Improved turbo-compressor system

Abstract

A turbo-compressor system is disclosed, comprising a multi-shaft gas turbine for power generation. The gas turbine includes a gas generator creating an exhaust gas flow, a power turbine or low-pressure turbine, and an internal coupling shaft linking these elements. The gas turbine's operation is defined by flow rate and pressure differential. The system also comprises a rotary compressor with rotating blades for gas compression, connected to the power turbine via a main coupling shaft. The turbo-compressor system features inlet guide vanes at the compressor's entrance and variable area turbine nozzles between the gas generator and power turbine, to enable the adjustment of both the compressed and exhaust gas flows. The system's design allows for the control of the gas turbine's operating point through the coordinated manipulation of the inlet guide vanes and variable area turbine nozzles.

Description

Improved Turbo-Compressor SystemDescriptionTECHNICAL FIELD

[0001] The present disclosure concerns an improved turbo-compressor or driving system, which combines variable geometry elements at both the power turbine and the driven compressor.BACKGROUND ART

[0002] Turbo-compressor train technology has consistently sought to address the issue of maintaining efficiency under varying operational conditions. Specifically, the efficiency of a turbo-compressor train during off-design conditions - where the flow rate, pressure, temperature, or gas composition does not align with the optimal design specifications - has been a long-standing design challenge. The deviations from the design point can lead to reduced compressor performance, increased energy consumption, and accelerated wear, all of which are undesirable in industrial processes.

[0003] In the field, there are some known solutions aimed at mitigating these inefficiencies by implementing bypass solutions. These solutions generally involve a system of valves and alternate flow paths that can divert the process fluid away from certain components of the turbo-compressor when operating under off-design conditions. A bypass solution can help maintain the compressor's efficiency by reducing the flow through the compressor, thus allowing it to operate closer to its intended design point.

[0004] However, the known art exhibits significant drawbacks. For instance, in the market have been recently introduced bypass solutions that, however, are not as effective as desired. Such a system uses a valve to bypass the combustor and the High- Pressure Turbine (HPT), redirecting the flow upstream of the Low-Pressure Turbine (LPT). This method, albeit partially effective in alleviating the compressor’s load, introduces a new set of problems. The abrupt diversion of fluid can lead to imbalances and suboptimal flow angles, particularly at the metallic surfaces of the LPT blades, which are not designed to accommodate such a range of angles.

[0005] Another important technical problem that arises from the known art, is the adjustment of metal angles to accommodate a wider range of fluid angles without compromising the integrity and performance of the turbo-compressor. In off-design conditions, the angle at which the fluid enters the LPT can vary significantly, which in turn can cause reduced efficiency, increased stress on the components, and an overall decline in the lifespan of the equipment.

[0006] The prior art fails to provide a satisfactory solution to this problem, as the existing bypass systems do not address the issue of metal angle adjustment. The known solutions may bypass critical components like the combustor and HPT, but they do not adequately manage the reintroduction of fluid in a manner that preserves the aerodynamic efficiency of the LPT, nor do they allow for the necessary flexibility in metal angle accommodation. As such, there is felt a need for an improved solution that overcomes these limitations, providing a means to maintain high efficiency and equipment longevity even in the face of wide-ranging operational demands.

[0007] Accordingly, an improved turbo-compressor capable of improving the operations and broadening the operational ranges would be welcomed in the technology.SUMMARY

[0008] In one aspect, the subject matter disclosed herein concerns a turbo-compressor system. This system includes a multi-shaft gas turbine designed to generate power, featuring a gas generator that produces an exhaust gas flow, a power turbine or low- pressure turbine, and an internal coupling shaft linking the gas generator to the power turbine or low-pressure turbine. The operation of this gas turbine is characterized by specific parameters such as flow rate and pressure differential. Additionally, the system comprises a rotary compressor equipped with rotating blades to compress a gas by reducing its volume, and a main coupling shaft that connects the power turbine or low- pressure turbine to the compressor. A characteristic of this turbo-compressor system is an inlet flow control device positioned at the entrance of the compressor. This device directs the compressed gas flow into the rotor blades of the compressor, and its adjustment enables the tuning of the system's operating point.

[0009] In another aspect, disclosed herein is a turbo-compressor system where the inlet flow control device includes a set of inlet guide vanes. These vanes, arranged at thecompressor's entrance, are responsible for directing the compressed gas flow into the rotor blades of the compressor.

[0010] A further aspect of the present disclosure is drawn to a turbo-compressor system in which the inlet flow control device comprises one or more throttling valves.

[0011] In another aspect, the subject matter concerns a turbo-compressor system that includes a set of variable area turbine nozzles. These nozzles, situated between the gas generator and the power turbine or low-pressure turbine, are used to adjust the exhaust gas flow by changing the nozzle area. The combined adjustment of these variable area turbine nozzles with the inlet flow control device further allows for the tuning of the system's operating point.

[0012] In another aspect, disclosed herein is a turbo-compressor system where the rotary compressor includes a chamber. This chamber is used to drive the compressed gas flow, which is influenced by the inlet flow control device.

[0013] A further aspect of the present disclosure is drawn to a turbo-compressor system that includes a control logic unit. This unit is connected to the first actuating means of the variable area turbine nozzles and to the second actuating means of the inlet guide vanes, allowing for independent adjustment of these components to adjust the system's operating point.

[0014] In another aspect, the subject matter concerns a turbo-compressor system where the control logic unit is programmable and capable of performing automatic multi-objective optimization algorithms.

[0015] In another aspect, disclosed herein is a turbo-compressor system that includes devices for measuring speed, such as encoders, located on both the internal and main coupling shafts. These devices are connected to the control logic unit, enabling feedback that broadens the compressor’s operating map.

[0016] A further aspect of the present disclosure is drawn to a turbo-compressor system where the gas turbine includes a gas generator, having a gas-generator compressor, a high-pressure turbine, and a combustor.BRIEF DESCRIPTION OF THE DRAWINGS

[0017] A more complete appreciation of the disclosed embodiments of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings, wherein:Fig. 1 illustrates a schematic of an embodiment of a drive system;Fig. 2 illustrates a graph showing the output shaft power as a function of the output shaft speed, according to the first embodiment; andFig. 3 illustrates a compressor map, according to the first embodiment.DETAILED DESCRIPTION OF EMBODIMENTS

[0018] According to one aspect, the present subject matter is directed to an innovative configuration for turbo-compression systems used in various applications, including pipelines, which aims to enhance the turndown capability, i.e., the ability to operate efficiently at reduced loads, without sacrificing performance in terms of efficiency and emissions. Traditionally, turbo-compression systems face challenges in maintaining efficiency at lower operating rates, often leading to increased emissions and reduced operational flexibility. The present subject matter addresses these limits / problems by incorporating variable geometry elements in both the driver (inter-turbine nozzle) and the driven (inlet guide vanes of the rotary compressor). These two degrees of freedom maximize the system flexibility in terms of flow while maximizing efficiency over this wide range of flow.

[0019] The variable inlet nozzles on the power turbine allow for precise control of the gas generator speed, which in turn, can be fine-tuned to match the power requirements of the process without excess energy expenditure. Also, the variable inlet nozzles adjust to accommodate different volumetric flows, ensuring that the compressor operates efficiently across a range of conditions. This dual application of variable inlet nozzles represents a significant advancement in turbo-compression technology, offering a solution that enables lower operational capacities while maintaining optimal efficiency and meeting stringent emission standards.

[0020] Referring now to the drawings, Fig. 1 shows a schematic of an embodiment of a driving system 1.

[0021] The driving system 1 comprises a multi-shaft gas turbine 2, for the generation of power. The gas turbine 2 comprises a gas generator 21 that generates an exhaust gas flow EGF, a power turbine or low-pressure turbine 22, and an internal fluid dynamic coupling 23. The fluid dynamic coupling 23 is linkage between the gas generator 21 and the power turbine or low-pressure turbine 22. The operation of the gas turbine 2 is characterized by an operating point that is defined by parameters such as the flow rate and the pressure differential.

[0022] The flow rate refers to the volume of gas passing through the gas turbine 2 per unit of time, while the head or pressure differential refers to the increase in pressure that the gas achieves as it passes through the compressor part of the turbine 2.

[0023] A rotary compressor 4 within the system contains rotating blades 42 that compress a gas flow CGF by reducing its volume, thereby increasing its pressure.

[0024] The main coupling shaft 3 connects the power turbine or low-pressure turbine 22 to the compressor 4, enabling the transfer of energy from the turbine to the compressor 4.

[0025] The driving system 1 comprises also a set of inlet guide vanes 6 that are arranged at the entrance of the compressor 4. The inlet guide vanes 6 are adapted to direct the compressed gas flow CGF into the rotor blades of the compressor 4. The adjustment of the inlet guide vanes 6 allows for modifying the flow and pressure conditions within the compressor 4, which in turn affects the operating point of the gas turbine 2.

[0026] In general, the driving system comprises an inlet flow control device 6, capable of directing the compressed gas flow CGF into the rotor blades of the compressor 4. In other embodiments, the inlet flow control device 6 may comprise a throttle valve or more than one throttle valve.

[0027] The inlet guide vanes 6 are operated by IGV actuating means 61, capable of changing the position of the vanes 6.

[0028] One embodiment of the actuating means 61 for inlet guide vanes includes a hydraulic actuator system. The hydraulic actuator is designed to adjust the angle of the inlet guide vanes based on fluid pressure changes. This system comprises a hydraulicpump, a fluid reservoir, and a series of control valves that manage the flow of hydraulic fluid to the actuators. The hydraulic actuators are connected to the inlet guide vanes through a linkage mechanism (not shown in the figures).

[0029] Another embodiment involves the use of an electromechanical actuator system, which employs electric motors connected to the variable area turbine nozzles 5 via gear assemblies or direct drive mechanisms. The electric motors (not shown in the figures) are controlled by a logic control unit, which receives signals based on the desired vane 6 position.

[0030] A further embodiment comprises a pneumatic actuator system for the adjustment of inlet guide vanes 6. This system utilizes air pressure to move the actuators and, consequently, the vanes. Compressed air is supplied by a compressor and is directed to the pneumatic actuators through a network of valves and hoses. The pneumatic system is usually controlled by a series of solenoid valves that respond to electronic control signals, providing a responsive and cost-effective solution for vane actuation.

[0031] The driving system 1 also comprises a set of variable area turbine nozzles 5 (VATN), situated between the gas generator 21 and the power turbine 2 or low-pressure turbine 22. These variable area turbine nozzles 5 can adjust the exhaust gas flow EGF by changing the nozzle area, then adjusting the energy delivery to the power turbine 2 thus enabling control over the gas turbine's operating point.

[0032] The variable area turbine nozzles 5 are arranged at the entrance of the power turbine or low-pressure turbine 22 of the gas turbine 2. Their primary function is to control the exhaust gas flow EGF into the gas turbine 2 by changing the nozzle area. This affects the mass flow rate, velocity, and pressure of the gases impinging on the power turbine or low-pressure turbine 22 blades (not shown in the figures).

[0033] By varying the area, the variable area turbine nozzles 5 can optimize the gas turbine’s 2 performance at different speeds, loads, and ambient conditions. They are especially important in maintaining efficiency and performance when the gas turbine 2 is not operating at its design point.

[0034] The variable area turbine nozzles 5 are operated by VATN actuating means 51,which allow for opening or closing the nozzles. The VATN actuating means 51 can be of different types. In one embodiment, the VATN actuating means 51 involves a hydraulic actuation system, including a series of hydraulic actuators connected to the turbine nozzles. The actuators are controlled by a hydraulic fluid, which is regulated by a control unit based on the turbine's operational parameters.

[0035] Another embodiment includes a pneumatic actuation system. This system utilizes pneumatic actuators that are linked to the turbine nozzles. The actuators are driven by compressed air or gas, and controlled through valves that respond to the gas turbine’s 2 operating conditions.

[0036] A further embodiment of variable area turbine nozzles 5 is based on an electromechanical actuation system, which employs electric motors connected to gear mechanisms that drive the movement of the turbine nozzles 5. The electric motors are governed by an electronic control unit, which adjusts the nozzle area in response to sensor inputs reflecting the turbine's performance.

[0037] The rotary compressor 4 further comprises a chamber 41, in which the compressed gas flow CGF is managed and directed by the inlet guide vanes 6, ensuring efficient compression and flow dynamics within the driving system 1.

[0038] The driving system 1 also comprises a control logic unit U, which is operatively connected to the VATN actuating means 51 of the variable area turbine nozzles 5 and to the IGV actuating means 61 of the inlet guide vanes 6. The control logic unit U has the capacity to independently adjust these components, thus fine-tuning the operating point of the gas turbine 2 for optimal performance under varying conditions.

[0039] The control logic unit U can be implemented in several ways. In one embodiment, the control logic unit U can be implemented as a programmable microprocessor, which is a compact and highly efficient option. Microprocessors offer high processing speeds and can be customized for specific control tasks.

[0040] In another embodiment, the control logic unit U can be a PLC (Programmable Logic Controller), on the other hand, is specifically designed for industrial control applications, making it a robust and reliable choice. PLCs are known for their durabilityand resistance to harsh industrial environments, including vibrations, temperature variations, and electrical noise.

[0041] In some other embodiments, the control logic unit U can be integrated in a computer, thus offering the most flexibility and computational power among the alternatives.

[0042] To enable precise control and feedback, the driving system comprises a device for measuring speed 62, installed on the main coupling shaft 3. Both devices are operatively connected to the control logic unit U, allowing for a feedback loop that can expand the compressor's operating map and adapt to different performance requirements.

[0043] In an embodiment of the devices for measuring speed 62 comprises an optical encoder-based speed measurement device, such devices comprise an optical encoder attached to the relevant rotating shaft. The encoder has a disc with precisely spaced markings, and one or more optical sensors positioned adjacent to the disc. As the shaft rotates, the markings on the disc intermittently block and allow light to reach the sensors, generating a pulse signal. The frequency of this pulse signal is directly proportional to the speed of the rotating shaft, thereby allowing for an accurate measurement of rotational speed.

[0044] Another embodiment of devices for measuring speed 62 incorporates an Hall effect sensor-based devices 62 for measuring the speed of a rotating shaft. This type of device utilizes a magnet attached to the rotating shaft and a Hall effect sensor mounted nearby. As the shaft rotates, the magnetic field passing in front of the Hall effect sensor changes, inducing a voltage in the sensor. The frequency of the voltage changes is directly related to the speed of the shaft, providing a means to measure the rotational speed accurately.

[0045] The control logic unit U is programmable and capable of performing automatic multi-objective optimization algorithms. This programmability facilitates the optimization of various operational parameters, ensuring the drive system’s 1 efficiency and adaptability to a range of objectives, such as fuel efficiency, emission reduction, and operational longevity.

[0046] In accordance with the present disclosure, the coordinated operation of the turbo-compressor system 1 is achieved through the control logic unit U, which is configured to regulate both the variable area turbine nozzles 5 and the inlet flow control device 6.

[0047] The control logic unit U dynamically adjusts the position of the variable area turbine nozzles 5 to modulate the exhaust gas flow and turbine performance, thereby influencing the rotational speed of the compressor 4. At the same time, the inlet flow control device 6 is adjusted to regulate the incoming air flow to the compressor 4, ensuring optimal pressure and flow conditions at its inlet.

[0048] This coordinated adjustment by the control logic unit U enables the tuning of the operating point of the turbo-compressor system 1, improving efficiency and ensuring stable operation across a wide range of operating conditions. The interplay between the variable area turbine nozzles 5 and the inlet flow control device 6 allows the system to respond effectively to changes in load demands, environmental conditions, or other external factors, thus enhancing the overall performance and reliability of the turbocompressor system.

[0049] The driving system 1 operates as follows.

[0050] Reference is made to Fig. 2 and Fig. 3. Specifically, Fig. 2 illustrates a set of curves concerning the dependence of the gas turbine 2 power generated (ordinate) as a percentage and the speed of the main shaft 3 (abscissa) as a percentage. In the graph are plotted several curves This curve illustrates how the rotational speed of the gas turbine 2 (comprising the compressor and the high-pressure turbine) affects the power output of the gas turbine 2.

[0051] Fig. 3 is a compressor map, having on the abscissa the normalized inlet volume flow, indicated with Q / Qv, namely, the compressed gas flow CGF, and on the ordinate the normalized isentropic head, which is the energy transfer in a fluid machine, namely the compressor or gas turbine 2 under the assumption of an isentropic process. It is a theoretical maximum efficiency that the machine can achieve in the absence of any irreversibilities like friction, heat transfer, or shock losses.

[0052] By Fig. 2 and Fig. 3, two distinct scenarios are considered to illustrate the operational flexibility and efficiency improvements in a rotary compressor 4 equipped with variable area turbine nozzles 5 and moveable inlet guide vanes 6, in the following referred to as “Scenario 1” and the “Scenario 2”.

[0053] In Scenario 1, a conventional compressor map (Fig. 3) is unable to cover certain operational points, namely B1.0 and Bl.2, at an inlet guide vanes 5 position angle setting of 0°, limiting the operational range and flexibility of the rotary compressor 4.

[0054] However, by integrating the operation of the variable area turbine nozzles 5 and the inlet guide vanes 6 at each stage of the process rotary compressor 4, the turndown capability is significantly enhanced. This adaptation allows the rotary compressor 4 to cover points B1.0 and Bl.2 (see Fig. 3) without resorting to anti-surge valve (ASV) recycle.

[0055] The implementation of the variable area turbine nozzles 5 and the inlet guide vanes 6 leads to a considerable reduction in the absorbed power by the rotary compressor 4, compared to the power required during anti-surge valve recycle operations. This reduction in energy consumption translates directly into an improvement in the overall system efficiency.

[0056] Scenario 2 addresses an operational point, Bl.6 (see Fig. 2 and Fig. 3), which is within the existing capabilities of the compressor map at an inlet guide vanes 6 position angle of 0°. In such operating conditions, closing the inlet guide vanes 6, optimally at each compressor stage, necessitates an increase in the rotating speed of the power turbine or low-pressure turbine 22, to maintain coverage of point Bl.6, which can be achieved by independently managing the operation of the variable area turbine nozzles 5 through the VATN actuating means 51.

[0057] This increase in rotational speed may lead to an overall enhancement of the system’s efficiency, as evidenced by reduced fuel consumption. The actual efficiency gains are dependent on the balance between low-pressure turbine 22 efficiency and process or driven compressor 4 efficiency, which are influenced by the rotating speed and the settings of the variable area turbine nozzles 5 and inlet guide vanes 6. This scenario emphasizes the capability of the drive system 1 to adapt to operational demands while optimizing performance, particularly in terms of fuel efficiency, which isa critical consideration in compressor technology.

[0058] The different operating states are characterized by flow rate and pressure differential, which are continuously detected and managed by the control logic unit U. The different operating conditions are also detected by the control logic unit U acquiring the speeds of the fluid dynamic coupling 23 and the main shaft 3, which are continuously detected and controlled. The control logic unit U is able to control the VATN actuating means 51 and the IGV actuating means 61, to vary the speeds of the fluid dynamic coupling 23 and the main shaft 3 and then the flow rate and pressure differential.

[0059] The control logic unit U is designed to execute automatic multi-objective optimization algorithms. These algorithms are integral to the control unit’s U functionality, enabling it to dynamically and efficiently manage the operation of a gas turbine 2. The control unit’s U focus is on optimizing the gas turbine 2 performance by controlling its operating point, which is determined, as mentioned above, by critical parameters such as flow rate and pressure differential.

[0060] The flow rate parameter determines the volume of air or gas passing through the gas turbine 2 at any given moment. The pressure differential is managed by the control logic unit U to monitor and adjust the difference in pressure across the turbine system, which directly impacts the turbine’s 2 energy output and overall efficiency. By tuning this pressure differential, the control logic unit U ensures that the turbine operates within its optimal performance envelope, thereby enhancing its efficiency and prolonging its service life.

[0061] Furthermore, the control logic unit’s U capability of performing multi-objective optimization allows it to balance multiple operational objectives simultaneously, such as maximizing energy output, minimizing fuel consumption, reducing emissions, and extending the lifespan of gas turbine 2 components. The control logic unit U achieves this balance by constantly analyzing operational data and making real-time adjustments to the gas turbine 2 control parameters.

[0062] While aspects of the invention have been described in terms of various specific embodiments, it will be apparent to those of ordinary skill in the art that many modifications, changes, and omissions are possible without departing form the spirt andscope of the claims. In addition, unless specified otherwise herein, the order or sequence of any process or method steps may be varied or re-sequenced according to alternative embodiments.

[0063] Reference has been made in detail to embodiments of the disclosure, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the disclosure, not limitation of the disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the disclosure. Reference throughout the specification to "one embodiment" or "an embodiment" or “some embodiments” means that the particular feature, structure or characteristic described in connection with an embodiment is included in at least one embodiment of the subject matter disclosed. Thus, the appearance of the phrase "in one embodiment" or "in an embodiment" or "in some embodiments" in various places throughout the specification is not necessarily referring to the same embodiment(s). Further, the particular features, structures or characteristics may be combined in any suitable manner in one or more embodiments.

[0064] When elements of various embodiments are introduced, the articles “a”, “an”, “the”, and “said” are intended to mean that there are one or more of the elements. The terms “comprising”, “including”, and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements.

[0065] The subject matter described herein can be implemented in digital electronic circuitry, or in computer software, firmware, or hardware, including the structural means disclosed in this specification and structural equivalents thereof, or in combinations of them. The subject matter described herein can be implemented as one or more computer program products, such as one or more computer programs tangibly embodied in an information carrier (e.g., in a machine-readable storage device), or embodied in a propagated signal, for execution by, or to control the operation of, data processing apparatus (e.g., a programmable processor, a computer, or multiple computers). A computer program (also known as a program, software, software application, or code) can be written in any form of programming language, including compiled or interpreted languages, and it can be deployed in any form, including as a stand-alone program or as a module, component, subroutine, or other unit suitable foruse in a computing environment. A computer program does not necessarily correspond to a file. A program can be stored in a portion of a file that holds other programs or data, in a single file dedicated to the program in question, or in multiple coordinated files (e.g., files that store one or more modules, sub-programs, or portions of code). A computer program can be deployed to be executed on one computer or on multiple computers at one site or distributed across multiple sites and interconnected by a communication network.

[0066] The processes and logic flows described in this specification, including the method steps of the subject matter described herein, can be performed by one or more programmable processors executing one or more computer programs to perform functions of the subject matter described herein by operating on input data and generating output. The processes and logic flows can also be performed by, and apparatus of the subject matter described herein can be implemented as, special purpose logic circuitry, e.g., an FPGA (field programmable gate array) or an ASIC (application-specific integrated circuit).

[0067] Processors suitable for the execution of a computer program include, by way of example, both general and special purpose microprocessors, and any one or more processors of any kind of digital computer. Generally, a processor will receive instructions and data from a read-only memory, or a random access memory, or both. The essential elements of a computer are a processor for executing instructions and one or more memory devices for storing instructions and data. Generally, a computer will also include, or be operatively coupled to receive data from or transfer data to, or both, one or more mass storage devices for storing data, e.g., magnetic, magneto-optical disks, or optical disks. Information carriers suitable for embodying computer program instructions and data include all forms of non-volatile memory, including by way of example semiconductor memory devices, (e.g., EPROM, EEPROM, and flash memory devices); magnetic disks, (e.g., internal hard disks or removable disks); magneto-optical disks; and optical disks (e.g., CD and DVD disks). The processor and the memory can be supplemented by, or incorporated in, special purpose logic circuitry.

[0068] To provide for interaction with a user, the subject matter described herein can be implemented on a computer having a display device, e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor, for displaying information to the user and akeyboard and a pointing device, (e.g., a mouse or a trackball), by which the user can provide input to the computer. Other kinds of devices can be used to provide for interaction with a user as well. For example, feedback provided to the user can be any form of sensory feedback, (e.g., visual feedback, auditory feedback, or tactile feedback), and input from the user can be received in any form, including acoustic, speech, or tactile input.

[0069] The techniques described herein can be implemented using one or more modules. As used herein, the term “module” refers to computing software, firmware, hardware, and / or various combinations thereof. At a minimum, however, modules are not to be interpreted as software that is not implemented on hardware, firmware, or recorded on a non-transitory processor readable recordable storage medium (i.e., modules are not software per se). Indeed “module” is to be interpreted to always include at least some physical, non-transitory hardware such as a part of a processor or computer. Two different modules can share the same physical hardware (e.g., two different modules can use the same processor and network interface). The modules described herein can be combined, integrated, separated, and / or duplicated to support various applications. Also, a function described herein as being performed at a particular module can be performed at one or more other modules and / or by one or more other devices instead of or in addition to the function performed at the particular module. Further, the modules can be implemented across multiple devices and / or other components local or remote to one another. Additionally, the modules can be moved from one device and added to another device, and / or can be included in both devices.

[0070] The subj ect matter described herein can be implemented in a computing system that includes a back-end component (e.g., a data server), a middleware component (e.g., an application server), or a front-end component (e.g., a client computer having a graphical user interface or a web browser through which a user can interact with an implementation of the subject matter described herein), or any combination of such back-end, middleware, and front-end components. The components of the system can be interconnected by any form or medium of digital data communication, e.g., a communication network. Examples of communication networks include a local area network (“LAN”) and a wide area network (“WAN”), e.g., the Internet.

Claims

Improved Turbo-Compressor SystemCLAIMS1. A turbo-compressor system (1), comprising: a multi-shaft gas turbine (2) configured to generate power, comprising a gas generator (21), generating an exhaust gas flow (EGF), a power turbine or low-pressure turbine (22), and a fluid dynamic coupling (23), connecting the gas generator (21) to the power turbine or low-pressure turbine (22), wherein the gas turbine (2) operates in an operating point defined at least by the parameters of the flow rate and pressure differential; a rotary compressor (4) comprising rotating blades (42) to compress a gas (CGF) by reducing its volume, wherein the rotary compressor (4) is connectable to an external load; a main coupling shaft (3), connecting the power turbine or low-pressure turbine (22) to the compressor (4); wherein the power turbine or low-pressure turbine (22) comprises a set of variable area turbine nozzles (5), to adjust the exhaust gas flow (EGF) into the power turbine or low-pressure turbine (22) by changing the nozzle area, arranged between the gas generator (21) and the power turbine or low-pressure turbine (22); wherein the turbo-compressor system (1) comprises an inlet flow control device (6) to direct the compressed gas flow (CGF) into the rotor blades of the compressor (4), arranged at the entrance of the compressor (4); wherein the set of variable area turbine nozzles (5) are arranged between the gas generator (21) and the power turbine or low-pressure turbine (22); wherein the combined adjustment of the variable area turbine nozzles (5) and the inlet flow control device (6) allows adjusting the operating point of the turbo-compressor system (1), and wherein the inlet flow control device comprises a set of inlet guide vanes (6), to direct the compressed gas flow (CGF) into the rotor blades of the compressor (4), arranged at the entrance of the compressor (4).

2. The turbo-compressor system (1) according to claim 1, wherein the inlet flow control device (6) comprises one or more a throttling valves.

3. The turbo-compressor system (1) according to the preceding claim, wherein the gas generator (21) comprises a gas-generator compressor (211), a high-pressure turbine (212), and a combustor (213), and wherein the set of variable area turbine nozzles (5) are arranged between the combustor (213) and the power turbine or low-pressure turbine (22).

4. The turbo-compressor system (1) according to any one of the preceding claims, wherein the rotary compressor comprises a chamber (41), in which the compressed gas flow (CGF) is driven by the inlet flow control device (6).

5. The turbo-compressor system (1) according to any one of the preceding claims, when depending on claims 2 and 4, comprising a control logic unit (U), wherein the variable area turbine nozzles (5) comprise first actuating means (51), for adjusting the nozzle area, wherein the inlet guide vanes (6) comprise second actuating means (61), for adjusting the angle of each vane, and wherein the control logic unit (U) is operatively connected to the first actuating means (51) and to the second actuating means (61), for independently adjusting the variable area turbine nozzles (5) and the inlet guide vanes (6) allows adjusting the operating point of the turbo-compressor system (1).

6. The turbo-compressor system (1) according to the preceding claim, wherein the control logic unit (U) is programmable, and wherein the control logic unit (U) is capable of performing automatic multiobjective optimization algorithms.

7. The turbo-compressor system (1) according to any one of claims 5or 6, comprising a device for measuring speed (62), such as an encoder, arranged on the main coupling shaft (3) and operatively connected to the control logic unit (U), wherein the control logic unit (U) is configured to allow a feedback from the speed device (62) to broaden the compressor operating map.

8. The turbo-compressor system (1) according to any one of the preceding claims, wherein gas turbine (2) comprises: a gas generator (21), comprising a gas-generator compressor (211), a high-pressure turbine (212), and a combustor (213); wherein the fluid dynamic coupling (23) couples the combustor (213) and the power turbine or low-pressure turbine (22).

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