or one or more other downstream components of the gas turbine system 10. Although generally described as being interposed between the first compressor stage 42a and the second compressor stage 42b, it is envisioned that the secondary heat exchanger 80a may be interposed between the last stage 42 of the compressor section 18 and the combustor section 20 to heat or otherwise increase a temperature of the filtered compressed fluid Fc before being received by the combustor section 20.

[0042] The second duct 98 is in thermal communication with one or more heaters 116. which in embodiments, may be the second heat exchanger 94 or may be in addition to the second heat exchanger 94. As can be appreciated, the one or more heaters 116 facilitate heating or otherwise increasing the temperature within the second duct 98 and / or fluid flowing within the second duct 98 to aid desorption of carbon dioxide CO2 from the sorbent material of the adsorption modules 93 disposed within the second duct 98. In operation, fluid flowing through the second duct 98 (e.g, steam supplied by the steam turbine 74, etc.) or the temperature within the second duct 98 is increased through heat transfer with the one or more heaters 116 and the sorbent material of the adsorption modules 93 is heated or otherwise increased in temperature to desorb CO2 captured by the sorbent material. The desorbed CO2 is transferred or otherwise transported to a storage tank (not shown) for storage or is utilized700905-WD-l (17851-1500) for one or more processes involving the use of carbon dioxide CO2. The fdtered or otherwise scrubbed fluid discharged from the outlet 112 of the second duct 98 to atmosphere or transferred or otherwise transported to one or more other downstream components of the gas turbine system 10.

[0043] It is contemplated that the control system 14 may control movement and / or translation of the movable adsorption assemblies 92, and therefore, movement and / or translation of the adsorption modules 93 relative to the first duct 96 and the second duct 98. It is envisioned that the control system 14 may control the movement of the movable adsorption assemblies 92 based on various parameters, such as, but not limited to, rates of adsorption, rates of desorption, temperature, flow rate, etc. and / or combinations thereof, that may be measured or otherwise determined by one or more sensors 118 coupled to the DAC module 90 and control system 14.

[0044] With continued reference to FIGS. 4 and 5, it is envisioned that the DAC module 90 may include a thermal control system 120 controlling or otherwise regulating the temperature of the compressed fluid Fc received by the inlet 102 of the first duct 96 to facilitate enhancing adsorption of carbon dioxide CO2 from the compressed fluid Fc and control or otherwise regulate the temperature within the second duct 98 to facilitate enhancing desorption of the carbon dioxide CO2 from the adsorption modules 93. As described hereinabove, the DAC module 90 may include one or more movable adsorption assemblies 92. For purposes of brevity, only one movable adsorption assembly 92 is illustrated in FIG. 5 and described in detail hereinbelow.

[0045] In some embodiments, the thermal control system 120 includes a cooling system 130 in thermal communication with the first duct 96 and a heating system 132 in thermal communication with the second duct 98. The cooling system 130 includes a cooling supply system 134 coupled to a cooling system heat exchanger 136 within the first duct 96 of an adsorption unit 138 of the DAC module 90. The heating system 132 includes a heating supply system 140 coupled to a heating system heat exchanger 142 within the second duct 98 of a desorption unit 144 of the DAC module 90. In some embodiments, the cooling system heat exchanger 136 is separate from the heating system heat exchanger 142 and may be separated by an intermediate wall 146 between the first duct 96 of the adsorption unit 138 and the second duct 98 of the desorption unit 144. It is contemplated that the thermal control system 120 may include a heat exchange system 148 having a heat exchanger 150 in the first700905-WO-l (17851-1500) duct 96 of the adsorption unit 138 and a heat exchanger 152 in the second duct 98 of the desorption unit 144. The heat exchange system 148 transfers or otherwise exchanges heat between the first duct 96 of the adsorption unit 138 and the second duct 98 of the desorption unit 144 via heat exchange between the heat exchangers 150, 152. Independently or in combination with one another, the cooling system heat exchanger 136 and the heat exchanger 150 of the adsorption unit 138 provide cooling of the compressed fluid Fc flowing through the first duct 96 of the adsorption unit 138 and / or cooling of the adsorption modules 93, while the heating system heat exchanger 142 and the heat exchanger 152 of the desorption unit 144 provide heating in the second duct 98 of the desorption unit 144 and / or heating of the adsorption modules 93. In another non-limiting embodiment, the cooling system heat exchanger 136 and the heat exchanger 150 of the adsorption unit 138 are integrated with one another to define a combined or common heat exchanger and / or the heating system heat exchanger 142 and the heat exchanger 152 of the desorption unit 144 are integrated with one another to define a combined or common heat exchanger. As described hereinabove, the cooling provided to the first duct 96 of the adsorption unit 138 and / or the adsorption modules 93 facilitates enhancing adsorption of CO2 by regulating or otherwise controlling a temperature within the first duct 96 and / or the adsorption modules 93 to be within a predetermined temperature range for the adsorption process. Similarly, the heating provided to the second duct 98 of the desorption unit 144 and / or the adsorption modules 93 facilitates enhancing desorption of CO2 by regulating or otherwise controlling a temperature within the second duct 98 and / or the adsorption modules 93 to be within a predetermined temperature range for the desorption process. In embodiments, the temperature within the first duct 96, the second duct 98, and / or the adsorption modules may be controlled or otherwise regulated by the control system 14.

[0046] With reference to FIG. 5. the cooling system 130 circulates a cooling fluid 160 from the cooling supply system 134 through the cooling system heat exchanger 136. In embodiments, the cooling supply system 134 may receive the cooling fluid 160 in an already cooled state 161 within a suitable temperature range, such that further temperature adjustments are not performed by any coolers or heat exchangers in the cooling supply system 134. It is envisioned that the cooling supply system 134 may receive the cooling fluid 160 from another cooled fluid source in the gas turbine system 10, such as, but not limited to, cooled water from a cooling tower, the cooling fluid 82 exiting the heat exchanger700905-WO-l (17851-1500)80, etc., and / or combinations thereof. In some embodiments, the cooling supply system 134 may receive the cooling fluid 160 at a temperature outside of a desired temperature range, in which case the cooling supply system 134 may perform additional temperature control (e.g. , heating and / or cooling) on the cooling fluid 160 to adjust the temperature of the cooling fluid within the suitable temperature range. In this manner, the cooling fluid 160 may be cooled by one or more additional coolers and / or heat exchangers of the cooling supply system 134 and / or the gas turbine system 10, and / or the cooling fluid 160 may be heated by one or more additional heaters and / or heat exchangers of the cooling supply system 134 and / or the gas turbine system 10. In another non-limiting embodiment, the cooling fluid 160 may be cooled and / or heated by the heat exchanger 80.

[0047] It is envisioned that the cooling supply system 134 may include a single heat exchanger and / or single fluid system 164 and / or a multi-heat exchange and / or multi-fluid system 166 supplying the cooling fluid 160 at the suitable temperature range for circulation and cooling through the cooling system heat exchanger 136. In this manner, the cooling fluid 160 may be the only cooling fluid (e.g., liquid coolant such as water) used by the single fluid system 164 and / or the cooling fluid 160 may be cooled by another cooling fluid (e.g., liquid or gas) in the multi-fluid system 166.

[0048] In the exemplar}' embodiment, the heating supply system 140 is coupled to the heating supply system heat exchanger 142 within the second duct 98 of the desorption unit 144. The heating supply system 140 circulates a heating fluid 168 through the heating supply system heat exchanger 142. In some embodiments, the heating supply system 140 may receive the heating fluid 168 in an already heated state 169 within a suitable temperature range, such that additional temperature adjustments are not performed by any heaters or heat exchangers in the heating supply system 140. It is envisioned that the heating supply system 140 may receive the heating fluid 168 from another heated fluid source in the gas turbine system 10, such as, but not limited to. heated water and / or steam from the HRSG 70 (FIG. 1), the steam turbine 74 (FIG. 1), a boiler (not shown), the heat exchanger 80 (FIG. 2), the second heat exchanger 94 (FIG. 2), etc., and / or combinations thereof. In another nonlimiting embodiment, the heating supply system heat exchanger 142 may be the heat exchanger 80 or the second heat exchanger 94. In embodiments, the heating supply system 140 may receive the heating fluid 168 at a temperature outside of a desired temperature range, in which case the heating supply system 140 may perform additional temperature control700905-WO-l (17851-1500)(e.g., heating and / or cooling) on the heating fluid 168 to adjust the temperature within the suitable temperature range. In this manner, the heating fluid 168 may be heated by one or more additional heaters and / or heat exchangers of the heating supply system 140 and / or the gas turbine system 10. In embodiments, the heating fluid 168 may be heated by the heat exchanger 80 and / or the second heat exchanger 94.

[0049] It is envisioned that the heating supply system 140 may include a single heat exchange and / or single fluid system 170 and / or a multi-heat exchange and / or multi-fluid system 172 supplying the heating fluid 168 at the suitable temperature range for circulation and heating through the heating supply system heat exchanger 142. In this manner, the heating fluid 168 may be the only heating fluid (e.g., liquid or gas) used by the single fluid system 170 and / or the heating fluid 168 may be heated by another heating fluid (e.g., liquid and / or gas) in the multi -fluid system 172. In some embodiments, the heating supply system 140 may use a heated water, steam, and / or another heated fluid for circulation directly through the heating supply system heat exchanger 142 as the heating fluid 168, and / or indirectly as another heating fluid in another heat exchanger to provide heating of the heating fluid 168 and / or combinations thereof.

[0050] In embodiments, the heat exchange system 148 may be used to provide both cooling in the adsorption unit 138 via the heat exchanger 150 and heating in the desorption unit 144 via the heat exchanger 152. In some embodiments, the heat exchangers 150, 152 of the heat exchange system 148 are along a closed-loop heat transfer circuit 174, which may be in a housing or body 176 of the heat exchange system 148. The closed-loop heat transfer circuit 174 circulates a working fluid through the heat exchanger 150. a compressor 180. the heat exchanger 152, an expansion valve 182, and back to the heat exchanger 150. In operation, the compressed fluid Fc flows through the first duct 96 of the adsorption unit 138 and transfers heat to the working fluid circulating through the heat exchanger 150. evaporating the working fluid to generate a warm gas or vapor. In this manner, the transfer of heat from the compressed fluid Fc to the working fluid facilitates enhancing cooling the compressed fluid Fc while the adsorption module 93 adsorbs CO2 from the compressed fluid Fc. The warm gas then flows through the compressor 180, which compresses the warm gas to generate a hot gas, which flows through the heat exchanger 152, transferring heat from the hot gas to the adsorption module 93 for desorbing the CO2 captured by the adsorption module 93. As can be appreciated, as the heat transfers to the adsorption module 93, the hot gas700905-WO-l (17851-1500) cools and condenses within the heat exchanger 152, producing a warm liquid. The warm liquid flows through the expansion valve 182, which causes an expansion of the warm liquid to provide cooling and generate a cool liquid. The cool liquid flows through the heat exchanger 150 and provides cooling to the compressed fluid Fc in the first duct 96 of the adsorption unit 138. In this manner, the cool liquid cools the compressed fluid Fc to a suitable temperature to facilitate the adsorption of CO2 in the adsorption module 93, while also becoming heated to generate the warm gas to continue the cycle in the closed-loop heat transfer circuit 174 of the heat exchange system 148.

[0051] With continued reference to FIG. 5, it is envisioned that the adsorption unit 138 may output the treated compressed fluid Fc after adsorption of the CO2 in the adsorption modules 93 to the second stage 42b of the gas turbine engine 12. In this manner, the cooling system 130 cools the compressed fluid Fc to a suitable temperature for the compressed fluid Fc and / or the sorbent material in the adsorption module 93 to facilitate enhancing the adsorption process in the adsorption module 93 compared to uncooled compressed fluid Fc. Similarly, the heating system 132 heats the sorbent material in the adsorption module 93 to facilitate enhancing the desorption process in the adsorption module 93 compared to unheated sorbent material.

[0052] Turning to FIG. 6, in the exemplary embodiment, the control system 14 includes a computer 600, which in embodiments, may be coupled to a display 602 that displays one or more user interfaces 604. The control system 14 may be a desktop computer or a tower configuration with the display, may be a laptop computer, may be integrated into a system control panel, etc. The control system 14 includes a processor 606 which executes software stored in a emory 608. The memory 608 may store data or other information regarding the gas turbine system 10. In addition, the memory' 608 may store one or more algorithms 610 and / or software applications 612 to be executed by the processor 606.

[0053] A network interface 614 enables the control system 14 to communicate with a variety of other devices and systems via the Internet. The network interface 614 may connect the control system 14 to the Internet via a wired or wireless connection. Additionally, or alternatively, the communication may be via an ad-hoc Bluetooth® or wireless network enabling communication with a wide-area network (WAN) and / or a local area network (LAN). The network interface 614 may connect to the Internet via on or more gateway, routers, and network address translation (NAT) devices. The network interface 614 may700905-WO-l (17851-1500) communicate with a cloud storage system 616, in which further data and / or information associated with the gas turbine system 10 may be stored. The cloud storage system 616 may be remote from or on the premises of a control room. An input module 618 receives inputs from an input device such as, for example, a keyboard, a mouse, or voice commands. An output module 620 connects the processor 606 and the memory 608 to a variety of output devices, such as, for example, the display 602. In embodiments, the control system 14 may include its own display (not shown), which may be a touchscreen display.

[0054] With reference to FIG. 7, a method of operating a gas turbine engine is illustrated and generally identified by reference numeral 700. Initially, a fluid, such as air. having first characteristics is channeled 702 to a first compressor stage of a gas turbine engine. The fluid flowing through the first compressor stage is compressed 704 prior to it being discharged as a compressed fluid having second characteristics. The compressed fluid and a cooling fluid having first characteristics are received 706 within a heat exchanger. Heat is exchanged 708 between the compressed fluid and the cooling fluid flowing through the heat exchanger to cool the compressed fluid and heat the cooling fluid. The cooled compressed fluid having third characteristics and the heated cooling fluid having second characteristics are discharged 710 from the heat exchanger. The cooled compressed fluid is received 712 within a DAC module and the heated cooling fluid is received within a second heat exchanger of the DAC module. Carbon dioxide is adsorbed 714 from the cooled compressed fluid flowing through an adsorbent module of the DAC module. Heat is then transferred 716 between the sorbent material of the adsorbent module and the heated cooling fluid flowing through the second heat exchanger to desorb carbon dioxide from the sorbent material. The desorbed carbon dioxide is transferred or transported 718 to downstream components of the gas turbine system, and filtered cooled compressed fluid is received 720 by a second compressor stage of the gas turbine engine. The filtered cooled compressed fluid flowing through the remaining compressor stages of the gas turbine engine is further compressed 722, and a mixture of fuel and the compressed filtered cooled compressed fluid is ignited 724 in a combustor section of the gas turbine engine to generate hot combustion gases. Optionally, natural gas may be mixed 726 with the compressed filtered cooled compressed fluid and then ignited 724. Optionally, hydrogen gas may be mixed 728 with the further compressed filtered cooled compressed fluid and then ignited 724. The hot combustion gases are received 730 by a turbine section of the gas turbine engine to effectuate rotation of the700905-WO-l (17851-1500) turbine section or otherwise drive a load. As can be appreciated, the above-described method 700 may be repeated as many times as necessary and the method 700 may be performed in any order without departing from the scope of the present invention.

[0055] Although the description of computer-readable media contained herein refers to solid-state storage, it should be appreciated by those skilled in the art that computer-readable storage media can be any available media that can be accessed by the processor 606. That is, computer readable storage media may include non-transitory, volatile, and non-volatile, removable and non-removable media implemented in any method or technology for storage of information such as for example, computer readable instructions, data structures, program modules or other data. For example, computer-readable storage media may include RAM, ROM, EPROM, EEPROM, flash memoiy or other solid-state memory technology, CD- ROM, DVD, Blu-Ray or other optical storage, magnetic cassettes, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other medium which may be used to store the desired information, and which may be accessed by the control system 14.

[0056] The gas turbine system according to exemplary embodiments as described herein facilitates increasing a yield of carbon dioxide captured for a given energy input. When the fluid entering the compressor stage of the gas turbine engine is compressed, the partial pressure of carbon dioxide in the volume of fluid is increased. The increased partial pressure of carbon dioxide within the compressed fluid, when channeled to the DAC module, facilitates increasing an amount of carbon dioxide captured by the DAC module compared to ambient air or uncompressed fluid channeled to known DAC modules. As such, the size of the DAC module may be decreased, and the amount of energy expended to capture a given amount of carbon dioxide is reduced. The first and second heat exchangers of the gas turbine system cooperate to facilitate cooling of the compressed fluid channeled to the DAC module and heating of the adsorption modules of the DAC module to desorb captured carbon dioxide As such, an amount of energy needed to heat and desorb carbon dioxide from the adsorption modules is reduced compared to known DAC modules. The increased pressure of the fluid channeled to the DAC module compared to ambient air reduces and / or otherwise eliminates the need to draw' a vacuum within the DAC module to desorb carbon dioxide, further facilitating reducing an amount of energy needed to desorb carbon dioxide from the adsorption modules.700905-WO-l (17851-1500)

[0057] The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. Modifications, which fall within the scope of the present invention, will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims. The systems described herein are not limited to the specific embodiments described herein, but rather portions of the various systems may be utilized independently and separately from other systems described herein.

[0058] Although specific features of vanous embodiments of the invention may be shown in some drawings and not in others, this is for convenience only. Moreover, references to “one embodiment” in the above description are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the recited features. In accordance with the principles of the invention, any feature of a drawing may be referenced and / or claimed in combination with any feature of any other drawing. Further aspects of the invention are provided by the subject matter of the following clauses:

[0059] A gas turbine engine includes a compressor section including a first compressor stage for compressing a fluid and a second compressor stage in flow communication with the first compressor stage and oriented to further compress the compressed fluid. The gas turbine engine also includes a direct air capture (DAC) module in flow communication with the first compressor stage and the second compressor stage. The DAC module receives compressed fluid from the first compressor stage, adsorbs carbon dioxide from the compressed fluid to generate a filtered compressed fluid, and discharges the filtered compressed fluid to the second compressor stage.

[0060] The gas turbine engine in accordance with any of the preceding clauses, w herein the gas turbine engine may include a first heat exchanger in flow communication with the first compressor stage and the DAC module. The first heat exchanger reduces a temperature of compressed fluid received from the first compressor stage and delivers cooled compressed fluid to the DAC module.

[0061] The gas turbine engine in accordance with any of the preceding clauses, w herein the first heat exchanger exchanges heat between compressed fluid received from the first compressor stage and cooling fluid circulating through the first heat exchanger.700905-WO-l (17851-1500)

[0062] The gas turbine engine in accordance with any of the preceding clauses, wherein the DAC module may include a second heat exchanger in flow communication with the first heat exchanger. The second heat exchanger receives heated cooling fluid from the first heat exchanger and desorbs adsorbed carbon dioxide.

[0063] The gas turbine engine in accordance with any of the preceding clauses, wherein the DAC module may include an adsorption module to adsorb carbon dioxide from cooled compressed fluid in contact with the adsorption module.

[0064] The gas turbine engine in accordance with any of the preceding clauses, wherein the second heat exchanger may be in thermal communication with the adsorption unit. The second heat exchanger exchanges heat between heated cooling fluid and the adsorption module to desorb adsorbed carbon dioxide.

[0065] The gas turbine engine in accordance with any of the preceding clauses, wherein the adsorption module is selectively movable between a first position in flow communication with cooled compressed fluid and a second position in thermal communication with the second heat exchanger.

[0066] The gas turbine engine in accordance with any of the preceding clauses, wherein the direct air capture module may include a carbon dioxide outlet to discharge desorbed carbon dioxide from the direct air capture module.

[0067] The gas turbine engine in accordance with any of the preceding clauses, wherein the gas turbine engine may operate using hydrogen gas and the gas turbine engine is a component of a negative emissions system.

[0068] In another aspect, a gas turbine system includes a gas turbine engine including a compressor section. The compressor section includes a first compressor stage for compressing a fluid and a second compressor stage in fluid communication with the first compressor stage and oriented to further compress the compressed fluid. The gas turbine engine also includes a direct air capture module in fluid communication with the first compressor stage and the second compressor stage. The direct air capture module receives compressed fluid from the first compressor stage, adsorbs carbon dioxide from the compressed fluid to generate a filtered compressed fluid, and discharges the filtered compressed fluid to the second compressor stage. A steam turbine is operably coupled to the gas turbine engine, and a control system is operably coupled to the gas turbine engine. The control system includes a memory and a processor. The memory stores instructions,700905-WO-l(17851-1500) when executed, cause the processor to regulate a temperature within the direct air capture module.

[0069] The gas turbine system in accordance with any of the preceding clauses, wherein the gas turbine system may include a first heat exchanger in fluid communication with the first compressor stage and the direct air capture module, the first heat exchanger configured to cool compressed fluid received from the first compressor stage and deliver cooled compressed fluid to the direct air capture module.

[0070] The gas turbine system in accordance with any of the preceding clauses, wherein the gas turbine system may include a cooling fluid in fluid communication with the first heat exchanger. The first heat exchanger exchanges heat between the compressed fluid received from the first compressor stage and the cooling fluid to cool the compressed fluid and heat the cooling fluid.

[0071] The gas turbine system in accordance with any of the preceding clauses, wherein the direct air capture module may include a second heat exchanger in fluid communication with the first heat exchanger. The second heat exchanger receives the heated cooling fluid from the first heat exchanger and desorbs the adsorbed carbon dioxide.

[0072] The gas turbine system in accordance with any of the preceding clauses, wherein the memory may store thereon further instructions, when executed, cause the processor to regulate the temperature within the DAC module by controlling a flow of the heated cooling fluid through the second heat exchanger.

[0073] In yet another aspect, a method of operating a gas turbine engine includes drawing a fluid into a first compressor stage of a gas turbine engine, and compressing, via the first compressor stage, the fluid drawn into the first compressor stage. The method also includes discharging compressed fluid, adsorbing, via a direct air capture (DAC) module, carbon dioxide from the compressed fluid to generate filtered compressed fluid, and discharging the filtered compressed fluid to a second compressor stage of the gas turbine engine.

[0074] The method in accordance with any of the preceding clauses, wherein the method may include cooling, via a first heat exchanger in flow communication with a cooling fluid, the compressed fluid to generate a cooled compressed fluid and a heated cooling fluid.

[0075] The method in accordance with any of the preceding clauses, wherein the method may include exchanging heat, via a second heat exchanger in flow communication with the first heat exchanger, between heated cooling fluid and the DAC module to desorb carbon700905-WO-l (17851-1500) dioxide adsorbed from the cooled compressed fluid.

[0076] The method in accordance with any of the preceding clauses, wherein the method may include selectively moving the adsorption module between a first position in flow communication with cooled compressed fluid and a second position in thermal communication with the second heat exchanger.

[0077] The method in accordance with any of the preceding clauses, wherein the method may include igniting a mixture of filtered compressed fluid and hydrogen gas to drive the turbine section.

Claims

700905-WO-l(17851-1500)CLAIMSWhat is claimed is:

1. A gas turbine engine, comprising: a compressor section, including: a first compressor stage configured to compress a fluid; and a second compressor stage in flow communication with the first compressor stage and configured to further compress the compressed fluid; and a direct air capture (DAC) module in flow communication with the first compressor stage and the second compressor stage, the DAC module configured to: receive compressed fluid from the first compressor stage; adsorb carbon dioxide from the compressed fluid to generate a filtered compressed fluid; and discharge the filtered compressed fluid to the second compressor stage.

2. The gas turbine engine according to Claim 1, further comprising a first heat exchanger in flow communication with the first compressor stage and the DAC module, the first heat exchanger configured to reduce a temperature of compressed fluid received from the first compressor stage and deliver cooled compressed fluid to the DAC module.

3. The gas turbine engine according to Claim 2, wherein the first heat exchanger is configured to exchange heat between compressed fluid received from the first compressor stage and cooling fluid circulating through the first heat exchanger .

4. The gas turbine engine according to Claim 3, wherein the DAC module further includes a second heat exchanger in flow communication with the first heat exchanger, the second heat exchanger configured to receive heated cooling fluid from the first heat exchanger, and desorb adsorbed carbon dioxide.

5. The gas turbine engine according to Claim 4, wherein the DAC module further includes an adsorption module configured to adsorb carbon dioxide from cooled compressed fluid in contact with the adsorption module.700905-WO-l(17851-1500)6. The gas turbine engine according to Claim 5, wherein the second heat exchanger is in thermal communication with the adsorption module, the second heat exchanger configured to exchange heat between heated cooling fluid and the adsorption module to desorb adsorbed carbon dioxide.

7. The gas turbine engine according to Claim 6, wherein the adsorption module is selectively movable between a first position in flow communication with cooled compressed fluid and a second position in thermal communication with the second heat exchanger.

8. The gas turbine engine according to Claim f , wherein the DAC module further includes a carbon dioxide outlet configured to discharge desorbed carbon dioxide from the DAC module.

9. The gas turbine engine according to Claim 1, wherein the gas turbine engine operates using natural gas.

10. The gas turbine engine according to Claim 1, wherein the gas turbine engine operates using hydrogen gas and the gas turbine engine is a component of a negative emissions system.

11. A gas turbine system, comprising: a gas turbine engine, including: a compressor section, including: a first compressor stage configured to compress a fluid; and a second compressor stage in flow communication with the first compressor stage and configured to further compress the compressed fluid; and a direct air capture (DAC) module in flow communication with the first compressor stage and the second compressor stage, the DAC module configured to receive compressed fluid from the first compressor stage, adsorb carbon dioxide700905-WO-l(17851-1500) from the compressed fluid to generate a fdtered compressed fluid, and discharge the filtered compressed fluid to the second compressor stage; a steam turbine operably coupled to the gas turbine engine; and a control system operably coupled to the gas turbine engine and including a memory and a processor, the memory storing instructions when executed, cause the processor to regulate a temperature within the DAC module.

12. The gas turbine system according to Claim 11. wherein the gas turbine system further includes a first heat exchanger in flow communication with the first compressor stage and the DAC module, the first heat exchanger configured to reduce a temperature of compressed fluid received from the first compressor stage and deliver cooled compressed fluid to the DAC module.

13. The gas turbine system according to Claim 12, wherein the first heat exchanger is configured to exchange heat between compressed fluid received from the first compressor stage and cooling fluid circulating through the first heat exchanger.

14. The gas turbine system according to Claim 13, wherein the DAC module further includes a second heat exchanger in flow communication with the first heat exchanger, the second heat exchanger configured to receive heated cooling fluid from the first heat exchanger and desorb adsorbed carbon dioxide.

15. The gas turbine system according to Claim 14, wherein the memory stores thereon further instructions, when executed, cause the processor to regulate the temperature within the DAC module by controlling a flow of heated cooling fluid through the second heat exchanger.

16. A method of operating a gas turbine engine, comprising: channeling a fluid into a first compressor stage of a gas turbine engine; compressing, via the first compressor stage, the fluid entering the first compressor stage and discharging compressed fluid;700905-WO-l (17851-1500) adsorbing, via a direct air capture (DAC) module, carbon dioxide from the compressed fluid to generate fdtered compressed fluid; and discharging the fdtered compressed fluid to a second compressor stage of the gas turbine engine.

17. The method according to Claim 16, further comprising cooling, via a first heat exchanger in flow communication with a cooling fluid, compressed fluid to generate a cooled compressed fluid and a heated cooling fluid.

18. The method according to Claim 17, further comprising exchanging heat, via a second heat exchanger in flow communication with the first heat exchanger, between the heated cooling fluid and the DAC module to desorb carbon dioxide adsorbed from the cooled compressed fluid.

19. The method according to Claim 18, further comprising selectively moving the adsorption module between a first position in flow communication with cooled compressed fluid and a second position in thermal communication with the second heat exchanger.

20. The method according to Claim 18, further comprising igniting a mixture of filtered compressed fluid and hydrogen gas to drive the turbine section.

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