JP2018510289A - Apparatus, system, and method for compressing a process fluid - Google Patents

Abstract

The supersonic compressor of the present invention includes an inlet configured to receive and flow process fluid. The supersonic compressor may further include a rotating shaft and a centrifugal impeller coupled thereto. The centrifugal impeller may be configured to energize the received process fluid to at least partially radially release the process fluid at an outlet absolute Mach number of about 1 or more. The supersonic compressor may further include a stationary diffuser disposed circumferentially around the centrifugal impeller and configured to receive process fluid from the centrifugal impeller and convert the applied energy. The supersonic compressor may further include a collector fluidly coupled to collect process fluid discharged from the diffuser such that the supersonic compressor is configured to provide a compression ratio of at least about 8: 1. Good.

Description

  This invention was made with government support under government contract number DOE-DE-FE000003 granted by the US Department of Energy. The government has certain rights in the invention.

  This application is a US patent having US Provisional Patent Application No. 62 / 139,027 filed on March 27, 2015 and US Patent Application No. 15 / 073,820 filed on March 18, 2016. Claims the benefit of the application. The aforementioned patent application is hereby incorporated by reference in its entirety to the extent that it is consistent with the present application.

  Compressors and systems including compressors have already been developed, and these are typically applied by applying mechanical energy to the gas in a low pressure environment and transferring the gas to the high pressure environment. By compressing, it is used in a wide variety of industrial processes (such as oil refineries, offshore oil production platforms, and subsea process control systems) to compress gas. Compressed gas may be utilized for efficient work performance or one or more downstream process operations. Conventional compressors are used in an increasing number of offshore oil production facilities and other environments and face space constraints. Thus, the demand for smaller, lighter and more compact compressors is increasing. In addition, for commercial purposes, it is desirable for such compact compressors to achieve higher compression ratios (eg, 10: 1 or higher) while maintaining a compact configuration.

  In view of the above, those skilled in the art often attempt to achieve higher compression ratios by increasing the number of compression stages in the compressor. However, increasing the number of compression stages increases the components required to achieve the desired compressor throughput (eg, mass flow) and pressure increase to achieve higher compression ratios (eg, impellers and / or Increase the number of all other complex parts). Increasing the number of components required for these compact compressors may increase the length required for the rotating shaft and / or increase the distance required between the rotating shaft bearings. In many cases, these requirements can result in larger and less compact compressors as compared to compact compressors with fewer compression stages. Further, in many cases, increasing the number of compression stages of a compact compressor does not provide the desired higher compression ratio, or even if the desired compression ratio is achieved, the compact compressor is efficient. It shows a decline, making such compact compressors commercially undesirable.

  Therefore, there is a need for an efficient compression system that can increase the compression ratio in a compact configuration that is economically and commercially feasible.

  Embodiments of the present disclosure may provide a supersonic compressor. The supersonic compressor may include a housing and an inlet coupled to or integral with the housing, the inlet defining an inlet passage configured to receive and flow process fluid. The supersonic compressor may also include a plurality of inlet guide vanes coupled to the housing and extending into the inlet passage. The supersonic compressor may further include a rotating shaft configured to be driven by the driving device, and a centrifugal impeller coupled to the rotating shaft. The centrifugal impeller includes a plurality of flow paths formed by the centrifugal impeller. And is fluidly connected to the inlet passage. The centrifugal impeller has a tip and energizes the process fluid received via the inlet passage, and at least partially radially through the plurality of channels with an absolute outlet Mach number of about 1 or more. It is configured to discharge process fluid from the tip. The supersonic compressor may also include a balance piston configured to balance the axial thrust generated by the centrifugal impeller. The supersonic compressor may further include a stationary diffuser disposed circumferentially around the tip of the centrifugal impeller. The fixed diffuser is partially bounded by a shroud wall and a hub wall that define an annular diffuser passage. The stationary diffuser may be configured to receive process fluid from a plurality of flow paths of the centrifugal impeller and convert the applied energy within the annular diffuser passage. The supersonic compressor may further include a collector fluidly coupled to the annular diffuser passage, wherein the collector is annular so that the supersonic compressor is configured to provide a compression ratio of at least about 8: 1. It is configured to collect the process fluid discharged through the diffuser passage.

  Embodiments of the present disclosure may further provide a compression system. The compression system is operably coupled to the drive device via a drive shaft, a drive device configured to provide rotational energy to the drive shaft, and a rotary shaft integrated with or coupled to the drive shaft. And a supersonic compressor. The supersonic compressor may include a compressor chassis and an inlet that defines an inlet passage configured to allow process fluid to flow therethrough. The process fluid may have a first velocity and a first pressure energy. The supersonic compressor includes a plurality of inlet guide vanes rotatably connected to the compressor chassis and extending into the inlet passage, and a plurality of flow paths connected to the rotating shaft and formed by a centrifugal impeller. And a centrifugal impeller that is fluidly coupled to the inlet passage. The centrifugal impeller may have a tip and increase the first velocity and first pressure energy of the process fluid received via the inlet passage, and increase the second velocity and second pressure energy. The process fluid may be configured to be at least partially discharged radially from the chip via the plurality of flow paths. The second velocity may be supersonic with an exit absolute Mach number of about 1 or greater. The supersonic compressor may include a fixed diffuser disposed circumferentially around the tip of the centrifugal impeller, the fixed diffuser defining an annular diffuser passage fluidly connected to the plurality of flow paths. The annular diffuser passage may be configured to receive the process fluid and reduce the second velocity of the process fluid to a third velocity and increase the second pressure energy to the third pressure energy. The third speed is subsonic. The supersonic compressor is configured to receive a process fluid fluidly coupled to and flowing from the annular diffuser passage such that the supersonic compressor is configured to provide a compression ratio of at least about 8: 1. A discharge volute may be included.

  Embodiments of the present disclosure may further provide a method for compressing a process fluid. The method may include driving the rotating shaft of the supersonic compressor via a drive device operably coupled to the supersonic compressor. The method also includes an inlet defined by the inlet of the supersonic compressor via at least one operable inlet guide vane pivotally connected to the housing of the supersonic compressor and extending into the inlet passage. Establishing fluid properties of the process fluid flowing through the passage may be included. This method uses a centrifugal mounted around a rotating shaft so that the process fluid flowing through the inlet passage of the supersonic compressor is drawn into the centrifugal impeller and discharged from the tip of the centrifugal impeller through a plurality of flow paths. A step of rotating the impeller may be included. The discharged process fluid may have a supersonic speed with an exit absolute Mach number of about 1.0 or greater. The method may also include flowing a discharge process fluid having supersonic speed through an annular diffuser passage defined by a stationary diffuser and fluidly connected to the plurality of flow paths. This increases the pressure energy of the released process fluid and compresses the released process fluid at a compression ratio of about 8: 1 or greater.

  The present disclosure will be best understood from the following detailed description when read with the accompanying drawing figures. It should be emphasized that the various features are not shown to scale in accordance with standard practice in the industry. Indeed, the dimensions of the various features may be arbitrarily increased or decreased for clarity of discussion.

FIG. 2 shows a schematic diagram of an exemplary compression system in accordance with one or more embodiments. 2 is a partial cross-sectional view of an exemplary compressor that may be included in the compression system of FIG. 1 in accordance with one or more disclosed embodiments. FIG. FIG. 3 is a perspective view of an exemplary impeller that may be included in the compressor of FIG. 2 according to one or more embodiments. FIG. 4 is a front view of a portion of the impeller of FIG. 3 and a portion of an exemplary vaneless fixed diffuser that may be included in the compressor of FIG. 2 according to one or more embodiments. FIG. 4 is a front view illustrating a portion of the impeller of FIG. 3 and a portion of an exemplary vaned stationary diffuser that may be included in the compressor of FIG. 2 in accordance with one or more embodiments. 6 is a flowchart illustrating an exemplary method for compressing a process fluid, according to one or more embodiments.

  It should be understood that the following disclosure describes several exemplary embodiments for implementing various features, structures, or functions of the present invention. To simplify the present disclosure, exemplary embodiments of components, arrangements, and configurations are described below; however, these exemplary embodiments are provided as examples only, and It is not intended to limit the scope. In addition, the present disclosure may repeat reference signs and / or text in various exemplary embodiments and throughout the drawings provided herein. These repetitions are for the sake of simplicity and clarity and do not prescribe the relationship between the various exemplary embodiments and / or configurations discussed in the various drawings. Furthermore, the formation of the first feature on the second feature in the following description may include an embodiment in which the first and second features are formed in direct contact with each other, and Embodiments may be included in which additional features are formed between the first and second features such that the first and second features are not in direct contact. Finally, the exemplary embodiments presented below may be combined in any combination of ways, i.e., any of the exemplary embodiments without departing from the scope of the disclosure herein. The element may be used in any other exemplary embodiment.

  In addition, specific terminology is used throughout the following description and claims to refer to specific components. As will be appreciated by those skilled in the art, the various components may refer to the same component with different names, and the naming conventions for the elements described herein are not expressly specified herein. In no way is it intended to limit the scope of the invention. Furthermore, the naming conventions used herein are not intended to distinguish between components that differ in name but not function. Further, in the following description and claims, the terms “including” and “comprising” are used in an unrestricted manner, so that “including, but not limited to” Should be taken to mean. All numerical values in this disclosure may be accurate or approximate unless stated otherwise. Accordingly, various embodiments of the disclosure may deviate from the numbers, numbers, and ranges disclosed herein without departing from the intended scope. Further, as used in the claims or specification, the term “or” is intended to encompass both exclusive and generic cases unless the context clearly dictates otherwise. That is, “A or B” is intended to be synonymous with “at least one of A and B”.

  FIG. 1 is a diagram illustrating a schematic diagram of an exemplary compression system 100 in accordance with one or more embodiments. The compression system 100 may include one or more compressors 102, one of which is shown, configured to compress the process fluid, among other components. In an exemplary embodiment, compression system 100 may have a compression ratio of at least about 6: 1 or higher. For example, the compression system 100 may process fluid at about 6: 1, about 6.1: 1, about 6.2: 1, about 6.3: 1, about 6.4: 1, about 6.5: 1, About 6.6: 1, about 6.7: 1, about 6.8: 1, about 6.9: 1, about 7: 1, about 7.1: 1, about 7.2: 1, about 7. 3: 1, about 7.4: 1, about 7.5: 1, about 7.6: 1, about 7.7: 1, about 7.8: 1, about 7.9: 1, about 8: 1 About 8.1: 1, about 8.2: 1, about 8.3: 1, about 8.4: 1, about 8.5: 1, about 8.6: 1, about 8.7: 1, About 8.8: 1, about 8.9: 1, about 9: 1, about 9.1: 1, about 9.2: 1, about 9.3: 1, about 9.4: 1, about 9. 5: 1, about 9.6: 1, about 9.7: 1, about 9.8: 1, about 9.9: 1, about 10: 1, about 10.1: 1, about 10.2: 1 About 10.3: 1, about 10.4: 1, about 10.5: 1, about 10.6: 1, about 10.7: 1, about 10.8: About 10.9: 1, about 11: 1, about 11.1: 1, about 11.2: 1, about 11.3: 1, about 11.4: 1, about 11.5: 1, about 11 .6: 1, about 11.7: 1, about 11.8: 1, about 11.9: 1, about 12: 1, about 12.1: 1, about 12.2: 1, about 12.3: 1, about 12.4: 1, about 12.5: 1, about 12.6: 1, about 12.7: 1, about 12.8: 1, about 12.9: 1, about 13: 1, about 13.1: 1, about 13.2: 1, about 13.3: 1, about 13.4: 1, about 13.5: 1, about 13.6: 1, about 13.7: 1, about 13 The compression may be at a compression ratio of .8: 1, about 13.9: 1, about 14: 1 or more.

  The compression system 100 may also include a drive device 104 operatively coupled to the compressor 102 via a drive shaft 106, among other components. The drive device 104 may be configured to provide rotational energy to the drive shaft 106. In the exemplary embodiment, the drive shaft 106 is integrated with or coupled to the rotation shaft 108 of the compressor 102 such that the rotational energy of the drive shaft 106 is imparted to the rotation shaft 108. Also good. The drive shaft 106 may be coupled to the rotary shaft 108 via a gear box (not shown) that includes a plurality of gears configured to transmit the rotational energy of the drive shaft 106 to the rotary shaft 108 of the compressor 102. So that the drive shaft 106 and the rotating shaft 108 can rotate at the same speed, substantially similar speeds, or different speeds and directions of rotation.

  The driving device 104 may be a motor, specifically an electric motor such as a permanent magnet motor, and may include a stator (not shown) and a rotor (not shown). Of course, other embodiments may use other types of electric motors including, but not limited to, synchronous motors, induction motors, and brushed DC motors. The driving device 104 may be a hydraulic motor, an internal combustion engine, a steam turbine, a gas turbine, or another device that can drive the rotating shaft 108 of the compressor 102 directly or via a power transmission system.

  In the exemplary embodiment, compressor 102 may be a direct suction centrifugal compressor. In other embodiments, the compressor 200 may be a back-to-back compressor. The direct suction centrifugal compressor may be, for example, a version of a dresser land pipeline direct suction (PDI) centrifugal compressor manufactured by Dresser-RandCompany of Olean, NY. The compressor 200 may have a center hang rotor structure or an overhang rotor structure, as shown in FIG. In the exemplary embodiment, compressor 102 may be an axial flow centrifugal compressor. In another embodiment, the compressor 102 may be a radial suction centrifugal compressor. As described above, the compression system 100 may include one or more compressors 102. For example, the compression system 100 may include a plurality of compressors (not shown). In another example shown in FIG. 1, the compression system 100 may include a single compressor 102. The compressor 102 may be a supersonic compressor or a subsonic compressor. In at least one embodiment, the compression system 100 may include a plurality of compressors (not shown), and at least one of the plurality of compressors is a subsonic compressor. In another embodiment shown in FIG. 1, the compression system 100 includes a single compressor 102, and the single compressor 102 is a supersonic compressor.

The compressor 102 may include a single stage (stage) or multiple stages (not shown). In at least one embodiment, the compressor 102 may be a single stage compressor. In another embodiment, the compressor 102 may be a multi-stage centrifugal compressor. Each stage (not shown) of the compressor 102 may be a subsonic compressor stage or a supersonic compressor stage. In the exemplary embodiment, compressor 102 may include a single supersonic compressor stage. In another embodiment, the compressor 102 may include multiple stage subsonic compressor stages. In yet another embodiment, the compressor 102 may include a subsonic compressor stage and a supersonic compressor stage. These stages of compressor 102 may have a compression ratio greater than about 1: 1. For example, the one or more stages of the compressor 102 may be about 1.1: 1, about 1.2: 1, about 1.3: 1, about 1.4: 1, about 1.5: 1, about 1. 6: 1, about 1.7: 1, about 1.8: 1, about 1.9: 1, about 2: 1, about 2.1: 1, about 2.2: 1, about 2.3: 1 About 2.4: 1, about 2.5: 1, about 2.6: 1, about 2.7: 1, about 2.8: 1, about 2.9: 1, about 3: 1, about 3 1: 1, about 3.2: 1, about 3.3: 1, about 3.4: 1, about 3.5: 1, about 3.6: 1, about 3.7: 1, about 3. 8: 1, about 3.9: 1, about 4: 1, about 4.1: 1, about 4.2: 1, about 4.3: 1, about 4.4: 1, about 4.5: 1 About 4.6: 1, about 4.7: 1, about 4.8: 1, about 4.9: 1, about 5: 1, about 5.1: 1, about 5.2: 1, about 5 .3: 1, about 5.4: 1, about 5.5: 1, about 5.6: 1, about 5.7: 1, about 5.8: 1, about 5.9: 1, about 6: 1, about 6. 1: 1, about 6.2: 1, about 6.3: 1, about 6.4: 1, about 6.5: 1, about 6.6: 1, about 6.7: 1, about 6.8 : 1, about 6.9: 1, about 7: 1, about 7.1: 1, about 7.2: 1, about 7.3: 1, about 7.4: 1, about 7.5: 1, About 7.6: 1, about 7.7: 1, about 7.8: 1, about 7.9: 1, about 8.0: 1, about 8.1: 1, about 8.2: 1, about 8.3: 1, about 8.4: 1, about 8.5: 1, about 8.6: 1, about 8.7: 1, about 8.8: 1, about 8.9: 1, about 9 : 1, about 9.1: 1, about 9.2: 1, about 9.3: 1, about 9.4: 1, about 9.5: 1, about 9.6: 1, about 9.7: 1, about 9.8: 1, about 9.9: 1, about 10: 1, about 10.1: 1, about 10.2: 1, about 10.3: 1, about 10.4: 1, about 10.5: 1, about 10.6: 1, about 10.7: 1, about 10.8: 1, about 10.9: 1, about 11: 1, about 11.1: 1, about 11.2. : About 11.3: 1, about 11.4: 1, about 11.5: 1, 11.6: 1, about 11.7: 1, about 11.8: 1, about 11.9: 1, about 12: 1, about 12.1: 1, about 12.2: 1, about 12.3: 1, about 12.4: 1, about 12.5: 1, about 12.6: 1, about 12.7 : 1, about 12.8: 1, about 12.9: 1, about 13: 1, about 13.1: 1, about 13.2: 1, about 13.3: 1, about 13.4: 1, Having a compression ratio of about 13.5: 1, about 13.6: 1, about 13.7: 1, about 13.8: 1, about 13.9: 1, about 14: 1 or more. Good. In an exemplary embodiment, compressor 102 may include a plurality of compressor stages, and a first stage (not shown) of the plurality of compressor stages has a compression ratio of about 1.75: 1. The second stage (not shown) of the plurality of compressor stages may be about 6.
It may have a compression ratio of 0: 1.

  FIG. 2 illustrates a cross-sectional view of an embodiment of a compressor 102 that may be included in the compression system 100 of FIG. As illustrated in FIG. 2, the compressor 102 includes a housing 110 that defines or includes an axial inlet 112 that defines an inlet passage 114, a fixed diffuser 116 fluidly coupled to the inlet passage 114, and a fixed diffuser 116. A fluid-coupled collector 117. Although shown as an axial inlet in FIG. 2, in one or more other embodiments, the inlet 112 may be a radial inlet. The drive device 104 is external to the housing 110 (shown in FIG. 1) such that the housing 110 can have a first or compressor end and a second end (not shown) or drive end. As shown) or inside the housing 110. The housing 110 may be configured to hermetically seal the drive device 104 and the compressor 102 therein, thereby supporting and protecting each component of the compression system 100. The housing 110 may also be configured to contain process fluid that flows through one or more portions or components of the compressor 102.

  The drive shaft 106 of the drive device 104 and the rotary shaft 108 of the compressor 102 may each be supported by one or more radial bearings 118 in an overhanging configuration as shown in FIG. The radial bearing 118 may be supported directly or indirectly by the housing 110 and subsequently supports the drive shaft 106 and the rotary shaft 108 that support the compressor 102 and drive device 104 during operation of the compression system 100. . In one embodiment, the radial bearing 118 may be a magnetic bearing such as an active magnetic bearing or a passive magnetic bearing. In other embodiments, other types of bearings (eg, oil film bearings) may be used. In addition, at least one axial thrust bearing 120 may be provided to manage the axial motion of the rotating shaft 108. In embodiments where the drive 104 and the compressor 102 are hermetically sealed within the housing 110, the thrust bearing 120 may be provided at the end of the rotating shaft 108 adjacent to the compressor end of the housing 110, Alternatively, it may be provided near such an end of the rotating shaft 108. The axial thrust bearing 120 may be a magnetic bearing and may be configured to bear the axial thrust generated by the compressor 102.

  As illustrated in FIG. 2, the axial inlet 112 that defines the inlet passage 114 of the compressor 102 adjusts the state of the process fluid flowing therethrough to provide predetermined desired fluid characteristics and / or fluid flow characteristics. One or more inlet guide vanes 122 of the inlet guide vane assembly configured to achieve may be included. Such fluid properties may include flow patterns (eg, vortex distribution), velocity, mass flow rate, pressure, temperature, and / or any suitable fluid that enables the compressor 102 to function as described herein. Characteristics and fluid flow properties may be included. The inlet guide vane 122 may be disposed in the inlet passage 114 and may be fixed or movable or adjustable. In the exemplary embodiment, the plurality of inlet guide vanes 122 may be arranged to face in a direction spaced about the circumferential inner surface 124 of the axial inlet 112. Each of the plurality of inlet guide vanes 122 extends into the inlet passage 114. The spacing of the inlet guide vanes 122 may be equally spaced, or may vary depending on predetermined process fluid characteristics and / or desired fluid flow attributes. With respect to shape, the inlet guide vane 122 may have an airfoil shape or streamline, or at least partially impart one or more fluid characteristics and / or fluid flow properties to the process fluid flowing through the inlet passage 114. Other shapes may be applied or may be configured as such.

  In one or more embodiments, the inlet guide vane 122 may be movably connected to the housing 110 and disposed in the inlet passage 114 as disclosed in US Pat. No. 8,632,302. This document is incorporated herein by reference to the extent that it is consistent with the disclosure of the present application. The inlet guide vane 122 may be further coupled to an annular inlet vane actuating member (not shown). During operation of the annular inlet vane actuating member, each of the inlet guide vanes 122 coupled to the annular inlet guide vane actuating member may pivot about a respective connection to the housing 110, thereby causing the compressor 102. It is possible to adjust the flow flowing into the components. The inlet guide vane 122 may be adjusted without disassembling the housing 110 to adjust the performance of the compressor 102 as set. By adjusting the compressor 102 without disassembling, the time and effort to optimize the compressor 102 for specific operating conditions can be eliminated. In addition, the impact of the impeller angle on the overall flow range and / or peak efficiency can be evaluated and optimized to improve performance, and the best inlet guide vane angle for a given application. A matrix of inlet guide vane angles may be generated in a relatively short cycle time for a conventional compressor so that the data can be analyzed to determine a combination.

  The compressor 102 may include a centrifugal impeller 126 configured to rotate about a central axis 128 within the housing 110. In the exemplary embodiment, centrifugal impeller 126 includes a hub 130 that is open or “not covered”. In another embodiment, the centrifugal impeller 126 may be an impeller covered with a shroud. The hub 130 may include a first meridian end 132, generally referred to as the eye of the centrifugal impeller 126, and a second meridian end 134 having a disk shape, and the second meridian end 134. Is generally referred to as the tip 136 of the centrifugal impeller 126. The disc-shaped second meridian end portion 134 may be tapered toward the inside with respect to the first meridian end portion 132 having an annular shape. The hub 130 may define a hole 138 configured to receive a connection member 140, such as a connection bolt, for connecting the centrifugal impeller 126 to the rotating shaft 108. In another embodiment, the hole 138 may be configured to receive a rotating shaft 108 that extends through the hole 138.

  As illustrated in FIG. 2, the compressor 102 may include a balance piston 142 configured to balance the axial thrust generated by the centrifugal impeller 126 during operation. In an exemplary embodiment, the balance piston 142 may be integrated with the centrifugal impeller 126 such that the balance piston 142 and the centrifugal impeller 126 are formed from a single piece or a single piece. In another embodiment, the balance piston 142 and the centrifugal impeller 126 may be separate components. For example, the balance piston 142 and the centrifugal impeller 126 may be separate annular components connected to each other. One or more seals, such as a labyrinth seal, can be implemented to isolate the balance piston 142 from external contaminants or lubricants.

  The centrifugal impeller 126 may be operably coupled to the rotating shaft 108. As such, the rotating shaft 108 rotates as it acts on the drive device 104 via the drive shaft 106 to cause rotation of the centrifugal impeller 126, whereby process fluid flowing into the inlet passage 114 is drawn into the centrifugal impeller 126. And accelerated at or around the tip 136 of the centrifugal impeller 126, resulting in an increase in the speed of the process fluid. In one or more embodiments, the process fluid at the tip 136 of the centrifugal impeller 126 may be subsonic and its absolute Mach number is less than one. For example, the process fluid at the tip 136 of the centrifugal impeller 126 may have an absolute outlet Mach number of less than 1, less than 0.9, less than 0.8, less than 0.7, less than 0.6, or less than 0.5. Good. Accordingly, in such an embodiment, the centrifugal impeller 126 is configured to rotate about the central axis 128 at a speed sufficient to provide process fluid at the tip 136 of the centrifugal impeller 126 having an outlet absolute Mach number of less than one. As may be obtained, the compressor 102 disclosed herein may be “subsonic”.

  In one or more embodiments, the process fluid at the tip 136 of the centrifugal impeller 126 may be supersonic and the exit absolute Mach number may be one or more. For example, the process fluid at the tip 136 of the centrifugal impeller 126 may have an absolute outlet Mach number of at least 1, at least 1.1, at least 1.2, at least 1.3, at least 1.4, or at least 1.5. Good. Thus, in such an embodiment, the centrifugal impeller 126 has a sufficient velocity to provide a process fluid at the tip 136 of the centrifugal impeller 126 having an outlet absolute Mach number greater than or equal to or greater than the speed of sound. The compressor 102 disclosed herein may be of “supersonic” so that it can be configured to rotate at. In a supersonic compressor or compression stage thereof, the rotational speed or tip speed of the centrifugal impeller 126 may be about 500 meters per second (m / s) or higher. For example, the tip speed of the centrifugal impeller 126 may be about 510 m / s, about 520 m / s, about 530 m / s, about 540 m / s, about 550 m / s, about 560 m / s or more.

  Referring now to FIGS. 3-5 following FIG. 2, FIG. 3 shows a perspective view of a centrifugal impeller 126 that may be included in the compressor 102 according to one or more embodiments. FIG. 4 illustrates a front view of a portion of the centrifugal impeller 126 of FIG. 3 and a portion of a stationary diffuser 116 that may be included in the compressor 102 of FIG. 2 according to one or more embodiments. FIG. 5 illustrates a portion of the centrifugal impeller 126 of FIG. 3 and another fixed diffuser included in the compressor 102 of FIG. 2 and used in place of the fixed supersonic diffuser 116, according to one or more embodiments. The front view with a part of 216 is shown.

  As shown in FIG. 2 and more clearly shown in FIGS. 3-5, the centrifugal impeller 126 includes a plurality of aerodynamic surfaces or blades 144a, b coupled to or integrally formed with the hub 130. The blades 144a, b may be configured to increase the speed and energy of the process fluid. As shown in FIGS. 3-5, the blades 144a, b of the centrifugal impeller 126 allow the process fluid to tangentially and tangentially through a plurality of channels 146,148 formed by the blades 144a, b. Radially urged to bend at least partially in the radial direction extending 360 degrees around the centrifugal impeller 126 from the blade tip of the centrifugal impeller 126 (cumulatively the tip 136 of the centrifugal impeller 126). It may be. Of course, the profile or amount of curvature of the blades 144a, b is not limited to the shape shown in FIGS. 3-5, and may be determined based at least in part on desired operating parameters.

  The plurality of blades 144a, b may include main blades 144a arranged at equal intervals around the central axis 128 in the circumferential direction. Each main blade 144 a extends from a leading edge 150 disposed adjacent to the first meridian end 132 of the centrifugal impeller 126 to a trailing edge 152 disposed adjacent to the second meridian end 134 of the centrifugal impeller 126. May extend up to. Further, based on the rotation of the centrifugal impeller 126, each main blade 144a may define a pressure surface on one side 154 of the main blade 144a and a suction surface on the side 156 opposite to the main blade 144a. As shown most clearly in FIG. 3, the centrifugal impeller 126 may include thirteen main blades 144a; still other embodiments including more than thirteen or less than thirteen main blades are used herein. May be considered. The number of main blades 144a may be determined based at least in part on desired operating parameters.

  The plurality of blades 144a, b are configured to reduce aerodynamic choking conditions that may occur in the compressor 102 depending on the number of blades 144a, b used for the centrifugal impeller 126. One or more splitter blades 144b may be included. The splitter blades 144b may be arranged at equal intervals around the central axis 128 in the circumferential direction. Each splitter blade 144b extends from a leading edge 158 spaced in the meridian direction downstream from the first meridian end 132 to a trailing edge 160 disposed adjacent to the second meridian end 134 of the centrifugal impeller 126. May be present. The front edge 158 of each splitter blade 144b is disposed outward from the front edge 150 of the main blade 144a in the meridian direction, and the front edge 150 of the main blade 144a and the front edge 158 of the splitter blade 144b are on the same plane. Alternatingly arranged so that there is no. Further, based on the rotation of the centrifugal impeller 126, each splitter blade 144b may define a pressure surface on one side 162 of the splitter blade 144b and a suction surface on the opposite side 164 of the splitter blade 144b.

  As most clearly shown in FIGS. 2 and 3, each of the main blade 144a and the splitter blade 144b is in the meridian direction from the second meridian end 134 of the centrifugal impeller 126 toward its first meridian end 132. Extend to. The configuration in the meridian direction of each of the main blade 144a and the splitter blade 144b may be substantially similar to the trailing edge 152 of the main blade 144a and the trailing edge 160 of the splitter blade 144b. The configuration in the meridian direction of each of the main blade 144a and the splitter blade 144b may be different from the second meridian end portion 134 with respect to the trailing edge 152 of the main blade 144a and the trailing edge 160 of the splitter blade 144b. . In the exemplary embodiment, the extension in the meridian direction of each of the main blades 144a may be greater than the extension in the meridian direction of the splitter blade 144b, and each leading edge 158 of the splitter blade 144b is in each of the main blades 144a. The leading edge 150 may be offset from the leading edge 150 toward the second meridian end portion 134 of the centrifugal impeller 126 in the meridian direction of the main blade 144b.

  The splitter blade 144b and the main blade 144a may be arranged circumferentially around the central axis 128 in a pattern in which the splitter blade 144b is arranged between the main blade 144a and the adjacent main blade 144a. . Each splitter blade 144b may be disposed between the pressure surface side 154 of the adjacent main blade 144a and the suction surface side 156 of the other adjacent main blade 144a. Furthermore, the splitter blades 144b are arranged such that each splitter blade 144b is not circumferentially displaced or equidistant from the respective adjacent main blades 144a and thus is not disposed in the center in the circumferential direction between the adjacent main blades 144a. "Clocked" to the main blade 144a. For example, the operating characteristics of the centrifugal impeller 126 can be improved by clocking the splitter blade 144b by moving the splitter blade 144b from a position equidistant from the adjacent main blade 144a.

  In one or more embodiments, the splitter blade 144b and the main blade 144a may be arranged circumferentially around the central axis 128 in a pattern in which a plurality of splitter blades 144b may be arranged between adjacent main blades 144a. Good. Thus, in one embodiment, at least two splitter blades 144b are disposed between adjacent main blades 144a. The leading edges 158 of the respective splitter blades 144b may be offset from each other in the meridian direction such that the respective leading edges 158 of the splitter blades 144b are arranged alternately so that they are not coplanar.

  When placed between adjacent main blades 144a, each splitter blade 144b may be oriented such that the splitter blade 144b is tilted so that the leading edge 158 of the splitter blade 144b is behind the splitter blade 144b. It is shifted in the circumferential direction from a position equidistant from the adjacent main blade 144a by a different amount from the edge 160. Thus, in the exemplary embodiment, the leading edge 158 of the splitter blade 144b is equidistant from the adjacent main blade 144a by a first percentage distance that is half the angular distance θ between the adjacent main blades 144a. It may be displaced from the position. The trailing edge 160 of the splitter blade 144b may be displaced from a position equidistant from the adjacent main blade 144a by a distance of a second percentage amount that is half the angular distance θ between the adjacent main blades 144a.

  In one or more embodiments, the splitter blade 144b and the main blade 144a may be arranged circumferentially around the central axis 128 in a pattern in which a plurality of splitter blades 144b may be arranged between adjacent main blades 144a. Good. Thus, in one embodiment, at least two splitter blades 144b are disposed between adjacent main blades 144a. The leading edges 158 of the respective splitter blades 144b may be offset from each other in the meridian direction such that the respective leading edges 158 of the splitter blades 144b alternate so that they are not coplanar.

  When placed between adjacent main blades 144a, each splitter blade 144b may be oriented such that the splitter blade 144b is tilted so that the leading edge 158 of the splitter blade 144b is behind the splitter blade 144b. It is shifted in the circumferential direction from a position equidistant from the adjacent main blade 144a in a proportion different from the edge 160. Thus, in the exemplary embodiment, the leading edge 158 of the splitter blade 144b is from a position equidistant from the adjacent main blade 144a by a first percentage amount that is half the angular distance θ between the adjacent main blades 144a. It may be shifted. The trailing edge 160 of the splitter blade 144b may be displaced from a position equidistant from the adjacent main blade 144a by a distance of a second percentage amount that is half the angular distance θ between the adjacent main blades 144a.

  In an exemplary embodiment, the first percentage amount may be greater than the second percentage amount. In another embodiment, the first percentage amount may be less than the second percentage amount. For example, the difference in displacement between the leading edge 158 and the trailing edge 160 from a position equidistant from the adjacent main blade 144a is about 1%, about 2%, about 3%, about 4%, about 5% percent. About 10 percent, about 15 percent, about 20 percent or more. In another example, the difference in displacement between the leading edge 158 and the trailing edge 160 from a position equidistant from the adjacent main blade 144a is about 1% to about 2%, about 3% to about 5%, It may be from about 5% to about 10%, or from about 10% to about 20%. The difference in distance for a percentage amount, such as the amount by which the splitter blade 144b is tilted, may be determined based at least in part on the desired operating parameter.

  As illustrated in FIGS. 3 to 5, a plurality of flow paths 146 and 148 disposed around the central axis 128 may be formed between the splitter blade 144 b and the adjacent main blade 144 a. In the exemplary embodiment, the plurality of flow paths 146, 148 are formed between the pressure surface side 162 of the splitter blade 144b and the suction surface side 156 of one of the adjacent main blades 144a. A second flow path 148 formed between the first flow path 146 and the suction face side 164 of the splitter blade 144b and the pressure face side 154 of the other main blade 144a of the adjacent main blade 144a. May be included. The mass flow rate of the process fluid through the first and second flow paths 146, 148 may be determined based on the displacement of the splitter blade 144b relative to the adjacent main blade 144b. For example, it is specified that equal mass flow rates through the first flow path 146 and the second flow path 148 may not be obtained by arranging the splitter blades 144b at equal intervals between adjacent main blades 144a. ing. Thus, in the exemplary embodiment, splitter blade 144b may be circumferentially offset from a position in the middle of adjacent main blade 144a, such that suction surface side 164 of splitter blade 144b is adjacent. The main blade 144a is disposed in a direction closer to the pressure side surface 154 of one main blade 144a and away from the suction surface side 156 of the other main blade 144a of the adjacent main blade 144a, thereby each flow path 146, Mass flow through 148 is substantially equalized.

  As will be appreciated by those skilled in the art, the desired displacement of the splitter blade 144b can vary, such as the shape of the blades 144a, b, the angle of incidence of the blades 144a, b, the size of the blades 144a, 144b, the size of the centrifugal impeller 126, etc. It may depend on factors. Note that the displacement required to equalize the mass flow rate through the first flow path 146 and the second flow path 148 is determined by measuring the mass flow rate using a mass flow meter, and the centrifugal impeller 126 and corresponding blades. 144a, b may be determined for a given design.

  As illustrated in FIG. 2, the compressor 102 may include a shroud 170 coupled to the housing 110 and disposed adjacent to the plurality of blades 144 a, b of the centrifugal impeller 126. In particular, the surface 172 of the shroud 170 may include an abradable material (abrasive material) and may have a contour that is substantially aligned with the silhouette of the plurality of blades 144a, b, thereby Leakage of process fluid in the gap defined therebetween is substantially reduced. The abradable material is disposed on the surface 172 of the shroud 170 and deforms during the axial movement of the rotating shaft 108 while the rotating centrifugal impeller 126 accidentally contacts the abradable material of the stationary shroud 170. And / or configured to be removed from the shroud 170, thereby preventing damage to the blades 144a, b and reducing the amount of sacrificial abradable material.

  With continued reference to FIG. 2, in the embodiment most clearly shown in FIG. 4, the compressor 102 may include a fixed diffuser 116 fluidly connected to the axial inlet 112, and the fixed diffuser 106 may be It is configured to receive radial process fluid that has exited from the tip 136 of the impeller 126. In the exemplary embodiment, stationary diffuser 116 may be a vaneless diffuser. The stationary diffuser 116 may be configured to convert the kinetic energy of the process fluid from the centrifugal impeller 126 to an increased static pressure. In the exemplary embodiment, stationary diffuser 116 may be disposed downstream of centrifugal impeller 126 and may be disposed in a circumferentially fixed manner around the outer periphery or tip 136 of centrifugal impeller 126.

  The fixed diffuser 116 may be connected to or integral with the housing 110 of the compressor 102 and has an annular end having an inlet end 176 adjacent to the tip 136 of the centrifugal impeller 126 and a radially outer outlet end 178. A diffuser passage 174 may be formed. In the exemplary embodiment, the annular diffuser passage 174 may be formed at least in part by a portion of the housing 110 that forms the boundary sidewalls of the fixed diffuser 116, ie, the shroud wall 180 and the hub wall 182. The shroud wall 180 and the hub wall 182 may each be a straight wall or a undulating wall, and the annular diffuser passage 174 may be formed from a straight wall or a undulating wall or combination thereof. In addition, the annular diffuser passage 174 may have a width that decreases as the shroud wall 180 and the hub wall 182 extend radially outward. Such a “pinch-shaped” diffuser may provide lower choke and surge limits, thereby improving the efficiency of the centrifugal impeller 126.

  With continued reference to FIG. 2, in another embodiment shown most clearly in FIG. 5, a fixed diffuser 216 may be utilized in the compressor 102 instead of the fixed diffuser 116 described above. . The fixed diffuser 216 shown in FIG. 5 may be similar in some respects to the fixed diffuser 116 described above, so that the fixed diffuser 216 will be best understood with reference to the description of FIGS. . Similar reference numbers may indicate similar components and details thereof will not be described again. The stationary diffuser 216 may be configured to receive a radial process fluid flow that is fluidly coupled to the axial inlet 112 and that is discharged from the centrifugal impeller 126.

  The stationary diffuser 216 may be configured to convert the kinetic energy of the process fluid from the centrifugal impeller 126 to increased static pressure. In the exemplary embodiment, the stationary diffuser 216 may be disposed downstream of the centrifugal impeller 126 and may be disposed in a circumferentially fixed manner around the outer periphery or tip 136 of the centrifugal impeller 126. The fixed diffuser 216 may be coupled to or integral with the housing 110 of the compressor 102 and may further include an inlet end 176 adjacent the tip 136 of the centrifugal impeller 126 and a radially outer outlet. An annular diffuser passage 174 having an end 178 may be formed. In the exemplary embodiment, annular diffuser passage 174 may be at least partially formed by shroud wall 180 and hub wall 182 of housing 110.

  In the exemplary embodiment, stationary diffuser 216 may be an impeller diffuser, such as a wedge diffuser, or an impeller diffuser (see FIG. 5). Fixed diffuser 216 may include a plurality of diffuser vanes 184 and 186 disposed within a plurality of concentric rings 188 and 190 about central axis 128. The plurality of diffuser vanes 184, 186 extend from the shroud wall 180 or hub wall 182 of the fixed diffuser 216, or from both the shroud wall 180 and the shroud wall 180. As shown in FIG. 5, a plurality of diffuser vanes 184, 186 are disposed in the first ring 188 about the central axis 128 and extend from the hub wall 182 of the fixed diffuser 216. 184 may be included. The first row vanes 184 each include a leading edge 192 disposed proximate to the inlet end 176 and a trailing edge 194 that is radially and circumferentially offset from the leading edge 192. The first row vane 184 may be a low stiffness diffuser vane in which the code to pitch ratio of the first row vane 184 is less than one. As provided herein, a diffuser vane having a chord to pitch ratio of less than 1 is referred to as a low stiffness diffuser vane. In the illustrated embodiment of FIG. 5, the first ring 188 includes 17 low stiffness diffuser vanes; still herein, embodiments that include more than 17 or less than 17 low stiffness diffuser vanes. May be considered. Each of the first row vanes 184 may be an airfoil or may have a shape substantially similar thereto.

  As illustrated in FIG. 5, a plurality of diffuser vanes 184, 186 are disposed in the second ring 190 about the central axis 128 and extend from the hub wall 182 of the fixed diffuser 216. 186 may be included. The plurality of diffuser vanes 184, 186 are arranged vertically such that the second ring 190 of the second row vane 186 is arranged radially outward from the first ring 188 of the first row vane 184. The second row vane 186 includes individual leading edges 196 disposed proximate to the trailing edge 194 of the first row vane 184 and individual trailing edges 198 that are radially and circumferentially offset from the leading edge 196. Including. The second row vane 186 may have greater rigidity than the first row vane 184. The chord to pitch ratio of the second row vane 186 is substantially greater than the chord to pitch ratio of the first row of vanes 184. In the exemplary embodiment, the cord-to-pitch ratio of the second row vane 186 is 1 or greater. As provided herein, a diffuser vane having a chord to pitch ratio of one or more is referred to as a high stiffness diffuser vane. In the illustrated embodiment of FIG. 5, the second ring 190 includes a plurality of first row vanes 184, more specifically, twice the number of first row vanes 184. Thus, in an embodiment where the first ring 188 includes 17 first row vanes 184, the second ring 190 may include 34 diffuser vanes; still herein, 34 or more or Embodiments including less than 34 diffuser vanes are also contemplated. Each of the second row vanes 186 may be an airfoil or may have a substantially similar shape.

  In the exemplary embodiment, the first row vane 184 of the first ring 188 may be located near the tip 136 of the centrifugal impeller 126 and through the space 200 without the inner vane 126 of the centrifugal impeller 126. It may be spaced from the tip 136. Accordingly, the inner vane-free space 200 may be provided between the centrifugal impeller tip radius 202 and the leading edge radius 204 of the first ring 188. In the exemplary embodiment, the inner vane-free space 200 may be formed from a leading edge radius 204 that is about 5 to about 10% greater than the centrifugal impeller tip radius 202. In another embodiment, the inner vane-free space 200 may be formed from a leading edge radius 204 that is about 6 to about 8 percent greater than the centrifugal impeller tip radius 202. Similarly, the outer impeller is between the radius 208 formed by the trailing edge 194 of the first row vane 184 of the first ring 188 and the radius 210 of the leading edge 196 of the second row vane 186 of the second ring 188. A space 206 without a gap can be provided. In the exemplary embodiment, the outer impellerless space 206 may be formed from the leading edge radius 210 of the second ring 190 that is about 5 to about 10 percent larger than the trailing edge radius 208 of the first ring 188. Good. In another embodiment, the outer impellerless space 206 may be formed from the leading edge radius 210 of the second ring 190 that is about 6 to about 8 percent larger than the trailing edge radius 208 of the first ring 188. .

  In the exemplary embodiment, the incidence of the first row vane 184 of the first ring 188 causes a supersonic flow introduced to the inlet end 176 of the fixed diffuser 216 to control the absolute outlet Mach number and It may be determined to reduce to subsonic flow at the trailing edge 194 of one ring 188. As configured, the shock wave generated by the leading edge 192 of the first ring 188 does not propagate to the second row vane 186; however, the leading edge 192 of the first ring 188 has a pressure of the centrifugal impeller 126. To provide a communication path from the downstream portion of the stationary diffuser 216 to the upstream portion of the centrifugal impeller 126, thereby providing a wider range. Incidence of the second row vane 186 of the second ring 190 may be determined by placing the second ring 190 in a “shadow” or flow path of the first ring 188. Accordingly, the second row vanes 186 may be configured such that two second row vanes 186 are provided after each first row vane 184 and change the direction of process fluid flow.

  In another embodiment, the fixed diffuser 216 is disposed within a third ring (not shown) about the central axis 128 and radially outward of the first ring 188 and the second ring 190. A third row vane 188 may also be included, and the first ring, the second ring 190 and the third ring are concentric. The third row vane may have a cord to pitch ratio that is less than the cord to pitch ratio of the second row vane 186 of the second ring 190. In another embodiment, the third row vane may have a cord to pitch ratio that is substantially equal to the cord to pitch ratio of the first row vane 184 of the first ring 188. The third row vanes may be configured to further swirl the process fluid flow.

  As described above, in one or more embodiments, the centrifugal impeller 126 is designed to rotate around the central axis 128 at high speed, and the moving process fluid entering the inlet end 176 of the stationary diffuser 116 is compressed process fluid. The compressor 102 provided herein may be referred to as being “supersonic” because it is said to have a fluid velocity that exceeds the speed of sound. Thus, in an exemplary embodiment, the moving process fluid entering the inlet end 176 of the stationary diffuser 116 may have an outlet absolute Mach number of about 1 or greater. Still, to increase the total energy of the fluid system, the moving process fluid entering the inlet end 176 of the stationary diffuser 116 is at least about 1.1, at least about 1.2, at least about 1.3, at least about 1.4. Or an absolute absolute Mach number of at least about 1.5. In another example, the process fluid at the tip 136 of the centrifugal impeller 126 may have an absolute outlet Mach number of about 1.1 to about 1.5, or about 1.2 to about 1.4.

  The flow of process fluid discharged from the outlet end 178 of the stationary diffusers 116, 216 may enter the collector 117 as best shown in FIG. Collector 117 may be configured to collect process fluid flow from stationary diffusers 116, 216 and to route process fluid flow to downstream pipes and / or process components (not shown). . In the exemplary embodiment, collector 117 may be a discharge volute, or specifically a scroll-type discharge volute. In another embodiment, the collector 115 may be a plenum. The collector 117 may be further configured to increase the static pressure of the process fluid flow by converting the kinetic energy of the process fluid to static pressure. The collector 117 may have a round tongue (not shown). In another embodiment, the collector may have a sharp tongue (not shown). Of course, the tongue of the collector 117 may form other shapes known to those skilled in the art without departing from the scope of the present disclosure.

  With continued reference to FIGS. 1-5, one or more exemplary operating aspects of the exemplary compression system 100 will be described. Process fluid may be provided to the compression system 100 from an external source (not shown) having a low pressure environment. The compression system 100 may include a compressor 102 having a centrifugal impeller 126 coupled to a rotating shaft 108 and a stationary diffuser 116 disposed circumferentially around the rotating centrifugal impeller 126, among other components. Good. In another embodiment, the compression system 100 may include a compressor 102 having a centrifugal impeller 126 coupled to the rotating shaft 108 and a stationary diffuser 216 disposed circumferentially around the rotating centrifugal impeller 126. .

  The process fluid may be drawn into the axial inlet 112 of the compressor 102, for example, at a speed in the range of about Mach 0.05 to about Mach 0.40. Process fluid may flow through an inlet passageway 114 defined by an axial inlet 112 and across an inlet guide vane 122 that extends into the inlet passageway 114. The process fluid flowing across the inlet guide vane 122 may be provided at an increased speed and imparted with at least one fluid characteristic (eg, vortex) before being drawn into the rotating centrifugal impeller 126. The inlet guide vane 122 may be adjusted to change one or more fluid properties imparted to the process fluid.

  Process fluid may be drawn into the rotating centrifugal impeller 126 and may contact the curved centrifugal impeller blades 144a, b. Thereby, the process fluid may be accelerated tangentially and radially by centrifugal force, and at least partially in the radial direction spreading 360 degrees around the rotating centrifugal impeller 126 (cumulatively, the blade tip of the centrifugal impeller 126 The fluid may be discharged from the flow paths 146 and 148 via the tip 136) of the centrifugal impeller 126. In some embodiments, the velocity of the process fluid discharged from the blade tip (cumulatively the tip 136 of the centrifugal impeller 126) is supersonic and at least about 1, at least about 1.1, at least about 1.. The rotating centrifugal impeller 126 increases the speed and static pressure of the process fluid so that it may have an outlet absolute Mach number of 2, at least about 1.3, at least about 1.4, or at least about 1.5.

  In one embodiment, the stationary diffuser 116 may be circumferentially disposed around the outer periphery or tip 136 of the centrifugal impeller 126 and may be coupled to or integrated with the housing 110 of the compressor 102. . In another embodiment, the stationary diffuser 216 may be circumferentially disposed around the outer periphery or tip 136 of the centrifugal impeller 126 and connected to or integrated with the housing 110 of the compressor 102. Good. The radial process fluid flow discharged from the rotating centrifugal impeller 126 is a process in which the velocity of the process fluid flow discharged from the tip 136 of the rotating centrifugal impeller 126 enters the inlet end 176 of the stationary diffuser 116, 216. It may be received by stationary diffusers 116, 216 so as to be substantially similar to the velocity of the fluid. Thus, the process fluid may enter the inlet end 176 of the fixed diffuser 116, 216 at supersonic speed, for example having at least one exit absolute Mach number, and may correspondingly be referred to as supersonic process fluid. .

  The speed of the supersonic process fluid flowing into the inlet end 176 of the fixed diffuser 116, 216 is such that the process fluid is radially outward from the fixed diffuser 116, 216 from the inlet end 176 so that the velocity head is converted to static pressure. As it flows toward the outlet end 178, the radius of the annular diffuser passage 174 increases and decreases. In at least one embodiment that includes a fixed diffuser 216, the tangential velocity of the supersonic process fluid may be decelerated from supersonic to subsonic across the first row vane 184 without shock loss. Fixed diffusers 116, 216 may decrease the speed of the process fluid and increase the pressure energy.

  The process fluid exiting the stationary diffusers 116, 216 may have subsonic speed and may be fed to the collector 117 or discharge volute. Collector 117 may increase the static pressure of the process fluid by converting the remaining kinetic energy of the process fluid to static pressure. Subsequently, the process fluid may be routed in a specific path to perform work or for operation of one or more downstream processes or components (not shown).

The process fluid that is pressurized, circulated, contained, or otherwise utilized in the compression system 100 may be a fluid in the liquid phase, gas phase, supercritical state, subcritical state, or a combination thereof. Good. The process fluid may be a mixture or a process fluid mixture. The process fluid may include one or more high molecular weight process fluids, one or more low molecular weight process fluids, or any mixture or combination thereof. As used herein, the term “high molecular weight process fluid” means a process fluid having a molecular weight of about 30 grams / mole (g / mol) or greater. Exemplary high molecular weight process fluids may include, but are not limited to, hydrocarbons such as ethane, propane, butane, pentane and hexane. Exemplary high molecular weight process fluids may include, but are not limited to, carbon dioxide (CO ₂ ) or a process fluid mixture containing carbon dioxide. As used herein, the term “low molecular weight process fluid” means a process fluid having a molecular weight of less than about 30 g / mol. Exemplary low molecular weight process fluids may include, but are not limited to, air, hydrogen, methane, or combinations or mixtures thereof.

  In an exemplary embodiment, the process fluid or process fluid mixture may be carbon dioxide or may include carbon dioxide. The amount of carbon dioxide in the process fluid or process fluid mixture is at least about 80%, at least about 85%, at least about 90%, at least about 95%, at least about 96%, at least about 97%, at least about 98 by volume. %, At least about 99%, or more. By utilizing carbon dioxide as a process fluid or as a component or part of a process fluid mixture in the compression system 100, one or more advantages can be provided. For example, the high density and high heat capacity or volumetric heat capacity of carbon dioxide relative to other process fluids can make carbon dioxide more “energy dense”. Thus, the relative size of the compression system 100 and / or its components can be reduced without reducing the performance of the compression system 100.

  The carbon dioxide may be of a particular type, source, purity, or grade. For example, industrial grade carbon dioxide may be utilized as a process fluid without departing from the scope of the disclosure herein. Further, as described above, the process fluid may be a mixture or a process fluid mixture. The process fluid mixture may be selected with respect to one or more desired properties of the process fluid mixture within the compression system 100. For example, the process fluid mixture may be a liquid absorbent and carbon dioxide (which can compress the process fluid mixture to a relatively high pressure using less energy input than compressing carbon dioxide (or a process fluid containing carbon dioxide) alone. Or a mixture of process fluids containing carbon dioxide).

  FIG. 6 is a flowchart illustrating an example method 300 for compressing a process fluid in accordance with one or more embodiments. The method 300 may include, in step 302, driving the rotating shaft of the supersonic compressor via a drive operably coupled with the supersonic compressor. The drive shaft may be driven by a drive device such as an electric motor.

  The method 300 also includes an inlet passage defined by the inlet of the supersonic compressor via at least one movable inlet guide vane pivotally connected to the housing of the supersonic compressor and extending into the inlet passage. Establishing a fluid property of the process fluid flowing therethrough may be included. The process fluid includes carbon dioxide at step 304. The method may also include adjusting at least one movable inlet guide vane to establish a fluid characteristic of the process fluid, where the fluid characteristic includes a flow pattern, a first velocity, a mass flow rate, a pressure Or temperature.

  In step 306, the method 300 is mounted around a rotating shaft such that process fluid flowing through the inlet passage of the supersonic compressor is drawn into the centrifugal impeller and released from the tip of the centrifugal impeller through a plurality of channels. A rotating centrifugal impeller provided may be included. The discharged process fluid has a supersonic speed with an exit absolute Mach number of about 1 or greater. The method 300 also includes, in step 308, the emitted process fluid having supersonic speed is defined by a stationary diffuser and fluidly coupled to the plurality of flow paths so that the pressure energy of the emitted process fluid is increased. A step of flowing through the annular diffuser passage may be included. Thereby, the discharged process fluid can be compressed at a compression ratio of about 8: 1 or more.

  The stationary diffuser may be a vaneless diffuser partially surrounded by a shroud wall and a hub wall that defines an annular diffuser passage between the shroud wall and the hub wall. The shroud wall defining the annular diffuser passage may be a straight wall, a relief wall, or a combination thereof, and the hub wall defining the annular diffuser passage is a straight wall, a relief wall, Alternatively, a combination thereof may be used. In another embodiment, the stationary diffuser may be a vaned diffuser partially surrounded by a shroud wall and a hub wall defining an annular diffuser passage between the shroud wall and the hub wall. The attached diffuser may include a plurality of low stiffness diffuser vanes extending into the annular diffuser passage from either or both of the shroud wall and the hub wall.

  It should be understood that all numbers and ranges disclosed herein are approximate numbers and ranges, regardless of whether “about” is used together. The term “about” as used herein, in conjunction with a number, is a value that is +/− 5% (inclusive), +/− 10% (inclusive) of the number. Or a (inclusive) value that is +/− 15% of the number. If a numerical range is disclosed herein, it should be further understood that any numerical value within that range is also specifically disclosed.

  Certain embodiments and features have been described using a set of numerical upper limits and a set of numerical lower limits. Any two value combinations, such as any lower and higher value combinations, any two lower value combinations, and / or any two higher value combinations are not otherwise indicated. It should be understood that it is considered as far as possible.

  The foregoing has outlined rather broadly the features of several embodiments so that those skilled in the art may better understand the present disclosure. One of ordinary skill in the art can use the present disclosure as a basis for designing or modifying other processes and structures to perform the embodiments introduced herein for the same purpose and / or achieve the same advantages. It should be understood that can be easily used. Those skilled in the art should realize such equivalent configurations without departing from the spirit and scope of the present disclosure, and that various changes, substitutions and modifications can be made without departing from the spirit and scope of the present disclosure. Should be understood.

DESCRIPTION OF SYMBOLS 100 Compression system 102 Compressor 104 Drive device 106 Drive shaft 108 Rotating shaft 110 Housing 112 Axial inlet 112 Inlet 114 Inlet passage 115 Collector 116 Fixed diffuser 117 Collector 118 Radial bearing 120 Thrust bearing 122 Inlet guide vane 124 Circumferential inner surface 126 Centrifugal impeller 128 Central axis 130 Hub 132 First meridian end portion 134 Second meridian end portion 136 Tip 138 hole 140 Connecting member 142 Balance piston 144a Main blade 144b Splitter blade 146, 148 Flow path 170 Shroud 174 Annular diffuser passage 176 Inlet end 178 Outlet end 180 Shroud wall 182 Hub wall

Claims (20)

A supersonic compressor,
A housing;
An inlet coupled to or integral with the housing, the inlet defining an inlet passage, the inlet passage configured to receive and flow process fluid therethrough;
A plurality of inlet guide vanes coupled to the housing and extending into the inlet passage;
A rotating shaft configured to be driven by a drive device;
A centrifugal impeller coupled to the rotating shaft, wherein the centrifugal impeller is fluidly coupled to the inlet passage through a plurality of flow paths formed by the centrifugal impeller, and the centrifugal impeller has a tip. And energizing the process fluid received via the inlet passage and at least partially radially through the plurality of channels from the tip with an absolute Mach number of about 1 or more. A centrifugal impeller configured to discharge process fluid;
A balance piston configured to balance the axial thrust generated by the centrifugal impeller;
A stationary diffuser disposed circumferentially around the tip of the centrifugal impeller, the stationary diffuser being partially bounded by a shroud wall and a hub wall defining an annular diffuser passage therebetween; The fixed diffuser is defined and configured to receive process fluid from the plurality of flow paths of the centrifugal impeller and to convert applied energy within the annular diffuser passage. When,
A collector fluidly connected to the annular diffuser passage and configured to collect process fluid discharged from the annular diffuser passage;
With
The supersonic compressor is configured to provide a compression ratio of at least about 8: 1. The plurality of inlet guide vanes are rotatably connected to the housing,
The balance piston is integral with the centrifugal impeller;
The supersonic compressor according to claim 1, wherein the collector is a discharge volute configured to discharge process fluid to a downstream processing component.   The plurality of inlet guide vanes condition process fluid flowing therethrough to provide one or more predetermined fluid properties selected from the group consisting of flow pattern, velocity, mass flow rate, pressure, and temperature. The supersonic compressor according to claim 2, which is configured as described above. The supersonic compressor is configured to provide a compression ratio of at least about 10: 1;
The process fluid contains carbon dioxide,
The centrifugal impeller is configured to discharge process fluid from the tip at an outlet absolute Mach number of about 1.3 or greater, at least partially in the radial direction, through the plurality of flow paths,
The supersonic compressor according to claim 1, wherein the centrifugal impeller is further configured to rotate through the rotating shaft at a rotational speed of about 500 meters per second or more.   The supersonic compressor of claim 1, wherein the stationary diffuser is a vaneless diffuser configured to discharge process fluid flowing therethrough at subsonic speeds. The centrifugal impeller includes a hub and a plurality of blades extending therefrom and forming the plurality of flow paths,
Each of the plurality of blades includes a leading edge, and at least one leading edge of the plurality of blades is spaced from the at least one other leading edge of the plurality of blades in a meridian direction. The supersonic compressor according to claim 1, wherein the compressor is a supersonic compressor.   The supersonic compressor according to claim 1, further comprising a shroud having an abradable material disposed adjacent to a plurality of blades extending from the hub of the centrifugal impeller.   The supersonic compressor according to claim 1, wherein the process fluid contains carbon dioxide.   The supersonic compressor of claim 8, wherein the process fluid comprises about 90% carbon dioxide.   The supersonic compressor according to claim 1, wherein the centrifugal impeller is an impeller having an open surface. A compression system,
A drive device comprising a drive shaft, wherein the drive device is configured to provide rotational energy to the drive shaft; and
A supersonic compressor that is integrated with the drive shaft or operatively connected to the drive device via a rotating shaft connected to the drive shaft, the supersonic compressor comprising:
A compressor chassis,
An inlet defining an inlet passage, the inlet passage configured to flow process fluid therethrough, the process fluid having a first velocity and a first pressure energy;
A plurality of inlet guide vanes pivotably connected to the compressor chassis and extending into the inlet passage;
A centrifugal impeller coupled to the rotating shaft, wherein the centrifugal impeller is fluidly coupled to the inlet passage through a plurality of flow paths formed by the centrifugal impeller, and the centrifugal impeller has a tip. And a process fluid having a second velocity and a second pressure energy to increase the first velocity and the first pressure energy of the process fluid received via the inlet passage. A centrifugal impeller configured to discharge at least partially in the radial direction from the tip through the plurality of channels, wherein the second velocity is a supersonic velocity having an outlet absolute Mach number of about 1 or more When,
A stationary diffuser that is circumferentially disposed about the tip of the centrifugal impeller and defines an annular diffuser passage fluidly connected to the plurality of flow paths, the annular diffuser passage receiving a process fluid; And configured to reduce a second speed of the process fluid to a third speed and to increase the second pressure energy to a third pressure energy, the third speed being subsonic. A fixed diffuser,
A discharge volute fluidly connected to the annular diffuser passage and configured to receive a process fluid flowing therefrom;
With
The supersonic compressor is configured to provide a compression ratio of at least about 8: 1. The supersonic compressor is
A shroud having an abradable material disposed adjacent to a plurality of blades extending from a hub of the centrifugal impeller and forming the plurality of flow paths fluidly connected to the annular diffuser passage and the inlet passage;
A balance piston integrated with the centrifugal impeller and configured to balance axial thrust generated by the centrifugal impeller;
Further comprising
The supersonic compressor is configured to provide a compression ratio of at least about 10: 1;
The process fluid contains carbon dioxide,
The compression system of claim 11, wherein the second speed has an exit absolute Mach number of about 1.3 or greater.   12. The compression system of claim 11, wherein the stationary diffuser is a vaneless diffuser partially delimited by a shroud wall and a hub wall defining the annular diffuser passage therebetween. .   Either or both of the shroud wall and the hub wall are formed such that the axial width of the annular diffuser passage decreases as the shroud wall and the hub wall extend radially outward. The compression system according to claim 13.   The compression system of claim 11, wherein the stationary diffuser includes a plurality of low stiffness diffuser vanes extending into the annular diffuser passage. The stationary diffuser is partially bounded by a shroud wall and a hub wall defining the annular diffuser passage therebetween;
The plurality of low stiffness diffuser vanes are arranged vertically in the annular diffuser passage, and from the shroud wall, the hub wall, or both the shroud wall and the hub wall into the annular diffuser passage. The compression system of claim 15, wherein the compression system extends. A method for compressing a process fluid comprising:
Driving the rotating shaft of the supersonic compressor via a drive device operably coupled to the supersonic compressor;
A fluid characteristic of the process fluid flowing through an inlet passage defined by the inlet of the supersonic compressor is at least one pivotally connected to the housing of the supersonic compressor and extending into the inlet passage. Establishing via an operable inlet guide vane;
The process fluid flowing through the inlet passage of the supersonic compressor is attached around the rotating shaft so that it is drawn into the centrifugal impeller and discharged from the tip of the centrifugal impeller through a plurality of flow paths. Rotating the centrifugal impeller, wherein the discharged process fluid has a supersonic velocity with an exit absolute Mach number greater than or equal to about 1.0;
The discharged process fluid having supersonic speed is fixed to a fixed diffuser so that the pressure energy of the discharged process fluid is increased and the discharged process fluid is compressed at a compression ratio of about 8: 1 or more. Flowing through an annular diffuser passage defined by and fluidly connected to the plurality of flow paths;
A method comprising the steps of: Adjusting the at least one operable inlet guide vane to establish fluid properties of the process fluid;
The fluid property is selected from the group consisting of a flow pattern, a first velocity, mass flow rate, pressure, and temperature; and
The method of claim 17, wherein the process fluid comprises carbon dioxide. The stationary diffuser is a vaneless diffuser partially delimited by a shroud wall and a hub wall defining an annular diffuser passage therebetween;
The shroud wall that delimits the annular diffuser passage is a straight wall, an undulating wall, or a combination thereof;
The method of claim 17, wherein the hub wall that delimits the annular diffuser passage is a straight wall, a undulating wall, or a combination thereof. The stationary diffuser is a vaned diffuser partially bounded by a shroud wall and a hub wall defining the annular diffuser passage therebetween;
The method of claim 17, wherein the stationary diffuser comprises a plurality of low stiffness diffuser vanes extending into the annular diffuser passage from either or both of a shroud wall and a hub wall.

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