Injector device with afterburner chamber and turbomachine

Abstract

Device (50, 70, 90) comprising: a reaction chamber (22, 52, 72, 92) arranged between a first turbine stage (18) of a power generation system (10) and a subsequent turbine stage (24) of the power generation system (10), each turbine stage (18, 24) having a turbine guide apparatus (44) and a turbine rotor blade row; several injectors (54, 74, 76, 94), wherein the injectors (54, 74, 76, 94) have at least one guide vane injector (54, 74, 94) on a neck (46) tapering in the fluid flow direction of the fluids through the reaction chamber (52) and the turbine guide vane (44) of the subsequent turbine stage (24), wherein the at least one guide vane injector (54, 74, 94) is configured to discharge fuel (32) and / or carrier gas in a discharge direction which has a directional component opposite to the fluid flow direction; a line (56) in fluid connection with a fuel supply line (34) and in fluid connection with the multiple injectors (54, 74, 76, 94), wherein the line (56) supplies at least fuel (32) to the reaction chamber (22, 52, 72, 92) through the multiple injectors (54, 74, 76, 94); at least one valve (60, 68, 78, 98) for controlling the amount of fuel (32) supplied to the injectors (54, 74, 76, 94) from the fuel supply line (34), which is arranged between the fuel supply line (34) and the line (56); a control device (64) which is operatively connected to the at least one valve (60, 68, 78, 98); a temperature sensor (66) which is communicatively connected to the control device (64) and is configured to measure an inlet temperature of the reaction chamber (22, 52, 72, 92), an emission sensor (66) which is communicatively connected to the control device (64) and is configured to measure an emission output from the reaction chamber (22, 52, 72, 92), wherein the control device (64) is configured to adjust a position of the at least one valve (60, 68, 78, 98) in order to adjust the amount of fuel (32) supplied to the injectors (54, 74, 76, 94) in response to the inlet temperature or the emission output being outside a range specified by at least one threshold.

Description

BACKGROUND TO THE INVENTION

[0001] The disclosure relates generally to injector devices and afterburners for fuel and air. In particular, the disclosure relates to afterburners and injectors for fuel and air that modify the performance and output power of a power generation system, such as a gas turbine system or a turbomachine.

[0002] Turbine systems are frequently used, for example, in electric generators to produce power. A working fluid, such as hot gas or steam, flows over sets of turbine blades that are mechanically connected to a rotor of the turbine system. The force of the working fluid on the blades causes these blades (and the connected rotor body) to rotate. In many cases, the rotor body is connected to the drive shaft of a dynamo-electric machine, such as an electric generator. In this sense, causing the turbine rotor to rotate can also rotate the drive shaft in the electric generator to produce an electric current and a certain amount of power output.

[0003] To generate the working fluid in a combustion chamber-based turbomachine, a fuel can be burned within a combustion chamber in the presence of oxygen to produce a hot gas stream that sets the turbine blades in motion. In some systems, some of the air may not react in the combustion chamber and can proceed downstream through the gas turbine system. To improve the power output and efficiency of the turbomachine, this unreacted air can flow into a further combustion chamber known as the afterburner. In the afterburner, the unreacted air can be burned in the presence of additional fuel to produce more hot gas and set the final turbine stage of the turbomachine in motion. This type of turbomachine is known in the field as an intercooled turbine.

[0004] A reheat turbine has the potential to achieve higher efficiencies than previously known in the field. The efficiency of conventional combined cycle power plants, which may include reheat turbines, can be limited by the output power and / or the efficiency of the afterburner. In particular, the design of the afterburner, such that it has a different outlet temperature than that of the first combustion chamber, can influence the power output (e.g., by increasing or decreasing the amount of fuel and the combustion energy in the afterburner) and the emissions (e.g., through combustion reactions in the afterburner that produce varying amounts of carbon monoxide (CO), carbon dioxide (CO2), in addition to nitrogen monoxide or nitrogen dioxide, collectively referred to as "NOx").

[0005] US 2011 / 0314825A1 shows a gas turbine with multiple turbine stages that can be coupled to one another by means of an intermediate combustion chamber. The afterburner can have injector guide vanes by means of which a fuel is mixed with the air flowing around the injector guide vanes. The afterburner is designed as an annular combustion chamber.

[0006] A gas turbine known from US 8 112 216 B2 has a combustion chamber in which fuel can be expelled downstream via injectors for lean combustion.

[0007] US 2008 / 0264033A1 concerns a combustion system for NOₓ x -Reduction. In a combustion chamber, an ignitable mixture is created using air injectors and fuel injectors.

[0008] A gas turbine with tandem air guide vanes is disclosed in US 2008 / 0134685A1. In this design, fuel can be injected into a space between the tandem air guide vanes and extracted from this space by the air flowing past the tandem air guide vanes. BRIEF SUMMARY OF THE INVENTION

[0009] The present invention relates to a device according to claim 1, an afterburner according to claim 4, and a turbomachine according to claim 6. Embodiments of the present invention can generally improve the performance of a combustion chamber-based power generation system by supplying additional fuel and air to a downstream region (also referred to as the "back section") of the combustion chamber. Diverting a portion of the fuel to the injector can increase the amount of combustion reactions occurring within an afterburner, reduce the temperature of fluids entering the back section, and reduce emissions from the reaction chamber.The additional combustion reactions can occur in a preferred area of ​​the chamber, downstream of relatively heat-sensitive components, based on the location and technical design of the injection devices and / or afterburner chamber components.

[0010] In any of the aforementioned devices of the seventh aspect, the mass ratio of the carrier gas to the fuel in one of the several injectors is preferably between approximately one to one and approximately five to one.

[0011] The relative amount of fuel supplied to the multiple injectors can be at most approximately one third of the fuel supplied to the reaction chamber from a fuel supply line.

[0012] In particular, at least one valve can supply at most approximately one third of the fuel in the fuel supply line to the multiple injectors.

[0013] The ratio of the carrier gas to the fuel in one of the several injectors can preferably be between approximately one to one and approximately five to one. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] These and other features of the invention will be more easily understood from the following detailed description of the various aspects of the invention, together with the accompanying drawings, which show different embodiments of the invention, in which: Fig. Figure 1 is a schematic view of a conventional gas turbine system that includes an afterburner. Fig. Figure 2 shows a cross-sectional view of a conventional afterburner chamber. Fig. Figures 3-7 show cross-sectional views of afterburning chambers and devices according to the present disclosure. Fig. Figure 8 shows a schematic view of a turbomachine according to the descriptions in the present disclosure. Fig. 9 shows an illustrative environment containing a control device which interacts with some sensors and valves, as described in the present disclosure.

[0015] Note that the drawings of the invention are not necessarily to scale. The drawings are intended only to show typical aspects of the invention and should therefore not be considered as limiting the scope of the invention. In the drawings, identical reference numerals denote identical elements between the drawings. DETAILED DESCRIPTION OF THE INVENTION

[0016] As described herein, aspects of the invention essentially relate to devices for injecting fuel and air into a combustion chamber of a power generation system, in particular an afterburner of a combustion chamber-based power generation system, such as a gas turbine. Devices according to the present disclosure may, for example, include an injector extending through the surface of a turbine guide vane or the wall of an afterburner. The injector may supply fuel and / or air into a "rear" section of the afterburner, which is generally defined as a section of the combustion chamber in which combustion reactions do not occur without the injection of additional fuel, e.g., at locations other than an inlet to the afterburner. The turbine guide vane neck section may separate the rear section of the afterburner from a turbine stage of the power generation system.A line can be in fluid communication with the injector and can convey fuel from a fuel supply line to the injector. The same line, or a different line, can convey a carrier gas, such as cooling air or bleed air from a combustion chamber, or other gases, including oxygen and / or inert gases (i.e., gases used for fuel injection and / or dilution), together with the fuel to the injector.

[0017] With reference to Fig. Figure 1 shows a conventional energy generation system 10 in the form of a turbomachine. Embodiments of the present invention can be adapted for use with the energy generation system 10 and / or can be integrated into its components. The energy generation system 10 is shown by way of example as a combustion-based turbomachine arrangement, although embodiments of the present disclosure can also be adapted for use with other types of combustion systems, where applicable. In the context of combustion-based turbomachines, a combustion chamber 12, which is connected to a fuel supply 14, is typically arranged between a compressor 16 and a high-pressure (HP) gas turbine 18 of the energy generation system 10. The fuel supply 14 can be fluidically connected to one or more fuel nozzles connected to the combustion chamber 12 or otherwise be formed in the shape of these.In one embodiment, the fuel supply 14 can be in fluid communication with a group arranged circumferentially around the combustion chamber 12 and / or other combustion chambers of the power generation system 10. The compressor 16 and the high-pressure gas turbine 18 can be mechanically connected to each other via a rotatable shaft 20. To increase power output and / or efficiency, the power generation system 10 can also include an afterburner 22 and a low-pressure (LP) turbine 24, which is in fluid communication with the fluids discharged from the high-pressure gas turbine 18.

[0018] The air 26 flows sequentially through the compressor 16, the combustion chamber 12, the high-pressure gas turbine 18, the afterburner 22, and the low-pressure gas turbine 24. The compression achieved by the compressor 16 can also increase the temperature of the air 26. The fuel supply 14 can deliver fuel to the combustion chamber 12 and the afterburner 22, which burns in the presence of air 26 to generate a hot gas stream. The hot gas stream from the combustion chamber 12 can enter the high-pressure gas turbine 18 to transfer mechanical energy to the rotating shaft 20, for example, by rotating a group of turbine blades, thereby supplying power back to the compressor 16 and / or to any (not shown) loads mechanically connected to the rotating shaft 20.Similarly, fuel supplied from fuel supply 14 to the afterburner 22 can be combusted in the presence of excess air supplied from gas turbine 18 to create a hot gas stream for the low-pressure gas turbine 24, which can transfer additional mechanical energy to the rotating shaft 20, for example by rotating turbine blades within the low-pressure gas turbine 24. The power generation system 10 can be one of several individual turbomachinery units controlled by the same operator and / or can be part of a larger power generation system.

[0019] A carrier gas supply 28 can be connected to the combustion chamber 12 and / or the afterburner 22. To reduce the amount of air 26 diverted from the compressor(s) 16 to specific sections of the combustion chamber 12 and / or the afterburner 22, a carrier gas supply 28 can be in fluid connection with the combustion chamber 12 and / or the afterburner 22. The carrier gas supply 28 can generally include any dedicated carrier gas supply and / or any other component or system from which the carrier gas can be drawn or reused. In a specific example, the carrier gas supply 28 can include a compressor in fluid connection with an afterburner 22 and / or another component. The carrier gas supply 28 can be arranged within and / or integrated with the power generation system 10.In other embodiments, the carrier gas supply 28 can be external to the power generation system 10 as an external component or another external source of the carrier gas. Air 26, which would otherwise be used to cool certain components of the power generation system 10, can thus be reused as a reactant with a fuel that, according to the present disclosure, is injected into other areas of the combustion chamber 12 and / or the afterburner chamber 22.

[0020] Referring to Fig. Figure 2 shows a cross-sectional view of a conventional afterburner chamber 22, which can be modified or adapted for embodiments of the present invention or otherwise used with them. During operation, air 26 can flow into an inlet 30 to the afterburner chamber 22. The fuel 32, which comes from the fuel supply 14 ( Fig. 1) For example, if the fuel is supplied via a fuel supply line 34, it can mix within a mixing channel 36 of the afterburner chamber 22. The dashed lines shown in the fuel supply 34 indicate an indefinite length. The air 26 can be in the form of a hot gas, which, for example, comes from the high-pressure gas turbine 18 ( Fig. 1) is expelled and can be mixed with the fuel 32 in a specific way to reduce the time delay before auto-ignition occurs. The size and length of a mixing channel 36 can be chosen to create a specific delay before auto-ignition and a specific type of fuel / air composition before combustion takes place. The afterburner chamber 22 can be maintained at a temperature sufficient for combustion reactions to occur therein, e.g., at least approximately 1065° Celsius (C). As used herein, the term "approximately" with respect to a specified numerical value (including percentages of numerical base values) can mean any value within 10 percentage points (i.e.,Above and below) the specified numerical value or percentage and / or any other values ​​that do not result in an operational difference or a material operational difference between the modified value and the listed value. The term "approximately" may also include other specific values ​​or ranges if specified herein.

[0021] The mixture of air 26 and fuel 32 can combust in a reaction zone 38 of the afterburner 22 via a process called auto-ignition. Auto-ignition generally refers to a combustion reaction that occurs without the use of a flame or spark located within or upstream of the area where reactions take place. Some excess unreacted air in the reaction zone 38 can recirculate back to the mixing channel 36 to initiate additional combustion reactions, while other portions of the unreacted air can proceed to other downstream components described herein. In general, the term "upstream" refers to a reference path extending in the opposite direction to the resultant direction in which fluids flow through the power generation system 10 ( Fig. 1) flow through it. The term “downstream” refers to a reference path extending in the same direction as the resulting direction in which fluids flow through the power generation system 10. Fuel and air thus generally flow through the power generation system 10 in a downstream direction during operation. The afterburner 22 can be divided into a front section 40 and a rear section 42 based, for example, on where combustion reactions take place between the air 26 and the fuel 32 from the fuel supply line 34. The rear section 42 may be free of combustion reactions in it, except where, according to embodiments of the present invention, additional fuel and carrier gas are injected into the rear section 42. In any case, at least one turbine guide vane or turbine nozzle 44 can separate the afterburner 22 from a turbine stage of the power generation system 10 ( Fig. 1) (e.g., of an ND gas turbine 24). The turbine guide vane 44 is shown in a generalized, simplified form and may contain a complex geometry (e.g., channels inside or outside components with airfoil-like geometries and / or dimensions) and / or may be in the form of several turbine guide vanes 44 in fluid communication with the same combustion chamber 22. The turbine guide vane 44 may include a reduced surface area at its downstream end, which may be referred to as a neck 46 of the turbine guide vane 44. Fluids flowing through the neck 46 may increase in fluid velocity before flowing to a turbine stage downstream of the afterburner chamber 22 (e.g., to the ND gas turbine 24).The reaction zone 38 can extend beyond the end of the rear section 42 of the afterburner chamber into the turbine guide vane 44, but can end upstream of the neck 46 of the turbine guide vane 44.

[0022] The applicants have determined that the efficiency of a conventional afterburner may be suboptimal in certain applications and / or under certain conditions. In an optimized afterburner cycle, the combustion temperature of both combustion chambers 12, 22 ( Fig. 1) be approximately the same, while the heat released in combustion chamber 12 would be approximately twice that of afterburner chamber 22. The various operational and design constraints (e.g., environmental losses, excess reactive materials, manufacturing tolerances, emissions and / or temperature requirements, etc.) may pose design challenges for creating these conditions within afterburner chamber 22 during operation. In particular, the applicants have found that the temperature of the inlet 30 in afterburner chamber 22 is approximately the same throughout the entire operating cycle of the power generation system 10 ( Fig. 1) appears to be restricted. In an example of a conventional energy generation system 10, the temperature of the inlet 30 of the afterburner 22 may be approximately 925°C. This temperature may be related to variables such as the pressure drop in the entire afterburner 22 and the number of auto-ignition reactions occurring therein. The exhaust gas temperature from the afterburner 22 may be approximately 1550°C and may be affected by emissions (e.g., CO or NO). x ), and the residence time required to achieve efficient combustion at emissions below certain levels (e.g. maximum values ​​for exhaust gases allowed under environmental regulations) may be limited.

[0023] Embodiments of the present disclosure may modify these limitations and / or improve performance by applying late lean injection of additional fuel and / or air to a combustion chamber at specific locations, thereby increasing its properties, such as its inlet temperature. As used herein, late lean injection generally refers to any injection of fuel and / or air located downstream of the inlet 30. Increasing the temperature of the inlet 30 may, for example, allow the first-stage firing temperature (i.e., the temperature at which combustion takes place within the combustion chamber 13) to be increased, thereby improving the overall cycle efficiency.

[0024] Referring to Fig. Figure 3 shows a device 50 and an afterburner 52 as described in the present disclosure. The device 50 may include an injector 54 extending through a surface of the turbine guide vanes 44. Embodiments of the device 50 may include any fluid injection devices known now or developed in the future. For example, the injector 54 may be in the form of a top-fed, side-fed, and / or body injector with a specific nozzle, such as an expansion-deflection nozzle (also called a "pin nozzle"), a disc nozzle, a ball nozzle, etc. In each case, the injector 54 may be connected to and in fluid communication with a line 56 to draw off a portion of the fuel 32 from the fuel supply line 34.Furthermore, the injector 54 can be in fluid communication with the air 26 from the inlet 30 via an air line 58, which is arranged between the inlet 30 and the injector 54. The air line 58 can optionally be in fluid communication with the carrier gas supply 28 to supply a carrier gas from a source other than the inlet 30 to the injector 54, such as from the dedicated carrier gas supply located within or external to the power generation system 10. Fig. 1) is arranged, or from unreacted air from compressor 16 ( Fig. 1) The carrier gas from the carrier gas supply 28 can optionally be mixed with the excess air from the inlet 30 within the air line 58.

[0025] The device 50 can be dimensioned to create specific operational characteristics. A separation distance S1 between the injector 54 and the neck 46 can be dimensioned to allow substantially all of the fuel 32 (e.g., at least approximately 95% of it) to ignite and react completely in the afterburner chamber 52 before passing through the neck 46 into downstream components, such as an ND gas turbine 24 ( Fig. 1) flows in. In one exemplary embodiment, the separation distance S1 can have a dimension between approximately 2.0 centimeters and approximately 20 centimeters. The flow of the fluids in the line 56 and the air line 58 and / or the size of the injector 54 can be controlled and / or selected such that a mass ratio of carrier gas to fuel (e.g., a mass of the injected air and / or the carrier gas divided by a mass of the injected fuel 32) in the injector 54 is between approximately one to one and approximately five to one.

[0026] The injector 54 can be oriented in a specific direction, exemplified in Fig. 3 is shown as being substantially opposite to a flow of fluids, such as the reactants and / or the combusted reaction products, through the afterburning chamber 52 and the turbine guide vanes 44. As used herein, “opposite to” includes all orientations in which at least some fuel and at least some carrier gas from the first injector 54 and fluids within and / or leaving the afterburning chamber 52 (e.g., within the turbine guide vanes 44) collide with one another before continuing to flow as an at least partially mixed fluid. In one embodiment, the injector 54 and the flow of fluids (e.g., air 26) through or out of the afterburning chamber 52 can be directly opposed along a certain linear direction, i.e.,have opposite or approximately opposite orientations, such that the angular orientation of the injector 54 and the fluid flow through the afterburner chamber 52 differ from each other by approximately 180° (i.e., within approximately five degrees more or less than 180°). In a further embodiment, the injector 54 and a direction of fluid flow through the afterburner chamber 52 can be directed at least partially in opposite directions, i.e., with one fluid flow component vector in the same direction as the other outlet along one axis, and with another component vector in a different direction from the other outlet along another axis. For example, a fluid flow through the afterburner chamber 52 can proceed in a substantially horizontal reference direction, while the injector 54 is oriented at an angle on the order of no more than approximately (e.g.,within five degrees of 45° with respect to this fluid flow. In the example of the . Fig. 3. The injector 54 supplies fuel and carrier gas in a direction with a component vector that is aligned against the fluid flow through the afterburning chamber 52. Any number of possible relative alignments between a fluid flow through the afterburning chamber 52 and the injector 54 are considered in embodiments of the present invention, as long as at least a portion of the carrier gas and the fuel collides, mixes, and / or reacts with at least a portion of the fluid flowing through the afterburning chamber 52.

[0027] To control the amount of fuel 32 supplied to the injector 54 from the fuel supply line 34, the device 50 may include a valve 60 arranged between the fuel supply line 34 and the line 56. In some embodiments, the valve 60 may be configured to direct at most approximately twenty percent of the total fuel 32 in the fuel supply line 34 to the line 56. This ratio may, for example, allow the majority of combustion reactions in the afterburner 52 to take place within the front section 40, while the supplied fuel can be used for a smaller number of combustion reactions taking place in the rear section 42 and / or in the turbine guide vanes 44.Dynamic control of the amount of combustion reactions in the rear reaction zone 38 from the fuel and the carrier gas of the injector 54 can be achieved via a control device 64, which is operatively connected to the valve 60. The control device 64 can generally include any type of computing device capable of performing operations by means of a processing component (e.g., a microprocessor), and may, for example, include a computer, a computer processor, electrical and / or digital circuits, and / or a similar component used for calculating and processing electrical inputs. Exemplary components and operating functions of the control device 64 are described in detail elsewhere.

[0028] A sensor 66 can be in communication with a control device 64 and can be located, for example, within the inlet 30 to the afterburner chamber 52 or downstream of the reaction zone 38 therein. The sensor(s) 66 can be in the form of a temperature sensor and / or an emission sensor to measure a temperature or an emission quantity (such as NOₓ). x) to evaluate at a specific location. The sensor(s) 66 in the form of a temperature sensor can be a thermometer, thermocouples (i.e., voltage-based devices that indicate a temperature change based on a change in voltage), resistance-based temperature sensing devices (i.e., devices for evaluating temperature based on changes in electrical resistance), infrared sensors, strain-based sensors (i.e., sensors for deriving temperature changes from the expansion or contraction of a material, such as a metal), and / or state-change sensors. If one or more sensors 66 contain temperature sensors, the temperature of fluid(s) flowing through the sensor location(s) can be measured and / or converted into an electrical signal or input. The sensor(s) 66 in the form of emission sensors can be...The sensor(s) may contain general-purpose gas detectors, thermal conductivity detectors, calorimetric test tubes, and / or similar devices for measuring the quantity or concentration of certain substances in a fluid stream or a sample of exhaust air. Examples of emissions that can be measured by the sensor(s) 66 include nitrogen oxides and nitrogen dioxide (NO₂). x ) and / or carbon monoxide (CO) and / or oxygen (O2). In each case, the relevant emissions can be measured in terms of their total weight or their relative molecular weight (e.g., number of moles of NO). xor CO per gram of total exhaust gas) and can be converted into an electrical signal or an input for the control device 64. The sensor(s) 66 can also detect or calculate parameters derived from algorithms that allow inferences about values ​​of interest, e.g., temperature or gas composition, based on measurements at other locations within the gas turbine and mathematical models of the flow physics of gases through the turbine, the calculations being performed in conjunction with the control device 64. The sensor(s) 66 can include components for measuring variables related to temperature and processing components (e.g., computer software) for predicting and / or calculating values ​​of temperature or other metrics based on related variables.In general, the term “determine” in the context of sensor(s) 66 refers to the process of finding a specific value by direct measurement, predictive modeling, derivation from related quantities and / or other mathematical procedures for measuring and / or finding a specific quantity.

[0029] The control device 64 can, by means of a mechanical connection to the valve 60, set a position of the valve 60 based on inputs and / or signals supplied by the sensor(s) 66. In an exemplary embodiment, the control device 64 can set a position of the valve 60 based on an inlet temperature of the afterburner chamber 52 and / or the emission output from the afterburner chamber 52. The control of the valve 60 can increase or decrease the quantity of fuel 32 supplied from the fuel supply line 34 to the line 56. The control device 64 can contain program code that is installed by a user to measure one or more variables (e.g., temperatures and / or emission outputs) with combustion parameters and / or inputs (e.g.,to relate the quantities of fuel or air to be injected through the injector 54) in order to increase or decrease the amount of combustion within the afterburning chamber 52 by a certain value.

[0030] In an exemplary embodiment, the control device 64 can adjust the valve 60 to divert, for example, between approximately ten and approximately twenty percent of the fuel 32 from the fuel supply line 34 to the line 56, thereby adjusting the tolerance of the afterburner chamber 52 to higher temperatures at the inlet 30. In particular, a reduction in the amount of fuel 32 entering an upstream combustion chamber (e.g., combustion chamber 12) can be achieved. Fig. 1)) is burned, reduce the amount of fuel present in the inlet 30 upstream of the mixing channel 36, and thus reduce the probability of premature combustion reactions occurring therein. The control device 64 can control the percentage of fuel 32 supplied from the fuel supply line 34 based on operating conditions detected by the sensor(s) 66 and / or on the composition of the fuel 32. Furthermore, the control device 64 can control a relative amount of fuel 32 supplied to the afterburner 52 instead of another combustion chamber (e.g., combustion chamber 12) by means of a fuel supply valve 68 that is operatively connected to and / or located within the fuel supply line 34. The control device 64 can control a total amount of fuel 32 supplied to the afterburner 52, e.g.,Fuel is supplied through the fuel supply line 34 and the line 56 through its operative connection with the fuel supply valve 68. Although the valve 60 and the fuel supply valve 68 are shown by way of example in . Fig. Where components 3 are shown as separate parts, a (not shown) three-way valve can replace valve 60 and fuel supply valve 68 to perform the same functions. Other valves and groups of valves described herein for controlling relative quantities of fluids can also be replaced, where applicable, by (not shown) multidirectional valves.

[0031] With reference to Fig. Figure 4 shows another embodiment of an afterburner chamber 52. In contrast to Fig. 3 shows Fig. 4 the afterburner chamber 52 with the injector 54 in fluid communication with the rear section 42 of the afterburner chamber 52. As described elsewhere herein, the rear section 42 can be defined as a section of the afterburner chamber 52 located downstream of the reaction zone 38, where combustion does not occur without late lean injection. In the Fig. In the embodiment shown in Figure 4, the line 56 can supply the fuel 32 from the fuel supply line 34 to the injector 54. Furthermore, the air line 58 can provide a fluid connection of air and / or carrier gas from the inlet 30 and / or the carrier gas supply 28 to the injector 54. The various additions and / or modifications described herein with reference to Fig. 3 are described elsewhere (e.g., the placement, use and / or operation of the valve 60, the control device 64, and the sensors 66), but not with reference to Fig. The features specifically described in Section 4 are usable and / or adaptable for all embodiments of the device 50 and the afterburner chamber 52. Furthermore, a separation distance S2 between the injector 54 in the rear section 42 of the afterburner chamber 52 can allow substantially all (e.g., at least approximately 95% of) the fuel 32 to ignite and react completely within the afterburner chamber 52 before reaching the neck 46 of the turbine guide vane 44. The flow of the fluids in the line 56 and the air line 58 and / or the size of the injector 54 can also allow the mass ratio of air to fuel in the injector 54 to be between approximately one to one and approximately five to one.

[0032] Fig. 3 and Fig. Figure 4 jointly show alternative embodiments of the device 50 and the afterburner chamber 52 according to the present disclosure. In some situations, a conventional afterburner chamber 22 ( Fig. 1, Fig. 2) machined, modified, reconfigured and / or otherwise processed into the afterburner chamber 52 with the injector 54 installed therein, which may extend through a wall / surface of the rear section 42 or the turbine guide vane 44. In this configuration, the air 26 and fuel 32 injected via the injector 54 can combust in the rear section 42. The remaining air 26 and fuel 32 introduced into the afterburner chamber 54, i.e., from the fuel supply line 34, can combust in the front section 40. As in Fig. As shown in Figure 3, the reaction zone 38 can essentially be a continuous reaction zone extending from the front section 40 of the afterburner 52 through the rear section 42 and to and / or including the turbine guide vane 44, without passing through the neck section 46. The additional modifications described herein with respect to the device 50 (e.g., the placement, use, and / or operation of the valve 60, the control device 64, and the sensors 66) can also be applied to the afterburner 52 where desired. In any case, the afterburner injector 54 can be located within either the rear section 42 or the turbine guide vane 44 to create varying amounts of mixed and / or supplemental combustion within the afterburner 52.

[0033] Embodiments of the device 50 can increase the power output of the energy generation system 10 ( Fig. 1) change during operation. For example, the injection of fuel into the afterburner chamber 52 at the rear section 42 can allow additional fuel to be injected due to a higher temperature tolerance at the inlet 30 of the afterburner chamber 52, bypassing earlier combustion chamber stages (e.g., combustion chamber 12 ( Fig. 1)) is supplied. The greater temperature tolerance at the inlet 30 can be based, at least in part, on diverting some fuel 32 into the injector 54, thereby reducing the amount of fuel supplied to the inlet 30 and the risk of premature combustion within the inlet 30. During operation, the turbine guide vane assembly 44 can be cooled by means of a carrier gas (e.g., from the carrier gas supply 28) at a specific temperature (e.g., approximately 315°C), and this carrier gas can then be mixed with the fuel 32 supplied by the fuel supply line 34 before it flows into the injector 54. In an exemplary embodiment, this mixing can increase the temperature of the inlet 30 by approximately 140°C to an elevated temperature of approximately 1065°C.Furthermore, the fuel flow to combustion chamber 12 can increase by approximately twenty percent, which, for example, can represent approximately ten percent of the total fuel supplied to the power generation system 10. This portion of the total fuel can be supplied from other combustion chambers using valve 68. Conversely, the fuel supplied to afterburner chamber 52 can be twenty percent less than in a conventional arrangement (which, for example, represents approximately ten percent of the total gas turbine fuel), making afterburner chamber 52 more tolerant of the increased temperature of inlet 30.

[0034] With reference to Fig. Figure 5 shows a device 70 according to the embodiments of this disclosure. The device 70 can form at least part of an afterburner chamber 72. Some of the elements and / or components described herein with respect to the device 70 and the afterburner chamber 72 are adaptable and / or modifiable for use with the device 70 and the afterburner chamber 72. The afterburner chamber can be in the form of a reaction chamber arranged between the inlet 30 and the turbine guide vane 44 and can be shaped, dimensioned, etc., for a predetermined degree of combustion to take place therein. The device 70 can include a first injector 74 extending through a surface of the turbine guide vane 44. The device 70 can also include a second injector 76 extending through a wall of the afterburner chamber 72.Line 56 and air line 58 can each be in fluid communication with the first injector 74 and the second injector 76, respectively. Line 56 can supply fuel 32 from fuel supply line 34 to the first and second injectors 74 and 76. Air line 58 can supply air from inlet 30 and / or carrier gas supply 28 (e.g., in the form of unreacted air) to the first and second injectors 74 and 76. The first and second injectors 74 and 76 can supply fuel 32 and air 26 to the afterburner 72 in any relative ratio. In an exemplary embodiment, each injector 74 and 76 can supply fuel 32 and air 26 to the afterburner 72 in a mass ratio of approximately one (i.e., with equal quantities and / or flow rates of fuel 32 and air 26). The afterburner chamber 72 can be divided into a front section 40 and a rear section 42.The front section 40 can be defined as a section of the afterburner chamber 72 where the combustion reactions of the fuel 32 leaving the fuel supply line 34, i.e., within the reaction zone 38, can take place. The rear section 42 can be defined as a section of the afterburner chamber 72 where the combustion reactions of fuel and air leaving the first and second injectors 74 and 76 take place. Thus, the rear section 42 is located downstream of the front section 40 within the afterburner chamber 72.

[0035] The device 70 may include a valve 60 arranged between the fuel supply line 34 and the line 56. The device 70 may also include a fuel supply valve 68 mechanically connected to the fuel supply line 34. The fuel supply valve 68 can control the quantity of fuel supplied to the afterburner chamber 72 and other (not shown) combustion chambers. The valve 60 and / or the fuel supply valve 68 may be operatively connected to the control device 64. The control device 64 can adjust the position(s) of the valve 60 and / or the fuel supply valve 68 based on operating characteristics of the afterburner chamber 72. These operating characteristics may include, for example, the temperature of the inlet 30 and / or an emission output (e.g., CO and / or NO). xThe levels of the afterburner chamber 72 are determined by the sensor(s) 66 in communication with the control device 64. The control device 64 can increase the amount of fuel 32 supplied to the line 56 based on the emissions being below a predetermined threshold and / or the temperature of the inlet 30 being above a predetermined threshold. One or more thresholds can be defined in the control device 64 via user input and / or mathematical calculations and can, for example, be stored in a memory (not shown) of the control device 64.In one embodiment, the control device 64 can adjust the valve 60 and / or the fuel supply valve 68 to divert at most approximately twenty percent of the fuel 32 in the fuel supply line 34 to the line 56, and in particular, it can divert between approximately ten percent and approximately twenty percent of the fuel in the fuel supply line 34 to the line 56.

[0036] The device 70 can include a distribution valve 78, which is arranged between the line 56 and the first and second injectors 74, 76 for controlling the relative proportions of fuel 32 and air 26 supplied to the first and second injectors 74, 76. The control device 64 can adjust the distribution valve 78 based on operational variables, e.g., the inlet 30 temperatures and / or the emission outputs, as determined by the sensor(s) 66, in order to supply different quantities of fuel 32 and air 26 to the injectors 74, 76. For example, supplying fuel 32 to the second injector 76 upstream of the first injector 74 can generate additional combustion reactions and / or combustion reactions at higher temperatures due to the greater proximity of injector 76 to the reaction zone 38.

[0037] The first and second injectors 74, 76 can each be separated from the neck 46 of the nozzle 44 by corresponding first and second separation gaps S1, S2. The first separation gap S1 can limit the combustion of the fuel from the first injector 74 to the reaction zone 38 before it enters the neck 46 of the turbine guide vane 44. The separation gap S1 can be determined, for example, by predicting a combustion quantity and an associated reaction volume for an expected injection rate by the first injector 74 and creating a separation gap S1 with at least one predetermined length value based on this prediction. In an exemplary embodiment, the separation gap S1 can have a dimension between approximately 2.0 centimeters and approximately 20 centimeters.To further increase the mixing of fuel 32 and air 26, the first injector 74 and / or the second injector 76 can project from the surface of the turbine guide vanes 44 and / or the wall of the afterburner chamber 72 in essentially the opposite direction to the fluid flow through the afterburner chamber 72. A general definition of the positions that make an injector 72, 74 "opposite" to a fluid flow is given elsewhere.

[0038] Embodiments of the present disclosure also provide systems for controlling the injection of fuel 32 and air 26 into a separately manufactured or existing afterburner chamber 72. Embodiments of the device 70 can include the control device 64, which is operatively connected to the valve 60, the valve 60 being arranged between the fuel supply line 34 and the line 56 to the first and / or the second injector 74, 76. As described elsewhere herein, the valve 60 can, for example, control the amount of air supplied from the fuel supply line 34 into the line 56. The control device 64 can be in communication with the sensor(s) 66 for determining one or more operating conditions of the afterburner chamber 72, such as the temperature of the inlet 30 and / or an emission output from the afterburner chamber 72. The control device 64 can be a computer system with instructions (e.g.,Algorithms, program code, lookup tables, etc.) for setting a position of the valve 60 and / or other components described herein (e.g., the fuel supply valve 68, the dividing valve 78 and / or an air supply valve 80, which are explained elsewhere herein) based on measurement readings from the sensor(s) 66.

[0039] Embodiments of the present disclosure may also include the dividing valve 78, which is operatively connected to the control device 64 for controlling a relative quantity of the fuel 34 supplied to the first injector 74 or the second injector 76. A carrier gas control valve 80 may also be operatively connected to the control device 64 and may be arranged between the carrier gas supply 28 and the air line 58. The carrier gas control valve 80 can control a quantity of air supplied from the carrier gas supply 28 and / or the inlet 30 to the first and second injectors 74, 76. In some embodiments, the dividing valve 78 can control the quantity of air that is divided between the first and the second injectors 74, 76 (i.e.,The control device 64 can control the first and second portions of the air 26 and / or the carrier gas from the carrier gas supply 28) as an alternative to or in addition to the distribution of the fuel 34 between the first and second injectors 74, 76. The control device 64 can adjust the position of the distribution valve 78 and / or the carrier gas control valve 80 based on operating characteristics of the afterburner chamber 72, e.g., an inlet temperature 30 and / or emission outputs from the afterburner chamber 72, which are determined by the sensor(s) 66 in conjunction with the control device 64. Although in . Fig. Figure 5 shows the dividing valve 78 as an example of a single component. It is understood that the valve 78 can be in the form of two separate valves for the fuel 32 and the air 26, each of which can be arranged between the injectors 74, 76 and the line 56 or the air line 58. It is understood that embodiments of the devices 50, 70, the afterburner chambers 52, 72 and / or their components can be mixed, modified and / or otherwise combined with one another as desired and / or required for specific applications.

[0040] With brief reference to Fig. Figure 6 shows an alternative embodiment of the device 70 and the afterburner chamber 72. Here, several lines 56 and air lines 58 can be fluidically connected to the afterburner chamber 72 via the first and second injectors 74, 76. In a specific example, as shown in Fig. As shown in Figure 6, each injector 74, 76 is connected to a corresponding line 56 and air line 58 in fluid communication. Each line 56 and air line 58 can also include an associated dividing valve 78 for controlling the proportions of fuel 32 and air 26 supplied to each injector 74, 76. Furthermore, in this illustrative example, the carrier gas control valve 80 is shown as a three-way valve for controlling the proportions of air 26 or carrier gas supplied to each air line 58. It is understood that the valve 60, the dividing valve(s) 78, and the carrier gas control valve 80 can be separated into several components and / or combined with one another if this is desired and / or appropriate for a particular implementation.

[0041] The present disclosure includes additional equipment for improving efficiency and otherwise increasing the output of the energy generation system 10 ( Fig. 1) quantity of power produced. With reference to Fig. 7. Embodiments of the present invention may include a device 90 which is a replacement for the afterburner chamber 22 ( Fig. 2) in a conventional energy generation system. The device 90 can be in the form of an alternative afterburner chamber with a reaction chamber 92 located therein and can be provided by one or more conventional afterburner chambers 22 of the energy generation system 10 ( Fig. 1) be replaced. Where desired, the embodiments of the device 90 can also be used in combination with and / or as a replacement for the afterburner chambers 52, 72 ( Fig. 3-6). The device 90 can be used free of the mixing channels 36 ( Fig. 3-6), which are arranged between the inlet 30 and the reaction chamber 92.

[0042] The device 90 can include several injectors 94 extending through a wall of the reaction chamber 92, and / or additional injectors 94 extending through the turbine guide vane 44. As described elsewhere herein, the turbine guide vane 44 can separate the reaction chamber 92 from a second turbine stage (e.g., the low-pressure gas turbine 24 ( Fig. 1)) of a specific energy generation system. The injectors 94 can be in the form of any component known today or developed in the future for injecting air 26 and / or fuel 32, and as non-limiting examples, one or more injectors 94 can be configured as "rack-like" immersion injectors, nozzle injectors, air-bubble fuel injectors, pressure atomizer injectors, premix injectors, and / or pre-evaporating injectors. The injectors 94 can be oriented substantially opposite to the flow of a fluid (e.g., air 26) through the reaction chamber 92, so that the mixing of fuel and air with the fluid(s) flowing through the device 90 is increased.In an exemplary embodiment, the ratio of fuel to carrier gas in each of the injectors 94 can be approximately one to one, or it can deviate from this value based on a position and / or a desired value or range of values ​​for the operating characteristics of the device 90. In any case, the fuel 32 injected into the device 90 by the injectors 94 can constitute the total amount of fuel 32 injected into the device 90 without a primary fuel supply line (e.g., the fuel supply line 34) being in direct fluid communication with the reaction chamber 92 of the device 90.

[0043] The use of multiple injectors 94 can reduce the presence of the mixing channel 36 ( Fig. 2-6) between the inlet 30 and the reaction chamber 92 can be reduced or eliminated entirely. If the reaction chamber 92 has approximately the same length as the afterburner chambers 22, 52, 72, the addition of injectors 94 and the omission of the mixing channel 36 can alter the temperature and / or time required to combust the fuel 32 and the air 26 therein. In one embodiment, the fuel 32 can combust within the reaction chamber 92 in less than approximately one millisecond after exiting a particular injector 94. It has been found that this change in reaction conditions can enable a larger quantity of air 26 and fuel 32 to react, complete combustion of emissions such as carbon monoxide (CO), and a reduction in the overall reaction temperature throughout the reaction chamber 92.These changes in the reaction conditions result in part from the reduced amounts of fuel 32 supplied by each injector 94 along the length of the reaction chamber 92 and the guide apparatus 44. The more complete combustion of the reactants in the device 90, compared with conventional afterburner chambers 22, can also reduce the generation of NO. x -limit emissions. This change in reaction conditions can also increase the tolerance for elevated temperatures at the inlet 30, thereby further reducing the pressure loss in the entire device 90 (i.e., between the inlet 30 and the turbine guide vane 44) because the device 90 is free of mixing zones and allows combustion in the entire reaction chamber 92 without the use of dedicated mixing zones and / or channels.

[0044] The device 90 may optionally, if desired and / or applicable, include further components and features described elsewhere herein as components of the devices 50, 70 or afterburner chambers 52, 72. For example, the device 90 may include a valve 98 arranged between the fuel supply line 34 and the line 56 to the injectors 94. The fuel supply line 34 may supply a large portion of the fuel 32 (e.g., at least two-thirds of the total fluid flow) to a further combustion chamber independent of the device 90, e.g., combustion chamber 12 ( Fig. 1) deliver there. The valve 98 can divert a portion of the fuel 32 in the fuel supply line 34 to the line 56 and to the injectors 94 to initiate combustion reactions within the reaction chamber 92 of the device 90. In an exemplary embodiment, the valve 98 can be dimensioned to divert up to one-third of the total flow of fuel 32 in the fuel supply line 34 to the injectors 94.

[0045] To further control the amount of fuel 32 supplied to the injectors 94, the device 90 may also include the control device 64, which is operatively connected to the valve 98. Sensor(s) 66 may also be connected to the control device 64 to determine an inlet temperature 40, an outlet temperature (i.e., a temperature within or above the turbine guide vanes 44), and / or an emission output from the reaction chamber 92. The control device 64 may be configured to adjust the position (i.e., open or closed) of the valve 98 by using program code and / or software provided therein, and with reference to values ​​determined by the sensor(s) 66.As described elsewhere herein, the control device 64 can, for example, close the valve 98 to reduce the amount of fuel 32 supplied to the device 90 in response to the fact that the emission levels detected by the sensor(s) 66 are too high, open the valve 98 based on the fact that the temperature of the inlet 30 is higher than a threshold value, and / or otherwise adjust the position of the valve 98 based on operating conditions of the device 90 determined by the sensor(s) 66.

[0046] Referring to Fig. 7 and Fig. 8. Combined embodiments of the present disclosure can result in a turbomachine 100 adapted to include the device 90. The turbomachine 100 can include the combustion chamber 12 in the form of a first-stage combustion chamber to receive fuel from the fuel supply 14 via the fuel feed line 34. The combustion chamber 12 can also be in fluid communication with the compressor 16 and / or the carrier gas supply 28 to receive air that reacts with the fuel from the fuel supply 14. The device 90 can be arranged between the high-pressure gas turbine 18 and the low-pressure gas turbine 24, thereby causing the reaction chamber 92 therein to be in fluid communication with an upstream turbine stage and a downstream turbine stage (e.g., the high-pressure gas turbine 18 (upstream) and the low-pressure gas turbine 24 (downstream)).The line 56 can supply the fuel 32, which may be mixed with air 26 drawn from the inlet 30, to the reaction chamber 92. The temperature inside the reaction chamber 92 can cause combustion reactions therein. At least some of the fuel 32 can react with excess air 26 supplied by the upstream turbine stage (e.g., the high-pressure gas turbine 18), which may be in the form of air from the compressor 12 and / or the carrier gas supplied from the carrier gas supply 28. In one embodiment, the fuel flowing into the reaction chamber 92 from the line 56 and the injectors 94 can combust in less than one millisecond after entering the reaction chamber 92.

[0047] As described elsewhere herein, the turbomachine 100 can include a valve 98 operatively connected to line 56 to control the quantity of fuel 32 supplied to the injectors 94 from fuel supply line 34. More specifically, the valve 98 can control a relative quantity of fuel supplied from fuel supply line 34. The quantity of fuel 32 supplied via the valve 98 can be limited, for example, by a physical limit on the valve 98 (maximum opening and / or closing positions), a user-defined maximum value stored in the control device 64 and used to adjust the valve 98, and / or by combinations of these methods and other methods. In one exemplary embodiment, the valve 98 can divert up to approximately one-third of the fuel 32 within the fuel supply line 34 into line 56.The position of valve 98 and the quantity of fuel 32 supplied to line 56 can, for example, be controlled by the control device 64 connected to valve 98. The control device 64 can adjust the position of valve 98 based on values ​​determined, for example, by the sensor(s) 66 in communication with the control device 64. The other features described herein with respect to device 90 can, where desired, also be applied to turbomachine 100. As examples, and as in . Fig. As shown in Figure 7, the injectors 94 can be oriented substantially opposite to a flow of fluid through the reaction chamber 92, and / or the injectors 94 can inject carrier gas and fuel into the reaction chamber 92 in a ratio of approximately one to one.

[0048] The fuel allocation between combustion chamber 12 and device 90 can be set and adjusted using control device 64 based on the current and / or desired operating conditions of the turbomachine 100 and on the composition of a specific fuel 32 to be burned. For example, approximately two-thirds of the total fuel in fuel supply 14 can be allocated to combustion chamber 12 of turbomachine 100, and the temperature at inlet 30 of device 90 can be approximately 1340°C to achieve a reduced auto-ignition delay time (e.g., of less than approximately 0.5 milliseconds). In another example, the operating temperatures of combustion chamber 12 and device 90 within turbomachine 100 can be approximately the same.The allocation of fuel from the fuel supply 14 between the combustion chamber 12 and the device 90 can, for example, determine the firing temperature within each stage. Furthermore, a total quantity of carrier gas supplied to the combustion chamber 12 and the device 90 can be selected to maintain a predetermined gas turbine exhaust gas temperature, and this quantity of carrier gas can be continuously and / or periodically adjusted via a control device 64. Other variables influenced by the quantity and allocation of fuel 32 and carrier gas 26 may include: emissions from the turbomachine 100, total fuel intake, and tolerance ranges for the temperature of the inlet 30.

[0049] Fig. Figure 9 shows an illustrative environment 100 in conjunction with the sensor(s) 66 for controlling one or more valves 60, fuel supply valve(s) 68, dividing valve(s) 78, carrier gas control valve(s) 80, and / or valve(s) 98 (collectively referred to as "valve(s)") according to embodiments. In this respect, the environment 100 includes the control device 64 for carrying out processes and transmitting electrical commands to the control valve(s) 60, 68, 78, 80, 98 and associated systems and tools. Although each type of valve 60, 68, 78, 80, 98 described herein is in Fig. As shown by way of example in Figure 9, it is understood that the environment 100 with the control device 64 with only one or more embodiments of the present disclosure as described herein, including without limitation one or more afterburning chambers 52, 72 ( Fig. 3-6) and / or devices 50, 70, 90 ( Fig. 3-8). The control device 64 is shown as it includes a valve control system 112, which enables the control device 64 to operate the valve(s) 60, 68, 78, 80, 98 and associated systems and tools described herein, and to implement any / all embodiments described herein. In operation, the valve control system 112 can output electrical commands, which in turn can be converted into mechanical activities (e.g., an activity to open and close one or more valves 60, 68, 78, 80, 98) in response to certain conditions. The conditions for opening and / or closing the valves 60, 68, 78, 80, 98 may, for example, include an inlet temperature 30 ( Fig. 2-7) or an emission output from the turbine guide vane 44 ( Fig. 2-7) may be within or outside a range of threshold values, or that other operating variables and / or values ​​determined by the sensor(s) 66 may be within or outside a range of threshold values.

[0050] The control device 64 is shown as comprising a processing component 104 (e.g., one or more processors), a memory 106 (e.g., a memory hierarchy), an input / output (I / O) component 108 (e.g., one or more I / O interfaces and / or devices), and a communication path 110. In general, the processing component 104 executes program code, such as a valve control system 112, which is at least partially stored in the memory 106. While the program code is executing, the processing component 104 can process data, which may involve reading and / or writing converted data from or into the memory 106 and / or from or into the I / O component 108 for further processing. The path 110 establishes a communication link between each of the components in the control device 64.The I / O component 108 can include one or more human I / O devices that enable a human or system user 114 to interact with the control device 64, and / or one or more communication devices to enable the user(s) 114 to communicate with the control device 64 using any type of communication link. In this respect, the valve control system 112 can manage a number of interfaces (e.g., graphical user interface(s), application programming interface, etc.) that enable the user(s) 112 to interact with the valve control system 112. The valve control system 112 can also manage data, such as system data 116 (including measured or recorded temperatures, emission outputs, etc.), using any solution (e.g., store, retrieve, generate, manipulate, organize, display, etc.).

[0051] In any case, the control device 64 may include one or more general-purpose or special-purpose computing articles (e.g., computer devices) capable of executing program code installed thereon, such as the valve control system 112. For the purposes of this text, “program code” means any set of instructions, in any language, code, or notation, that cause a computing device with an information-processing capability to perform a specific function, either directly or following any combination of the following: (a) conversion to another language, code, or notation; (b) reproduction in another material form; and / or (c) decompression. Accordingly, the valve control system 112 may be embodied as any combination of system software and / or application software.

[0052] The valve control system 112 can further be implemented using a set of modules 118. In this case, a module 118 can enable the control device 64 to perform a number of tasks used by the valve control system 112 and can be developed separately and / or implemented remotely from other parts of the valve control system 112. The control device 64 can also include a user interface module 120 to display a specific user interface on a display component, such as a monitor (e.g., using graphics, text, and / or a combination thereof). When fixed in the memory 106 of the control device 64, which contains a processing component 104, a module is an essential part of a component that implements the functionality.Notwithstanding the foregoing, it is understood that two or more components, modules, and / or systems may share some or all of their respective hardware and / or software. Furthermore, it is understood that some of the functionality described herein need not be implemented, or that additional functionality may be included as part of the control device 64.

[0053] If the control device 64 has multiple computing units, each computing unit can only have a part of the valve control system 112 attached to it (e.g., one or more modules 118). It is understood, however, that the control device 64 and the valve control system 112 are merely representative of various possible equivalent computer systems that can perform a process described herein. In other embodiments, the functionality provided by the control device 64 and the valve control system 112 can be implemented, at least partially, by one or more computing units containing any combination of general-purpose and / or special-purpose hardware, with or without program code. In each embodiment, the hardware and the program code, if included, can be created using standard engineering or programming methods.

[0054] Notwithstanding the foregoing, if the control device 64 contains multiple computing devices, the computer devices may communicate with each other via any type of communication link. Furthermore, while a process described herein is being carried out, the control device 64 may communicate with one or more other computer systems using any type of communication link. In any case, the communication link may include any combination of different types of wired and / or wireless connections; any combination of one or more types of networks; and / or any combination of different types of transmission methods and protocols.

[0055] It is understood that aspects of the invention may also result in various alternative embodiments. For example, in one embodiment, the present disclosure provides a control device for adjusting the quantity of fuel and / or air supplied to the components of the afterburner chambers 52, 72 ( Fig. 3-6) and / or the devices 50, 70, 90 ( Fig.3-7) are supplied by adjusting the position of the valve(s) 60, 68, 78, 80, 98. In other embodiments, the use of the afterburner chambers 52, 72 and / or the device 90 may involve operating the control device 64 manually (e.g., by a technician) or by means of one or more computer systems operatively connected to it. It is understood that the control device 64 may serve technical purposes in other facilities beyond general operation, including, but not limited to, inspection, maintenance, repair, replacement, testing, etc.

[0056] The valve control system 112 can be in the form of a computer program fixed in at least one computer-readable medium which, when executed, enables the control device 64 to function and to adjust the position of the valve(s) 60, 68, 78, 80, 98. In this respect, the computer-readable medium contains program code that includes some or all of the processes and / or embodiments described herein. The term "computer-readable medium" is understood to mean one or more of any kind of tangible expression medium, as is currently known or may be developed in the future, from which a copy of the program code can be perceived, reproduced, or otherwise transmitted by a computing device. For example, the computer-readable medium may include: one or more portable storage devices; one or more memory components of a computing device; paper; etc.

[0057] The device and method of the present disclosure are not limited to any particular gas turbine, combustion system, power engine, energy generation system, or other system and can be used with other energy generation systems and / or systems (e.g., a combined cycle power plant, a single cycle power plant, a nuclear power plant, etc.). Furthermore, the device of the present invention may potentially be used with other systems not described herein that may benefit from the increased or enhanced operating range, efficiency, durability, and reliability of the device described herein. The technical effects of the present disclosure may, without limitation, include the ability to control the inlet temperatures and combustion rates in the combustion chambers and afterburners of an energy generation system, e.g.,by increasing, decreasing, or otherwise adjusting the amount of fuel and carrier gas allocated to different combustion chambers and parts of the same combustion chamber.

[0058] Embodiments of the present invention can achieve several technical and commercial advantages. For example, embodiments of the present invention can be provided as modifications or retrofit components for existing gas turbine systems. By combining embodiments of the present disclosure with conventional power generation systems and / or their components, it is possible to supply a larger proportion of the total gas turbine fuel flow to any afterburner in the system at a lower load and with greater operating efficiency to a first-stage combustion chamber. Furthermore, the various embodiments of a first-stage combustion chamber described herein can enable fuel to be burned at a higher temperature because the staged combustion reactions in a downstream afterburner, as described herein, can be staged in multiple reaction zones.

[0059] The terminology used herein serves solely to describe certain embodiments and is not intended to be limiting to the disclosure. In the sense used herein, the singular forms "a," "an," and "the" are to include the plural forms as well, unless the context clearly indicates otherwise. It is further understood that the expressions "has" and / or "having" when used in this description indicate the presence of the specified features, integers, steps, operations, elements, and / or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or their groups.

[0060] This written description uses examples to disclose the invention, including its best embodiment, and to enable a person skilled in the art to apply the invention, including the manufacture and use of devices or systems and the performance of the methods contained therein. The patentable scope of the invention is defined by the claims and may include further examples that a person skilled in the art might think of. These further examples shall fall within the scope of the claims if they have structural elements that do not deviate from the wording of the claims or if they include equivalent structural elements with insignificant differences from the wording of the claims.

[0061] Embodiments of the present disclosure provide a device comprising: a reaction chamber arranged between a first turbine stage of a power generation system and a subsequent turbine stage of the power generation system, the subsequent turbine stage comprising a turbine guide vane assembly and a turbine rotor blade array; several injectors arranged on a wall of the reaction chamber; and a conduit in fluid communication with the several injectors, the conduit supplying at least one of a fuel from a fuel supply line and a carrier gas to the reaction chamber through the several injectors. REFERENCE MARK LIST 10 Energy generation system 12 Combustion chamber 14 Fuel supply 16 compressors 18, 24 Gas turbine 20 rotating shaft 22, 52, 72 Afterburner chamber 24 Low-pressure (LP) gas turbine 26 air 28 Carrier gas supply 30 Admission 32 Fuel 34 Fuel supply line 36 Mixing channel 38 Reaction zone 40 front section 42 rear section 44 Turbine guide vane, turbine nozzle 46 Neck 50, 70, 90 device 54 injectors 56 Management 58 Air duct 60 valve 64 Control device 66 Sensor 74 first injector 76 second injector 78 Dividing valve 80 Air supply valve 92 Reaction chamber 94 multiple injectors 98 Opening valve 100 turbomachines 104 Processing component 106 memory 108 Input / Output (I / O) Component 110 Communication channel 112 Valve control system 114 users 118 Module

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