Adaptive regenerative gas turbine system with mode-switching capability
Patent Information
- Application Number
- PCT/IB2025/053049
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- Filing Date
- 2025-03-23
- Publication Date
- 2026-10-01
Smart Images
Figure IB2025053049_01102026_PF_FP_ABST
Abstract
Description
REF- 1403-0308003ADAPTIVE REGENERATIVE GAS TURBINE SYSTEM WITH MODE-SWITCHING CAPABILITY TECHNICAL FIELD
[0001] The present disclosure relates to gas turbines, particularly adaptive regenerative gas turbine systems. More particularly, the present disclosure relates to gas turbine architectures incorporating multiple regenerators and flow control mechanisms to enable switching between different operation modes for enhanced efficiency and adaptability.BACKGROUND
[0002] Gas turbine power plants are frequently utilized in energy production due to their rapid response to load changes and relatively compact size. Despite these advantages, improving their thermal efficiency remains a critical challenge. The Brayton cycle serves as the fundamental operating cycle of gas turbines, where thermal efficiency increases with higher compressor pressure ratios. When a regenerative gas turbine is operating, the rate of improvement diminishes at elevated pressure ratios, and efficiency may even decline. This limitation arises due to the decreasing temperature of turbine exhaust gases, which can impact the heat recovery effectiveness of the regenerator.
[0003] Various strategies have been developed to enhance the efficiency of gas turbines, including regenerative cycles, intercooling, reheating, and combined cycle approaches. Regenerative Brayton cycles, in particular, leverage the thermal energy in turbine exhaust gases to preheat compressed air prior to combustion, thereby reducing fuel consumption and enhancing efficiency. A conventional regenerative gas turbine typically incorporates a single regenerator that transfers heat from the turbine exhaust to the compressed air. However, the effectiveness of this configuration is constrained by fluctuations in operational parameters such as ambient conditions, load requirements, and compression ratios, which can impact the heat recovery process and the overall performance of the cycle.REF- 1403-0308003
[0004] The regenerative Brayton cycle improves efficiency at lower pressure ratios but becomes less effective at higher pressure ratios due to the decreasing turbine exhaust temperature, which may drop below the compressor outlet temperature. In such conditions, instead of preheating the air before combustion, the regenerator may undesirably cool the compressed air, increasing fuel consumption and reducing cycle efficiency. To overcome this limitation, a modified regenerative cycle incorporating two turbine expansion stages and an intermediate heat recovery step has been introduced. In this configuration, the first turbine expands the high-temperature air to an intermediate pressure level, ensuring that the exhaust temperature remains sufficiently high for effective heat recovery. The partially expanded air then undergoes heat exchange before entering a second turbine stage, thereby maintaining efficient thermal recovery across a broader range of pressure ratios.
[0005] To further enhance efficiency and adaptability, adaptive regenerative gas turbines have been developed that can switch between different operational modes. These systems integrate multiple regenerators and employ flow control mechanisms to optimize heat exchange processes based on instantaneous operating conditions. By enabling mode transitions, adaptive regenerative gas turbines can sustain high efficiency across diverse operational scenarios, reducing fuel consumption under varying loads. Nevertheless, existing adaptive systems may involve intricate control architectures and additional components, leading to increased complexity and costs.
[0006] Accordingly, there is a demand for advanced adaptive regenerative gas turbine systems that deliver superior heat recovery efficiency while offering operational adaptability. An ideal system would facilitate seamless transitions between regenerative modes, ensuring high efficiency across varying compressor pressure ratios without imposing substantial complexity or cost. The innovative adaptive heat recovery system described herein achieves this objective by continuously adjusting to different operating conditions, leveraging theREF- 1403-0308003advantages of various regenerative cycle configurations, and maintaining optimal thermal efficiency across a wide range of compressor pressure ratios.SUMMARY
[0007] This summary is intended to provide an overview of the subject matter of one or more exemplary embodiments, and is not intended to identify essential elements or key elements of the subject matter, nor is it intended to be used to determine the scope of the claimed implementations. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that is presented later. The proper scope of one or more exemplary embodiments may be ascertained from the claims set forth below in view of the detailed description below and the drawings.
[0008] According to one or more exemplary embodiments, the present disclosure is directed to an exemplary adaptive regenerative gas turbine that may be switchable between an exemplary first operation mode and an exemplary second operation mode. An exemplary adaptive regenerative gas turbine may include an exemplary compressor that may be configured to compress an exemplary air stream from an exemplary first pressure to an exemplary second pressure. An exemplary adaptive regenerative gas turbine may further include an exemplary first regenerator that may be disposed downstream of an exemplary compressor and connected in fluid communication therewith. An exemplary first regenerator may be configured to preheat an exemplary compressed air stream by placing an exemplary compressed air stream in indirect contact with an exemplary first heating fluid input in an exemplary first operation mode. An exemplary adaptive regenerative gas turbine may further include an exemplary second regenerator that may be disposed downstream of an exemplary first regenerator and connected in fluid communication therewith. An exemplary second regenerator may be configured to preheat an exemplary compressed air stream by placing an exemplary compressed air stream in indirect contact with an exemplary second heating fluid input in an exemplary second operation mode.REF- 1403-0308003
[0009] An exemplary adaptive regenerative gas turbine may further include an exemplary combustion chamber that may be disposed downstream of an exemplary second regenerator and connected in fluid communication therewith. An exemplary combustion chamber may be configured to receive an exemplary preheated compressed air stream to generate an exemplary combustion gas stream. An exemplary adaptive regenerative gas turbine may further include an exemplary first turbine that may be disposed downstream of an exemplary combustion chamber and connected in fluid communication therewith. An exemplary first turbine may be configured to receive an exemplary combustion gas stream to drive an exemplary compressor and exhaust an exemplary first exhaust stream. An exemplary first turbine may further be coupled with an exemplary compressor via an exemplary first shaft.
[0010] An exemplary adaptive regenerative gas turbine may further include an exemplary second turbine that may be configured to drive an exemplary external load. An exemplary second turbine may be configured to receive either an exemplary first exhaust stream from an exemplary first turbine in an exemplary first operation mode or an exemplary second heating fluid output from an exemplary second regenerator in an exemplary second operation mode. An exemplary external load may comprise an exemplary electricity generator, which may be coupled with an exemplary second turbine via an exemplary second shaft.
[0011] An exemplary adaptive regenerative gas turbine may further include an exemplary first flow control mechanism that may be disposed downstream of an exemplary first turbine and connected in fluid communication therewith. An exemplary first flow control mechanism may be configured to selectively conduct an exemplary first exhaust stream either toward an exemplary second regenerator in an exemplary first operation mode or toward an exemplary second turbine in an exemplary first operation mode. An exemplary adaptive regenerative gas turbine may further include an exemplary second flow control mechanism that may be disposed downstream of an exemplary second turbine and connected in fluid communication therewith. An exemplary second flow control mechanism may be configured to selectively conduct anREF- 1403-0308003exemplary second exhaust stream either toward an exemplary first regenerator in an exemplary first operation mode or toward an exemplary atmospheric discharge in an exemplary second operation mode.
[0012] An exemplary adaptive regenerative gas turbine may further include an exemplary control system that may be coupled with an exemplary first flow control mechanism and an exemplary second flow control mechanism. An exemplary control system may include at least one exemplary processor and at least one exemplary memory coupled to the at least one exemplary processor. An exemplary control system may be configured to receive temperature and pressure parameters, calculate a first dimensionless ratio based on an exemplary combustion gas stream temperature and an exemplary air stream temperature, determine a predefined calibration relationship, and determine a third ratio.
[0013] An exemplary control system may be further configured to compare an exemplary second ratio with an exemplary third ratio, which may be determined based on an exemplary predefined calibration relationship. An exemplary control system may be configured to urge an exemplary first flow control mechanism and an exemplary second flow control mechanism to change corresponding operation modes based on a comparison between an exemplary second ratio and an exemplary third ratio.
[0014] In an exemplary embodiment, when an exemplary second ratio is less than an exemplary third ratio, an exemplary adaptive regenerative gas turbine may operate in an exemplary first operation mode. In an exemplary first operation mode, an exemplary first flow control mechanism may direct an exemplary first exhaust stream from an exemplary first turbine toward an exemplary second turbine, and an exemplary second flow control mechanism may direct an exemplary second exhaust stream from an exemplary second turbine toward an exemplary first regenerator. Conversely, when an exemplary second ratio is greater than or equal to an exemplary third ratio, an exemplary adaptive regenerative gas turbine may operate in an exemplary second operation mode. In an exemplary second operation mode, an exemplaryREF- 1403-0308003first flow control mechanism may direct an exemplary first exhaust stream from an exemplary first turbine toward an exemplary second regenerator, and an exemplary second flow control mechanism may direct an exemplary second exhaust stream from an exemplary second turbine toward an exemplary atmospheric discharge.
[0015] An exemplary first flow control mechanism may comprise an exemplary first three-port valve including an exemplary first inlet port in fluid communication with an exemplary first turbine and configured to receive an exemplary first exhaust stream, an exemplary first outlet port configured to direct an exemplary first exhaust stream toward an exemplary second turbine in an exemplary first operation mode, and an exemplary second outlet port configured to direct an exemplary first exhaust stream toward an exemplary second regenerator in an exemplary second operation mode. Similarly, an exemplary second flow control mechanism may comprise an exemplary second three -port valve including an exemplary second inlet port in fluid communication with an exemplary second turbine and configured to receive an exemplary second exhaust stream, an exemplary third outlet port configured to direct an exemplary second exhaust stream toward an exemplary first regenerator in an exemplary first operation mode, and an exemplary fourth outlet port configured to direct an exemplary second exhaust stream toward an exemplary atmospheric discharge in an exemplary second operation mode.
[0016] In an exemplary embodiment, an exemplary predefined calibration relationship may define an exemplary third ratio as a function of an exemplary first dimensionless ratio, which may be derived from an exemplary combustion gas stream temperature and an exemplary air stream temperature. An exemplary predefined calibration relationship may be expressed as follows:rpsw= 3.6261 (Tmax / T1) - 8.6475.REF- 1403-0308003where rpswmay represent an exemplary third ratio, may represent an exemplary combustion gas stream temperature, and T1may represent an exemplary air stream temperature.
[0017] In an exemplary embodiment, an exemplary first pressure may be equal to an atmospheric pressure. An exemplary adaptive regenerative gas turbine may be configured to optimize energy efficiency and operational flexibility by dynamically switching between an exemplary first operation mode and an exemplary second operation mode based on real-time system parameters.
[0018] This Summary may introduce a number of concepts in a simplified format; the concepts are further disclosed within the “Detailed Description” section. This Summary is not intended to configure essential / key features of the claimed subject matter, nor is intended to limit the scope of the claimed subject matter.BRIEF DESCRIPTION OF THE DRAWINGS
[0019] The novel features which are believed to be characteristic of the present disclosure, as to its structure, organization, use and method of operation, together with further objectives and advantages thereof, will be better understood from the following drawings in which a presently preferred embodiment of the present disclosure will now be illustrated by way of example. It is expressly understood, however, that the drawings are for the purpose of illustration and description only and are not intended as a definition of the limits of the present disclosure. Embodiments of the present disclosure will now be described by way of example in association with the accompanying drawings in which:FIG. 1A illustrates a schematic view of adaptive regenerative gas turbine, consistent with one or more exemplary embodiments of the present disclosure;FIG. IB illustrates a schematic view of adaptive regenerative gas turbine operating in first operation mode, consistent with one or more exemplary embodiments of the present disclosure;REF- 1403-0308003FIG. 1C illustrates a schematic view of adaptive regenerative gas turbine operating in second operation mode, consistent with one or more exemplary embodiments of the present disclosure;FIG. 2 illustrates a detailed schematic view of first flow control mechanism and second flow control mechanism in first operation mode, consistent with one or more exemplary embodiments of the present disclosure;FIG. 3 illustrates a control system diagram of adaptive regenerative gas turbine, consistent with one or more exemplary embodiments of the present disclosure;FIG. 4 illustrates a graphical representation of the relationship between third ratio, rpsw, andfirst dimensionless ratio, Tmax / T1, consistent with one or more exemplary embodiments of thepresent disclosure;FIG. 5 illustrates a comparative analysis of the thermal efficiencies of B, RB and 2TRB cycles as a function of pressure ratio, rc, consistent with one or more exemplary embodiments of the present disclosure;FIG. 6 illustrates the variations in dimensionless specific power output, wnet / CpT1, for B,RB, and 2TRB configurations as a function of pressure ratio, rc, of compressor, consistent with one or more exemplary embodiments of the present disclosure;FIG. 7 illustrates the variations in the dimensionless temperature of exhaust gas, Texh / T1, of B, RB, and 2TRB as a function of pressure ratio, rc, of compressor, consistent with one or more exemplary embodiments of the present disclosure; andFIG. 8 illustrates the thermal efficiency, ηth, of the proposed adaptive regenerative gas turbine (ARGT) as a function of pressure ratio, rc, of compressor, consistent with one or more exemplary embodiments of the present disclosure.DETAILED DESCRIPTION
[0020] In the following detailed description, numerous specific details are set forth by way of examples to provide a thorough understanding of the relevant teachings related to theREF- 1403-0308003exemplary embodiments. However, it should be apparent that the present teachings may be practiced without such details. In other instances, well known methods, procedures, components, and / or circuitry have been described at a relatively high-level, without detail, in order to avoid unnecessarily obscuring aspects of the present teachings.
[0021] The following detailed description is presented to enable a person skilled in the art to make and use the methods and devices disclosed in one or more exemplary embodiments of the present disclosure. For purposes of explanation, specific nomenclature is set forth to provide a thorough understanding of the present disclosure. However, it will be apparent to one skilled in the art that these specific details are not required to practice the disclosed exemplary embodiments. Descriptions of specific exemplary embodiments are provided only as representative examples. Various modifications to the exemplary implementations will be plain to one skilled in the art, and the general principles defined herein may be applied to other implementations and applications without departing from the scope of the present disclosure. The present disclosure is not intended to be limited to the implementations shown, but is to be accorded the widest possible scope consistent with the principles and features disclosed herein.
[0022] The present disclosure is directed to exemplary embodiments of an exemplary adaptive regenerative gas turbine. An exemplary adaptive regenerative gas turbine may be switchable between an exemplary first operation mode and an exemplary second operation mode to optimize efficiency and performance under varying operating conditions.
[0023] An exemplary adaptive regenerative gas turbine may comprise an exemplary compressor that may be coupled to and driven by an exemplary first turbine. An exemplary air stream may enter an exemplary compressor, where an exemplary air stream may be compressed to generate an exemplary compressed air stream. An exemplary compressed air stream may be preheated in either an exemplary first regenerator in an exemplary first operation mode or an exemplary second regenerator in an exemplary second operation mode. In an exemplary first operation mode, an exemplary first regenerator may receive an exemplary first heating fluid toREF- 1403-0308003preheat an exemplary compressed air stream. In an exemplary second operation mode, an exemplary second regenerator may receive an exemplary second heating fluid to preheat an exemplary compressed air stream before feeding an exemplary compressed air stream into an exemplary combustion chamber.
[0024] In an exemplary combustion chamber, an exemplary preheated compressed air stream may be mixed with an exemplary pressurized fuel stream and may be ignited to produce exemplary combustion gas stream that may exit an exemplary combustion chamber at a maximum temperature of an exemplary adaptive regenerative gas turbine. An exemplary combustion gas stream at an exemplary maximum temperature may be expanded in an exemplary first turbine to produce an exemplary required power to drive an exemplary compressor. An exemplary first turbine may subsequently exhaust an exemplary first exhaust stream.
[0025] An exemplary second turbine may be utilized to drive an exemplary external load. In an exemplary first operation mode, an exemplary first exhaust stream from an exemplary first turbine may be directed toward an exemplary second turbine to drive an exemplary external load. In an exemplary second operation mode, an exemplary first exhaust stream may be directed toward an exemplary second regenerator to serve as an exemplary second heating fluid input. An exemplary second turbine may then exhaust an exemplary second exhaust stream.
[0026] An exemplary adaptive regenerative gas turbine may comprise an exemplary first flow control mechanism and an exemplary second flow control mechanism to selectively direct exemplary exhaust streams based on an exemplary operational mode. In an exemplary first operation mode, an exemplary first flow control mechanism may direct an exemplary first exhaust stream toward an exemplary second turbine, and an exemplary second flow control mechanism may direct an exemplary second exhaust stream toward an exemplary first regenerator. In an exemplary second operation mode, an exemplary first flow controlREF- 1403-0308003mechanism may direct an exemplary first exhaust stream toward an exemplary second regenerator, and an exemplary second flow control mechanism may direct an exemplary second exhaust stream toward an exemplary atmospheric discharge.
[0027] An exemplary adaptive regenerative gas turbine may further comprise an exemplary control system configured to adjust the configurations of an exemplary first flow control mechanism and an exemplary second flow control mechanism to ensure seamless transitions between exemplary operational modes.
[0028] An exemplary adaptive regenerative gas turbine may include an exemplary first turbine that may drive an exemplary compressor via an exemplary first shaft. Additionally, an exemplary second turbine may be coupled to an exemplary external load, such as an exemplary electricity generator, via an exemplary second shaft, enabling efficient conversion of available energy into mechanical or electrical work.
[0029] By dynamically adjusting exemplary flow paths of exemplary exhaust gases and switching between exemplary operation modes based on exemplary real-time operating conditions, an exemplary adaptive regenerative gas turbine may enhance energy utilization, improve fuel efficiency, and provide operational flexibility across various applications. This adaptability may be particularly beneficial for varying load demands, ensuring optimal performance in diverse operational scenarios.
[0030] Referring to the figures, FIG. 1A illustrates a schematic view of an exemplary adaptive regenerative gas turbine 100, FIG. IB illustrates a schematic view 101 of adaptive regenerative gas turbine 100 operating in an exemplary first operation mode and FIG. 1C illustrates a schematic view 102 of adaptive regenerative gas turbine 100 operating in an exemplary second operation mode, consistent with one or more exemplary embodiments of the present disclosure.
[0031] As depicted in FIG. 1A, in an exemplary embodiment, adaptive regenerative gas turbine 100 may operate in first operation mode 101 and second operation mode 102. In anREF- 1403-0308003exemplary embodiment, adaptive regenerative gas turbine 100 may comprise an exemplary compressor 104 configured to compress an exemplary air stream 1042 from an exemplary first pressure, P, to an exemplary second pressure, P2, thereby producing an exemplary compressed air stream 1040.
[0032] With continued reference to FIG. 1A and reference to FIG. IB and FIG. 1C, in an exemplary embodiment, compressed air stream 1040 may be directed into an exemplary first regenerator 106, which may preheat compressed air stream 1040. In first operation mode 101, as shown in FIG. IB, first regenerator 106 may facilitate heat exchange between compressed air stream 1040 and an exemplary first heating fluid input 1180, resulting in an exemplary preheated compressed air stream 1060. In an exemplary embodiment, downstream of first regenerator 106, preheated compressed air stream 1060 may enter an exemplary second regenerator 108. In second operation mode 102, as shown in FIG. 1C, second regenerator 108 may preheat compressed air stream 1040 by facilitating a heat exchange process with an exemplary second heating fluid input 1140.
[0033] In further detail regarding FIG. 1A, in an exemplary embodiment, preheated compressed air stream 1060 exiting second regenerator 108 may be directed into an exemplary combustion chamber 110. In an exemplary embodiment, within combustion chamber 110, preheated compressed air stream 1060 may combine with an exemplary fuel stream and ignite, generating an exemplary combustion gas stream 1100. In an exemplary embodiment, combustion gas stream 1100 may then enter an exemplary first turbine 112, which may be mechanically coupled to compressor 104 via an exemplary first shaft 122. In an exemplary embodiment, first turbine 112 may expand combustion gas stream 1100 to produce a mechanical work, drive compressor 104, and generate an exemplary first exhaust stream 1120.
[0034] In an exemplary embodiment, an exemplary first flow control mechanism 114 may be disposed downstream of first turbine 112. In first operation mode 101, as illustrated in FIG. IB, first flow control mechanism 114 may direct first exhaust stream 1120 to an exemplaryREF- 1403-0308003second turbine 116, which may be coupled to an exemplary external load 120. In second operation mode 102, as illustrated in FIG. 1C, first flow control mechanism 114 may redirect first exhaust stream 1120 to second regenerator 108, where first exhaust stream 1120 may function as second heating fluid input 1140.
[0035] In further detail, in an exemplary embodiment, second turbine 116 may exhaust an exemplary second exhaust stream 1160, which may be managed by an exemplary second flow control mechanism 118. In first operation mode 101, as shown in FIG. IB, second flow control mechanism 118 may direct second exhaust stream 1160 to first regenerator 106, where second exhaust stream 1160 may serve as first heating fluid input 1180. In an exemplary embodiment, in second operation mode 102, second exhaust stream 1160 may be directed toward an exemplary atmospheric discharge 1181 (as shown in FIG. 1C).
[0036] In an exemplary embodiment, FIG. 2 illustrates a detailed schematic view of first flow control mechanism 114 and second flow control mechanism 118 in first operation mode, consistent with one or more exemplary embodiments of the present disclosure. As depicted in FIG. 2, in an exemplary embodiment, first flow control mechanism 114 may comprise an exemplary first three-port valve 224, and second flow control mechanism 118 may comprise an exemplary second three-port valve 226. In an exemplary embodiment, first three-port valve 224 and second three-port valve 226 may be configured to manage first exhaust stream 1120 and second exhaust stream 1160 between various components of adaptive regenerative gas turbine 100. In an exemplary embodiment, first three-port valve 224 may include an exemplary first damper 202, and second three -port valve 226 may include an exemplary second damper 204. In an exemplary embodiment, first damper 202 may be operable to redirect first exhaust stream 1120 between first operation mode 101 and second operation mode 102, while second damper 204 may be operable to redirect second exhaust stream 1160 between first operation mode 101 and second operation mode 102.REF- 1403-0308003
[0037] With continued reference to FIG. 2, in an exemplary embodiment, first three-port valve 224 may include an exemplary first inlet port 206, an exemplary first outlet port 208, and an exemplary second outlet port 210. In an exemplary embodiment, first inlet port 206 may be in fluid communication with first turbine 112 and may receive first exhaust stream 1120 from first turbine 112. In an exemplary embodiment, in first operation mode 101, first outlet port 208 may direct first exhaust stream 1120 to second turbine 116 to drive an external load 120. In an exemplary embodiment, in second operation mode 102, second outlet port 210 may direct first exhaust stream 1120 to second regenerator 108.
[0038] In further detail regarding FIG. 2, in an exemplary embodiment, second three -port valve 226 may include an exemplary second inlet port 216, an exemplary third outlet port 218, and an exemplary fourth outlet port 220. In an exemplary embodiment, second inlet port 216 may be in fluid communication with second turbine 116 and may receive second exhaust stream 1160. In an exemplary embodiment, in first operation mode 101, third outlet port 218 may direct second exhaust stream 1160 to first regenerator 106, where second exhaust stream 1160 may serve as first heating fluid input 1180. In an exemplary embodiment, in second operation mode 102, fourth outlet port 220 may direct second exhaust stream 1160 to atmospheric discharge 1181.
[0039] Referring to the figures, FIG. 3 illustrates a control system diagram 222 of adaptive regenerative gas turbine 100, consistent with one or more exemplary embodiments of the present disclosure. As illustrated in FIG. 2 and FIG. 3, in an exemplary embodiment, adaptive regenerative gas turbine 100 may further include an exemplary control system 222. In an exemplary embodiment, control system 222 may manage operational configurations between first operation mode 101 and second operation mode 102 by adjusting first flow control mechanism 114 and second flow control mechanism 118. In an exemplary embodiment, first operation mode 101 and second operation mode 102 may be dynamically selected based on operational conditions monitored by control system 222.REF- 1403-0308003
[0040] As depicted in FIG. 2 and FIG. 3, in an exemplary embodiment, control system 222 may include at least one exemplary processor 212 and an exemplary memory 214 configured to store executable instructions. In an exemplary embodiment, executable instructions may enable control system 222 to monitor parameters such as temperature of combustion gas stream, Tmax, temperature of air stream 1042, T1first pressure, P, and second pressure, P2. In an exemplary embodiment, adaptive regenerative gas turbine 100 may include a plurality of exemplary pressure gages (e.g. 302a and 302b) and a plurality of exemplary temperature gages (e.g. 304), as illustrated in FIG. 3, to monitor P, P2,and, Tmax.
[0041] In further detail regarding FIG.3, in an exemplary embodiment, data from pressure gages (e.g. 302a and 302b) and temperature gages (e.g. 304 ) may be transmitted to control system 222 via an exemplary transmitter 308, which facilitates efficient communication between pressure gages (e.g. 302a and 302b), temperature gages (e.g. 304) and control system 222. As shown in FIG. 3, in an exemplary embodiment, an exemplary data logger 306 may be integrated into control system 222 to record and store the measured data over time. In an exemplary embodiment, control system 222 may calculate an exemplary first dimensionlessratio, -2122.,anc|anexemplary second ratio, rc= —, and retrieve an exemplary predefined A Picalibration relationship linking a first dimensionless ratio to a third ratio, rcsw. In an exemplary embodiment, at rcsw, control system 222 may initiate a transition between first operation mode 101 and second operation mode 102 by adjusting first flow control mechanism 114 and second flow control mechanism 118.
[0042] In an exemplary embodiment, when ( rc< rcsw), adaptive regenerative gas turbine 100 may operate in first operation mode 101. Conversely, when (rc> rcsw), adaptive regenerative gas turbine 100 may switch to second operation mode 102.
[0043] In an exemplary embodiment, processor 212 within control system 222 may execute control algorithms to adjust configurations of first flow control mechanism 114 and second flow control mechanism 118 in real-time, ensuring optimal performance under varyingREF- 1403-0308003operational conditions. In an exemplary embodiment, these adjustments may involve repositioning first damper 202 within first three-port valve 224 and second damper 204 within second three-port valve 226 through actuating by electric or pneumatic actuators (e.g. 312).
[0044] In further detail regarding FIG. 3, in an exemplary embodiment, system architecture may comprise communication pathways, including but not limited to buses or network interfaces that facilitate seamless data exchange between components of control system 222, such as sensors, actuators, and processors 212. In an exemplary embodiment, adaptive regenerative gas turbine 100 may support distributed processing environments, enabling localized decision-making for enhanced response times. In an exemplary embodiment, additional processors may be integrated into both first flow control mechanism 114 and second flow control mechanism 118, each performing localized computations. In an exemplary embodiment, control system 222 may include a display interface, for example a video connector, to transfer data to a display unit 310, for example, a monitor.
[0045] Referring to the figures, FIG. 4 illustrates a graphical representation of therelationship between third ratio, rcsw, and first dimensionless ratio, consistent with one T-Lor more exemplary embodiments of the present disclosure. As depicted in FIG. 4, in an exemplary embodiment, third ratio, rcsw, may exhibit an approximately linear relationship with first ratio.
[0046] In an exemplary embodiment, temperature of combustion gas stream, Tmax, may primarily depend on the type of fuel and the air-to-fuel ratio utilized in combustion process. Considering that the range of fuels typically employed in gas turbines may be limited, significant variations in temperature of combustion gas stream, Tmax, may be uncommon. InTan exemplary embodiment, linear relationship between rcswand may offer a predictable Aand stable foundation for control system adjustments. In an exemplary embodiment, control system 222 of adaptive regenerative gas turbine 100 may utilize linear relationship betweenREF- 1403-0308003Trcswand -2i2£to establish the optimal pressure ratio for switching damper configurations. As Aillustrated in FIG. 4, in an exemplary embodiment, based on the calculated first dimensionless ratio, control system 222 may determine rcswfor switching damper configuration using predefined calibration relationship. In an exemplary embodiment, the predefined calibration Trelationship may define a linear correlation between rcswand In an exemplary ATembodiment, predefined calibration relationship may be expressed as rvsw= A(-2i££.)+B. In anexemplary embodiment, A may be 3.6261 and B may be -8.6475.EXAMPLES
[0047] Hereinafter, one or more exemplary embodiments will be described in further detail with reference to examples. It will be obvious to a person having ordinary skill in the art that these examples may be for illustrative purposes only and are not to be interpreted to limit the scope of the present disclosure.
[0048] In an exemplary embodiment, the proposed adaptive regenerative gas turbine 100 (ARGT) operates in two distinct modes (i.e. 101 and 102). In an exemplary embodiment, as illustrated in FIG. IB, first operation mode 101 is a regenerative Brayton cycle (RB), utilizing a regenerator to recover exhaust heat and improve thermal efficiency. In an exemplary embodiment, as illustrated in FIG. 1C, second operation mode 102 may be an exemplary two-stage regenerative Brayton cycle (2TRB), incorporating a dual-stage expansion process to further enhance energy recovery. In an exemplary embodiment, the performance of Brayton cycle (B), RB cycle, 2TRB cycle, and proposed adaptive regenerative gas turbine 100 (ARGT) may be compared in three exemplary cases.Example 1: Comparative Performance Analysis of Thermal Efficiency, Net Specific Work, and Temperature of Exhaust Gas for B, RB, and 2TRB Cycles as Functions of Pressure RatioREF- 1403-0308003
[0049] In this example, for comparing performance and efficiency of three gas turbine configurations including Brayton cycle (B), regenerative Brayton cycle (RB), and regenerative Brayton cycle with two-stage turbines (2TRB), the following thermodynamic assumptions may apply.
[0050] In an exemplary embodiment, air stream may be modeled as an ideal gas with constant specific heat capacity, Cp, gas constant coefficient, R. and a constant ratio of specificheat capacity, K. Pressure drops across combustion chambers, regenerators, and pipelines may be assumed negligible. The maximum temperature of the cycle may remain constant and may occur at the exit of combustion chamber. The combustion process may be modeled as a heat transfer mechanism to air stream passing through combustion chamber. Processes within compressor and turbines may be adiabatic, with constant isentropic efficiencies. For configurations involving a regenerator, regenerator may be modeled as a counter-current heat exchanger with constant effectiveness. Table 1 summarizes the thermodynamic assumptions and properties used in this example.TABLE 1Operating parametersProperty SymbolValue(SIUnit) Specific heat capacity of the air stream Cp1.0 kJ / kgRatio of specific heat capacities of the air stream K 1-4Gas constant coefficientR0.287 kJ / kg Compressor isentropic efficienciesn0.85eTurbine isentropic efficiencies°-85Heat exchanger effectiveness£0.8Maximum normalized temperature of the cycle T1max / IT1i.n,c 5.333
[0051] In an exemplary embodiment, thermodynamic modeling of the B, RB and 2TRB cycles may involve four primary control volumes: compressor, regenerator, combustion chamber, and turbine. Each control volume may be analyzed independently using principles ofREF- 1403-0308003mass conservation, energy conservation, and exergy conservation. Governing equations may form the foundation for the thermodynamic analysis of each process.
[0052] In an exemplary embodiment, the ambient temperature, denoted as Tm,c, may serve as the inlet temperature to compressor and may correspond to Ti in state diagrams of the system. In an exemplary embodiment, the maximum temperature of the cycle, Tmax, may equate to the temperature of the exit of combustion chamber. Since air may be treated as an ideal gas, all temperatures within the thermodynamic equations may be expressed in Kelvin for consistency and accuracy.
[0053] To evaluate the performance of B, RB and 2TRB cycles, thermal efficiency r]thmay be computed as the ratio of the net specific work, wnet, to specific heat supplied to combustion chamber, qc.c.th = wnet / qc cEquation (1)
[0054] The specific work generated by a turbine, wt, may be expressed as:= Cp(Tin t- Tout t) = - rtQ1~k) / k), rtEquation (2)—Pin,t / Pout,t
[0055] The specific work consumed by compressor, wc, may be calculated as:wc= Cp(T0Ut,c- Tin,c) = CpTin^k~1} / k- 1) / 77C, rcEquation (3) Pout,c / Pin,c
[0056] The relationship between pressure ratio (rc) and pressure ratios of turbines (rtland rt2) may be expressed as follows:rc= rtl.rt2Equation (4)REF- 1403-0308003where rtland rt2are the pressure ratios of first turbine 112 and second turbine 116 in the two-stage turbines configuration.
[0057] The net specific work of the cycle (wnet) may then be computed as:Wnet Equation (5)
[0058] The specific heat supplied to combustion chamber (qc c) may be determined using the following relationship:Qc.c—Cp(Tmax Tjn c c') Equation (6)
[0059] For configurations involving a regenerator, regenerator may operate as a countercurrent heat exchanger. The heat transfer balance within regenerator may be represented as: Tin, hot ~—Tg^^gid — Tin coid— ^R(Tin,hot ~ 'T’tn.coid^ Equation (7)where ERis the effectiveness of regenerator, representing the efficiency of heat transfer between the two streams and Tout coidis the temperature of exhaust gas, Texh.
[0060] In an exemplary embodiment, the simultaneous solution of governing equations (Equations 1-7) for each control volume may determine thermal efficiency, ηth, net specific work, wnet, and temperature of exhaust gas, Texh, for the three B, RB and 2TRB configurations. In an exemplary embodiment, the performance of three B, RB and 2TRB configurations may be analyzed as functions of the pressure ratio, rc, of compressor, enabling a detailed comparative analysis of performance and efficiency, particularly highlighting the impact of the pressure ratio on thermal efficiency, net specific work, and temperature of exhaust gas.REF- 1403-0308003
[0061] Referring to the figures, FIG. 5 illustrates a comparative analysis of the thermal efficiencies of B, RB and 2TRB cycles as a function of pressure ratio, rc, consistent with one or more exemplary embodiments of the present disclosure. In an exemplary embodiment, identical operating conditions may be assumed for all B, RB and 2TRB cycles to ensure consistency and reliability in the analysis.
[0062] In an exemplary embodiment, the thermal efficiencies depicted in FIG. 5 may be determined through iterative solutions of thermodynamic equations applied to each cycle. The results may indicate that Brayton cycle (B) consistently exhibits the lowest efficiency among the three B, RB and 2TRB configurations, primarily due to the absence of a regenerative heat recovery mechanism. The regenerative Brayton cycle (RB), incorporating a regenerator, may demonstrate higher efficiencies at lower pressure ratios (e.g., between 2:1 and 10:1) by recovering exhaust heat to preheat compressed air entering combustion chamber.
[0063] In an exemplary embodiment, FIG. 5 may further reveal a performance crossover between the RB and 2TRB configurations at pressure ratios exceeding approximately 11. In an exemplary embodiment, for pressure ratios equal to or greater than 11 (rc> 11), 2TRB may demonstrate superior efficiency. The improvement in efficiency may result from the staged extraction of mechanical work and the optimized utilization of thermal energy within the regenerator. These enhancements may highlight the benefits of two- stage turbine configurations in high-pressure operating regimes.
[0064] Referring to the figures, FIG. 6 illustrates the variations in dimensionless specific power output, w^t / CpT^, for B, RB, and 2TRB configurations as a function of pressure ratio, rc, of compressor, consistent with one or more exemplary embodiments of the present disclosure. In an exemplary embodiment, dimensionless specific power output may represent net specific work produced by each cycle per unit mass of air processed.
[0065] In an exemplary embodiment, as illustrated in FIG. 6, the specific power outputs of B and RB remain identical across all pressure ratios. This trend may be attributed toREF- 1403-0308003regenerator in RB configuration, which may enhance thermal efficiency without significantly affecting the specific power output. Conversely, 2TRB may achieve higher specific power output at elevated pressure ratios. This improvement may result from the optimized work extraction facilitated by the two-stage turbine arrangement and the enhanced heat recovery enabled by regenerator.
[0066] In an exemplary embodiment, at lower pressure ratios (e.g. between 2: 1 and 30: 1), B and RB configurations may demonstrate comparable and higher specific power outputs compared to 2TRB configuration. As pressure ratio increases (e.g. beyond approximately 30: 1), the performance of 2TRB configuration may exceed that of B and RB configurations.
[0067] In an exemplary embodiment, the analysis depicted in FIG. 6 may highlight the trade-offs among the three configurations. B and RB may provide simplicity and operational efficiency, making them effective for low-pressure applications. In contrast, regenerative 2TRB may demonstrate superior performance in high-pressure regimes. The advanced design features of 2TRB may enhance both thermal efficiency and power output, demonstrating its suitability for demanding operational conditions.
[0068] Referring to the figures, FIG. 7 illustrates the variations in the dimensionless temperature of exhaust gas, T^ / T-, of B, RB, and 2TRB as a function of pressure ratio, rc, of compressor, consistent with one or more exemplary embodiments of the present disclosure
[0069] In an exemplary embodiment, temperature of exhaust gas may represent a critical parameter influencing both the performance and environmental impact of gas turbine cycles.FIG. 7 may demonstrate that the dimensionless temperature of exhaust gas of the 2TRB is consistently lower than that of B and RB configurations across all pressure ratios. This reduction may result from the enhanced utilization of thermal energy in the 2TRB cycle, enabled by its two-stage turbine arrangement and regenerator.
[0070] In an exemplary embodiment, the RB may exhibit slightly higher exhaust gas temperatures than the 2TRB at lower pressure ratios (e.g. between 2: 1 and 20: 1). However, atREF- 1403-0308003higher pressure ratios (e.g. rc> 11 ), 2TRB configuration may offer superior thermal performance and efficiency. Specifically, in high-pressure regimes (e.g. rc> 30), 2TRB cycle may outperform the RB cycle in both thermal efficiency and specific power output, while maintaining consistently lower exhaust gas temperatures.
[0071] In an exemplary embodiment, this comparative analysis may highlight the operational advantages of 2TRB cycle, particularly in high-pressure applications. The advanced design of 2TRB cycle may enable superior energy recovery and reduced thermal losses. Additionally, the consistently lower exhaust gas temperatures may indicate improved environmental performance, as lower exhaust temperatures may lead to reduced thermal pollution and enhanced compatibility with downstream systems.
[0072] In an exemplary embodiment, these findings may inspire the development of a novel gas turbine cycle configuration featuring an adaptive heat recovery system. Such a system may dynamically optimize the thermal performance of the cycle by leveraging the advantages of different Brayton cycle configurations across varying pressure ratios. This proposed adaptive regenerative gas turbine 100 (ARGT) may ensure consistently high efficiency across a broad range of operating conditions, forming the foundation of the claims described in this invention.
[0073] Referring to the figures, FIG. 8 illustrates the thermal efficiency, ηth, of the proposed adaptive regenerative gas turbine 100 (ARGT) as a function of pressure ratio, rc, of compressor, consistent with one or more exemplary embodiments of the present disclosure. ARGT may dynamically adjust its configuration to capitalize on the advantages of RB and 2TRB across varying pressure ratio regimes.
[0074] Previous analyses presented in FIG. 5 may demonstrate that RB achieves the highest thermal efficiency among B, RB and 2TRB cycles at lower compressor pressure ratios (e.g. rc< 11). Conversely, at higher pressure ratios (e.g. rc> 11), 2TRB may surpass both RB and B in thermal efficiency. FIG. 8 illustrates the proposed adaptive regenerative gas turbineREF- 1403-0308003100 (ARFT) cycle maintains consistently high thermal efficiency across a wide range of compressor pressure ratios. This adaptability may result from heat recovery system capable of dynamically switching between cycle configurations to optimize performance. The adaptive heat recovery system may ensure that thermal efficiency of the proposed ARGT cycle approaches or exceeds that of the optimal fixed-configuration cycles (RB or 2TRB) under all operating conditions.
[0075] In an exemplary embodiment, temperature of exhaust gas of ARGT may also remain consistently low, further enhancing its environmental performance and operational efficiency. These characteristics may represent a significant improvement over traditional fixed-configuration cycles by addressing the limitations of each cycle within specific pressure ratio ranges.Example 2: Comparative Analysis of Net Specific Work, Temperature of Exhaust Gas, and Thermal Efficiency for the Proposed ARGT Cycle vs. B, RB, and 2TRB Cycles at a Pressure Ratio of 6.
[0076] In an exemplary embodiment, the net specific work, temperature of exhaust gas, and thermal efficiency of proposed ARGT cycle with adaptive switching between operating modes (i.e. 101 and 102) are compared with those of the Brayton cycle (B), the regenerative Brayton cycle (RB), and the two-stage regenerative Brayton cycle (2TRB) at a low compressor pressure ratio of 6. At this pressure ratio (rc= 6), the proposed ARGT cycle operates in RB mode, utilizing a regenerator to recover waste heat from the exhaust gases and preheat the compressed air before combustion. This process enhances thermal efficiency and reduces temperature of exhaust gas. The assumed parameters for this analysis are summarized in Table 2 below:TABLE 2Operating parametersProperty Symbol Value (SI Unit) Pressure ratio of compressor rc6Specific heat capacity of the air stream Cp1.0 kJ / kgREF- 1403-0308003Ratio of specific heat capacities of the air stream K 1.4Gas constant coefficient R 0.287 kJ / kg Compressor isentropic efficiencies ηc1, ηc20.85 Turbine isentropic efficiencies ηt1, ηt20.85 combustion chamber effectiveness εr0.8 Maximum normalized temperature of the cycle Tmax / Tin,c5.333 Temperature of combustion gas stream Tmax1600 K Temperature of air streamTin c300 K pressure ratio of switching of damper10.73 configuration rcsw
[0077] The computed results of ARGT cycle vs. B, RB, and 2TRB cycles at a pressure ratio of 6 are shown in Table 3 below:TABLE 3Comparative results of ARGT cycle vs. B, RB, and 2TRB cycles at (rc= 6).Thermal Temperature of Net Specific Cycle TypeEfficiency Exhaust Gas (Texh) Work Brayton Cycle (B) 0.29035 3.5168 1.0297 Regenerative Brayton (RB) 0.47623 2.1325 1.0297 Two- stage Regenerative „.no 1,1.7922 0.5463 Brayton (2TRB)0'40816Proposed AdaptiveRegenerative gas Turbine 100 0.47623 2.1325 1.0297 (ARGT)
[0078] The results indicate that the proposed ARGT cycle, operating in RB mode (first operation mode 101) at pressure ratio of 6, achieves a significant improvement in thermal efficiency compared to the Brayton cycle. The reduction in temperature of exhaust gas suggests enhanced energy utilization and minimized heat loss.Example 3: Comparative Analysis of Net Specific Work, Temperature of Exhaust Gas, and Thermal Efficiency for the Proposed ARGT Cycle vs. B, RB, and 2TRB Cycles at a Pressure Ratio of 20.
[0079] In an exemplary embodiment, the performance of the proposed ARGT cycle is evaluated at a high compressor pressure ratio of 20. At this pressure ratio (rc= 20), the cycle transitions into 2TRB mode, employing a two-stage turbine configuration with an intermediateREF- 1403-0308003heat exchanger to optimize energy recovery. This mode allows for a more effective expansion process, further reducing the temperature of exhaust gas while maintaining high thermal efficiency.
[0080] Using the same assumed parameters as in Example 2, the cycle performance is compared with the Brayton, RB, and 2TRB cycles. The assumed parameters for this analysis are summarized in Table 4 below:TABLE 4Operating parametersProperty Symbol Value (SI Unit) Pressure ratio of compressor rc20Specific heat capacity of the air stream Cp1.0 kJ / kgRatio of specific heat capacities of the air1.4streamGas constant coefficient R 0.287 kJ / kg Compressor isentropic efficiencies Rcl’ Rc2 0.85Turbine isentropic efficiencies ηt1, ηt20.85combustion chamber effectiveness εr0.8Maximum normalized temperature of theTmax / Tin,c5.333cycleTemperature of combustion gas stream T ‘max 1600 KTemperature of air stream Tin,c300 Kpressure ratio of switching of damper10.73configuration rcsw
[0081] The computed results of ARGT cycle vs. B, RB, and 2TRB cycles at a pressure ratio of 20 are shown in Table 5 below:TABLE 5Comparative results of ARGT cycle vs. B, RB, and 2TRB cycles at (rc= 6).Net Thermal Temperature ofCycle Type Specific Efficiency Exhaust Gas (Texh)Work Brayton Cycle (B) 0.37021 2.7260 1.0146 Regenerative Brayton (RB) 0.38523 2.6191 1.0146 Two-stage Regenerative Brayton4(2TRB) 0.45423 1.9944 0.8276 Proposed Adaptive Regenerative „41.9944 0.8276 gas Turbine 100 (ARGT) 0.45423REF- 1403-0308003
[0082] These results confirm that at high-pressure ratios, the proposed ARGT cycle operates in 2TRB mode, benefiting from a staged expansion process that enhances efficiency. The reduced exhaust gas temperature highlights the superior thermal management of the proposed configuration, making it an ideal choice for high-efficiency power generation applications. The ability to switch between RB and 2TRB modes allows the proposed ARGT cycle to achieve optimal performance across a broad range of operating conditions, ensuring improved efficiency and energy utilization.
[0083] Furthermore, the proposed ARGT cycle demonstrates remarkable flexibility in adapting to different operating conditions while maintaining superior performance compared to conventional cycles. For instance, at low-pressure ratios (as shown in Example 2), the ARGT cycle operates in RB mode, achieving significant improvements in thermal efficiency without compromising net specific work. At high-pressure ratios, the ARGT cycle seamlessly transitions to 2TRB mode (as shown in Example 2), leveraging a two-stage expansion process to further enhance efficiency and reduce exhaust temperatures. This dual-mode adaptability ensures that the proposed ARGT cycle can operate efficiently across a wide spectrum of pressure ratios, making it highly versatile for various industrial applications.
[0084] The integration of adaptive switching between RB and 2TRB modes is a key innovation of ARGT cycle. By dynamically adjusting the operational mode based on real-time pressure conditions, the proposed cycle maximizes energy recovery, minimizes heat loss, and maintains optimal power output. This adaptability not only improves overall system performance but also extends the operational lifespan of the gas turbine by reducing thermal stresses associated with inefficient cycles.
[0085] While the foregoing has described what are considered to be the best mode and / or other examples, it is understood that various modifications may be made therein and that the subject matter disclosed herein may be implemented in various forms and examples, and that the teachings may be applied in numerous applications, only some of which have beenREF- 1403-0308003described herein. It is intended by the following claims to claim any and all applications, modifications and variations that fall within the true scope of the present teachings.
[0086] Unless otherwise stated, all measurements, values, ratings, positions, magnitudes, sizes, and other specifications that are set forth in this specification, including in the claims that follow, are approximate, not exact. They are intended to have a reasonable range that is consistent with the functions to which they relate and with what is customary in the art to which they pertain.
[0087] The scope of protection is limited solely by the claims that now follow. That scope is intended and should be interpreted to be as broad as is consistent with the ordinary meaning of the language that is used in the claims when interpreted in light of this specification and the prosecution history that follows and to encompass all structural and functional equivalents. Notwithstanding, none of the claims are intended to embrace subject matter that fails to satisfy the requirement of Sections 101, 102, or 103 of the Patent Act, nor should they be interpreted in such a way. Any unintended embracement of such subject matter is hereby disclaimed.
[0088] Except as stated immediately above, nothing that has been stated or illustrated is intended or should be interpreted to cause a dedication of any component, step, feature, object, benefit, advantage, or equivalent to the public, regardless of whether it is or is not recited in the claims.
[0089] It will be understood that the terms and expressions used herein have the ordinary meaning as is accorded to such terms and expressions with respect to their corresponding respective areas of inquiry and study except where specific meanings have otherwise been set forth herein. Relational terms such as first and second and the like may be used solely to distinguish one entity or action from another without necessarily requiring or implying any actual such relationship or order between such entities or actions. An element proceeded by “a” or “an” does not, without further constraints, preclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.REF- 1403-0308003
[0090] The Abstract of the Disclosure is provided to allow the reader to quickly ascertain the nature of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims. In addition, in the foregoing Detailed Description, it may be seen that various features are grouped together in various implementations. This is for purposes of streamlining the disclosure, and is not to be interpreted as reflecting an intention that the claimed implementations require more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive subject matter lies in less than all features of a single disclosed implementation. Thus, the following claims are hereby incorporated into the Detailed Description, with each claim standing on its own as a separately claimed subject matter.
[0091] While various implementations have been described, the description is intended to be exemplary, rather than limiting and it will be apparent to those of ordinary skill in the art that many more implementations and implementations are possible that are within the scope of the implementations. Although many possible combinations of features are shown in the accompanying figures and discussed in this detailed description, many other combinations of the disclosed features are possible. Any feature of any implementation may be used in combination with or substituted for any other feature or element in any other implementation unless specifically restricted. Therefore, it will be understood that any of the features shown and / or discussed in the present disclosure may be implemented together in any suitable combination. Accordingly, the implementations are not to be restricted except in light of the attached claims and their equivalents. Also, various modifications and changes may be made within the scope of the attached claims.
Claims
REF-1403-0308003What is claimed is:
1. An adaptive regenerative gas turbine being switchable between operating in a first operation mode and in a second operation mode, the adaptive regenerative gas turbine comprising:a compressor configured to compress an air stream from a first pressure to a second pressure;a first regenerator disposed at a downstream of the compressor and connected in fluid communication therewith, the first regenerator configured to preheat a compressed air stream received from the compressor by a heat exchange between the compressed air stream and a first heating fluid input in the first operation mode;a second regenerator disposed at a downstream of the first regenerator and connected in fluid communication therewith, the second regenerator configured to preheat the compressed air stream received from the compressor by a heat exchange between the compressed air stream and a second heating fluid input in the second operation mode; a combustion chamber disposed at a downstream of the second regenerator and connected in fluid communication therewith, the combustion chamber configured to receive the preheated compressed air stream to exhaust a combustion gas stream;a first turbine coupled to the compressor, the first turbine disposed at a downstream of the combustion chamber and connected in fluid communication therewith, the first turbine configured to receive the combustion gas stream to drive the compressor and exhaust a first exhaust stream;a second turbine configured to exhaust a second exhaust stream either from the first exhaust stream of the first turbine in the first operation mode or from a second heating fluid output of the second regenerator in the second operation mode, to drive an external load;a first flow control mechanism disposed at a downstream of the first turbine and connected in fluid communication therewith, the first flow control mechanism configuredREF-1403-0308003to selectively conduct the first exhaust stream either toward the second regenerator to serve as the second heating fluid input in the first operation mode or toward the second turbine in the first operation mode; anda second flow control mechanism disposed at a downstream of the second turbine and connected in fluid communication therewith, the second flow control mechanism configured to selectively conduct the second exhaust stream either toward the first regenerator to serve as the first heating fluid input in the first operation mode or toward an atmospheric discharge in the second operation mode.
2. The adaptive regenerative gas turbine of claim 1, wherein in the first operation mode, the first flow control mechanism directs the first exhaust stream from the first turbine to the second turbine, and the second flow control mechanism directs the second exhaust stream from the second turbine to the first regenerator.
3. The adaptive regenerative gas turbine of claim 1, wherein in the second operation mode, the first flow control mechanism directs the first exhaust stream from the first turbine to the second regenerator, and the second flow control mechanism directs the second exhaust stream from the second turbine to the atmospheric discharge.
4. The adaptive regenerative gas turbine of claim 1, wherein the first flow control mechanism comprises a first three-port valve including:a first inlet port being in a fluid communication with the first turbine and configured to receive the first exhaust stream from the first turbine;a first outlet port configured to direct the first exhaust stream from the first turbine to the second turbine in the first operation mode; anda second outlet port configured to direct the first exhaust stream from the first turbine to the second regenerator in the second operation mode;REF-1403-03080035. The adaptive regenerative gas turbine of claim 4, wherein the second flow control mechanism comprises a second three-port valve including:a second inlet port being in fluid communication with the second turbine and configured to receive the second exhaust stream from the second turbine;a third outlet port configured to direct the second exhaust stream from the second turbine to the first regenerator in the first operation mode; anda fourth outlet port configured to direct the second exhaust stream from the second turbine to the atmospheric discharge in the second operation mode.
6. The adaptive regenerative gas turbine of claim 5, further comprising a control system coupled with the first three-port valve and the second three -port valve, wherein the control system is configured to urge the first three -port valve to direct the first exhaust stream either toward the second turbine in the first operation mode or toward the second regenerator in the second operation mode, the control system is further configured to urge the second three-port valve to direct the second exhaust stream either toward the first regenerator in the first operation mode or toward the atmospheric discharge in the second operation mode.
7. The adaptive regenerative gas turbine of claim 6, wherein the control system comprises:at least one processor; andat least one memory coupled to the at least one processor, the at least one memory storing executable instructions to urge the at least one processor to:receive a temperature of the combustion gas stream, Tmax, a temperature of the air stream, T1the first pressure and the second pressure of the air stream; calculate a first dimensionless ratio equal to the temperature of the combustion gas stream, Tmax, divided by the temperature of the air stream, T1;REF-1403-0308003calculate a second ratio, rc, equal to the second pressure divided by the first pressure;retrieve a predefined calibration relationship between the first dimensionless ratio and a third ratio, rpsw, wherein at the third ratio the first flow control mechanism and the second flow control mechanism change corresponding operation modes;determine the third ratio based on the first dimensionless ratio and the predefined calibration relationship;change a configuration of the first flow control mechanism and a configuration of the second flow control mechanism based on at least one of the predefined calibration relationship and the third ratio;urge the first flow control mechanism to adjust a configuration of the first three-port valve to selectively conduct the first exhaust stream either toward the second turbine in the first operation mode or toward the second regenerator in the second operation mode; andurge the second flow control mechanism to adjust a configuration of the second three-port valve to selectively conduct the second exhaust stream either toward the first regenerator in the first operation mode or toward the atmospheric discharge in the second operation mode.
8. The adaptive regenerative gas turbine of claim 7, wherein the third ratio is defined by an operation as follows:rpsw= 3.6261 (Tmax / T1) - 8.6475.
9. The adaptive regenerative gas turbine of claim 7, wherein:REF-1403-0308003when the second ratio is less than the third ratio, the adaptive regenerative gas turbine operates in the first operation mode; andwhen the second ratio is greater than or equal to the third ratio, the adaptive regenerative gas turbine operates in the second operation mode.
10. The adaptive regenerative gas turbine of claim 7, wherein the first pressure of the air stream equals to an atmospheric pressure.
11. The adaptive regenerative gas turbine of claim 1, wherein the first turbine drives the compressor via a first shaft coupled therebetween.
12. The adaptive regenerative gas turbine of claim 1, wherein the external load comprises an electricity generator to which the second turbine is coupled via a second shaft.