WO2023151862A1 - Système de turbomachine à étages multiples et procédé de fonctionnement - Google Patents

Système de turbomachine à étages multiples et procédé de fonctionnement Download PDF

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Publication number
WO2023151862A1
WO2023151862A1 PCT/EP2023/025046 EP2023025046W WO2023151862A1 WO 2023151862 A1 WO2023151862 A1 WO 2023151862A1 EP 2023025046 W EP2023025046 W EP 2023025046W WO 2023151862 A1 WO2023151862 A1 WO 2023151862A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbo machine
cooling
supply
fluid
line
Prior art date
Application number
PCT/EP2023/025046
Other languages
English (en)
Inventor
Nicolas BRUNNER
Original Assignee
Cryostar Sas
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Cryostar Sas filed Critical Cryostar Sas
Publication of WO2023151862A1 publication Critical patent/WO2023151862A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/5806—Cooling the drive system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/04—Shafts or bearings, or assemblies thereof
    • F04D29/046—Bearings
    • F04D29/048—Bearings magnetic; electromagnetic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5826—Cooling at least part of the working fluid in a heat exchanger

Definitions

  • the present invention relates to a multistage turbo machine system comprising multiple turbo machines, and to a method of f operating such multistage turbo machine system.
  • Turbo machines can be used in different applications.
  • cryogenic applications i.e. applications with process gases at cryogenic temperatures, e.g., plants for air separation or the like
  • cryogenic turbo machines like turbo expanders and/or compressors are often used.
  • Such turbo machines typically comprise an expander impeller and/or a compressor impeller, which are fixed on a shaft.
  • multiple stages of turbo machine e.g., for compressing operating fluid
  • multistage turbo machine systems comprising multiple turbo compressors can be used.
  • cooling of the individual compressors or their motors can be difficult.
  • WO 2019/077212 A1 and WO 2019/077213 A1 disclose multistage fluid compression systems comprising two compressors. Parts or fractions of operating fluid can be used for cooling purposes.
  • WO 2019/077212 A1 describes a serial cooling
  • WO 2019/077213 A1 describes a parallel cooling of said two compressors or their motors.
  • Serial cooling requires two cooling gas heat exchangers, and parallel cooling means the same level of pressure for both cavities (motor cavities or housing) of said two compressors. It is therefore an object of the present invention to provide an improved multistage fluid compression system.
  • the invention relates to a multistage turbo machine system, which comprises (at least) a first turbo machine with a drive unit and a second turbo machine with a drive unit.
  • the system might comprise a third turbo machine with a drive unit, as will further be explained later.
  • These turbo machines can be of radial or axial type; also different types in the same system might be used.
  • these turbo machines are of magnetic bearing type (magnetic turbo compressors).
  • Each of these drive units can comprise a motor (e.g., an electrical motor) with a housing (or cavity).
  • Such drive unit typically, also comprises a gearing and/or bearings (preferably, magnetic bearings).
  • Each of said a turbo machines can comprise or be configured as a turbo compressor. In such case, said system can be considered a multistage fluid compression system.
  • one or more of said turbo machines can (e.g., additionally) comprise or be configured as a turbo expander.
  • such multistage turbo machine system comprises a first supply line configured to supply operating fluid to be compressed to an inlet of said first turbo machine, a second supply line configured to supply operating fluid, which is provided at an outlet of said first turbo machine, to an inlet of said second turbo machine, and a third supply line for operating fluid, which is provided at an outlet of said second turbo machine.
  • operating fluid like gas can be supplied the first turbo machine, e.g., be compressed, then further supplied to the second turbo machine, be, e.g., further compressed and then be provided for any further use.
  • a first operating fluid heat exchanger is provided in said second supply line, i.e. , operating fluid in said second supply line can be or is cooled by said first operating fluid heat exchanger.
  • a second operating fluid heat exchanger is provided in said third supply line.
  • said system comprises a first cooling line configured to divert part (or fraction) of operating fluid in said second supply line and supply it, as cooling fluid, to said drive unit of said first turbo machine, and a second cooling line configured to supply cooling fluid from said drive unit of said first turbo machine to said first supply line.
  • said first cooling line is connected to said second supply line between said first operating fluid heat exchanger and said inlet of said second turbo machine. In this way, cooling of the drive unit of said first turbo machine can be provided by means of said operating fluid.
  • said system comprises a third cooling line configured to divert part (or fraction) of operating fluid in said third supply line and supply it, as cooling fluid, to said drive unit of said second turbo machine, and a fourth cooling line configured to supply cooling fluid from said drive unit of said second turbo machine to said second supply line.
  • said third cooling line is connected to said third supply line after said second operating fluid heat exchanger. In this way, cooling of the drive unit of said second turbo machine can also be provided by means of said operating fluid.
  • a particular advantage of such specific connection of cooling lines in a multistage fluid compression system is that a single cooling fluid heat exchanger is sufficient for the entire cooling fluid used.
  • Such cooling fluid heat exchanger is preferably provided in said second cooling line.
  • said system further comprises a first sealing fluid line configured to divert part (or fraction) of operating fluid in said third supply line and supply it, as sealing fluid, to said drive unit of said first turbo machine.
  • a first sealing fluid line configured to divert part (or fraction) of operating fluid in said third supply line and supply it, as sealing fluid, to said drive unit of said first turbo machine.
  • Said system preferably comprises a third turbo machine with drive unit, as mentioned above.
  • said fourth supply line is configured to supply operating fluid, which is provided at said outlet of said second turbo machine, to an inlet of said third turbo machine.
  • Said system further comprises a fourth supply line for operating fluid, which is provided at an outlet of said third turbo machine.
  • a third operating fluid heat exchanger is then provided in said fourth supply line.
  • said system further comprises a fifth cooling line configured to divert part (or fraction) of operating fluid in said fourth supply line and supply it, as sealing and/or cooling fluid, to said drive unit of said third turbo machine.
  • said fifth cooling line is connected to said fourth supply line after said third operating fluid heat exchanger.
  • Said system further comprises a sixth cooling line configured to supply sealing and/or cooling fluid from said drive of said third turbo machine to said second cooling line, preferably before said cooling fluid heat exchanger.
  • a sixth cooling line configured to supply sealing and/or cooling fluid from said drive of said third turbo machine to said second cooling line, preferably before said cooling fluid heat exchanger.
  • said system further comprises a second sealing line configured to divert part (or fraction) of operating fluid in said fourth supply line and supply it, as sealing fluid, to said drive unit of said second turbo machine.
  • a second sealing line configured to divert part (or fraction) of operating fluid in said fourth supply line and supply it, as sealing fluid, to said drive unit of said second turbo machine.
  • said third turbo machine comprises a turbo compressor and a turbo expander.
  • a turbo compressor can be combined with a turbo expander in a turbo machine, using the same drive unit.
  • a third sealing line can be provided, which is configured to supply sealing fluid from said drive unit of said third turbo machine to said second supply line.
  • sealing fluid like seal gas sent to the cavity (or housing) of a drive unit of a turbo machine can also be used as cooling gas (saving in term of flow consumption).
  • No cooling fluid or gas is necessary for, in particular, magnetic, turbo machines because sealing fluid like seal gas provides sufficient cooling flow.
  • Said first operating fluid heat exchanger can be shared for main refrigerant gas cooling and cooling gas re-cooling. Operating or cooling fluid of said second turbo machine can be let down to intermediate pressure (downstream said first turbo machine).
  • Cooling fluid or gas flow is let down to the lowest fluid or gas pressure (inlet of said first turbo machine) and recompressed up to high pressure (downstream/outlet of said second turbo machine). Since the cooling fluid lines for the different turbo machines are independent, it is possible to set two different flow values for the cooling lines depending on actual heating of the turbo machines (and, thus, avoid overconsumption).
  • the invention also relates to a method for operating a multistage turbo machine system like the one mentioned above in any of its embodiments. With respect to preferred embodiments and advantages, it is referred to the remarks from above, which apply correspondingly.
  • Fig. 1 illustrates a multistage turbo machine system according to a preferred embodiment of the invention.
  • Fig. 2 illustrates a multistage turbo machine system according to a further preferred embodiment of the invention.
  • Fig. 1 schematically illustrates a multistage turbo machine system 100 according to a preferred embodiment of the invention.
  • Said system 100 comprises a first turbo machine 110 with a drive unit 112, a second turbo machine 120 with a drive unit 122, and a third turbo machine 130 with a drive unit 132.
  • Each of said first turbo machine 110 and said second turbo machine 120 are configured as a turbo compressor, having a compressor impeller 111 and 121 , respectively.
  • Said third turbo machine 130 comprises a turbo compressor 1138 with a compressor impeller 131 and a turbo expander 139 with a expander impeller 137.
  • Said drive unit 112 comprises a bearing 113 and a motor 114 in a housing or casing.
  • said drive unit 122 comprises a bearing 123 and a motor 124 in a housing or casing, and said drive unit 132 comprises a bearing 133 and a motor 134 in a housing or casing.
  • said system 100 comprises a first supply line S1 configured to supply operating fluid a to an inlet of said first turbo machine 110, a second supply line S2 configured to supply operating fluid b, which is provided at an outlet of said first turbo machine 110, to an inlet of said second turbo machine 120, a third supply line S3 configured to supply operating fluid c, which is provided at an outlet of said second turbo machine 120, to an inlet of said third turbo machine 130 (the inlet of the turbo compressor 138), and a fourth supply line S4 for operating fluid d, which is provided at an outlet of said third turbo machine 130 (the outlet of the turbo compressor 138).
  • operating fluids a, b, c and d correspond to the same operating fluid at different stages of said system 100.
  • Said system 100 further comprises a fifth supply line S5 configured to supply operating fluid e to another inlet of said third turbo machine 130 (the inlet of the turbo expander 139), and sixth supply line S6 configured to supply operating fluid f provided at another outlet of said third turbo machine 130 (the outlet of the turbo expander 139).
  • Said system 100 further comprises a first operating fluid heat exchanger 115 (provided or arranged) in said second supply line S2, a second operating fluid heat exchanger 12 5(provided or arranged) in said third supply line S3, and a third operating fluid heat exchanger 135 (provided or arranged) in said fourth supply line S4.
  • said system 100 comprises a first cooling line L1 configured to divert part of operating fluid b in said second supply line S2 and supply it, as cooling fluid g, to said drive unit 112 of said first turbo machine 110.
  • Said first cooling line L1 is connected to said second supply line S2 between said first operating fluid heat exchanger 115 and said inlet of said second turbo machine 120.
  • Said system 100 further comprises a second cooling line L2 configured to supply cooling fluid h from said drive unit 112 of said first turbo machine 110 to said first supply line S1.
  • Said system 100 further comprises a cooling fluid heat exchanger 150 (arranged or provided) in said second cooling line L2.
  • said system 100 comprises a third cooling line L3 configured to divert part of operating fluid c in said third supply line S3 and supply it, as cooling fluid k, to said drive unit 122 of said second turbo machine 120, and a fourth cooling line L4 configured to supply cooling fluid I from said drive unit 122 of said second turbo machine 120 to said second supply line S2.
  • said cooling fluid I is re-used. No further cooling fluid heat exchanger is necessary.
  • said system 100 comprises a fifth cooling line L5 configured to divert part of operating fluid d in said fourth supply line S4 and supply it, as sealing and/or cooling fluid m, to said drive unit 132 of said third turbo machine 130, and a sixth cooling line L6 configured to supply sealing and/or cooling fluid n from said drive unit 132 of said third turbo machine 130 to said second cooling line L2.
  • a fifth cooling line L5 configured to divert part of operating fluid d in said fourth supply line S4 and supply it, as sealing and/or cooling fluid m, to said drive unit 132 of said third turbo machine 130
  • a sixth cooling line L6 configured to supply sealing and/or cooling fluid n from said drive unit 132 of said third turbo machine 130 to said second cooling line L2.
  • sealing gas o and p is supplied to or arrives in said drive unit 132.
  • Flows o and p are, typically, internal leakage flows of the turbomachine (both, on expander side and compressor side). This is a flow coming from main process flow c, e going through the expander/compressor and a small portion of the main process flow is passing behind the impeller (because of space at the top of the impeller) and going into the cavity or housing of said turbo machine or its drive unit.
  • said system 100 comprises a third sealing line G3 configured to supply sealing fluid q from said drive unit 132 of said third turbo machine 130 to said second cooling line L2. In this way, said sealing fluid p is re-used. No further cooling or other fluid exchanger is necessary.
  • Fig. 2 schematically illustrates a multistage turbo machine system 200 according to a further preferred embodiment of the invention.
  • System 200 corresponds to system 100 of Fig. 1 , which additionally lines and fluid flows.
  • Fig. 1 schematically illustrates a multistage turbo machine system 200 according to a further preferred embodiment of the invention.
  • System 200 corresponds to system 100 of Fig. 1 , which additionally lines and fluid flows.
  • Fig. 1 schematically illustrates a multistage turbo machine system 200 according to a further preferred embodiment of the invention.
  • System 200 corresponds to system 100 of Fig. 1 , which additionally lines and fluid flows.
  • Fig. 1 schematically illustrates a multistage turbo machine system 200 according to a further preferred embodiment of the invention.
  • Fig. 1 schematically illustrates a multistage turbo machine system 200 according to a further preferred embodiment of the invention.
  • System 200 corresponds to system 100 of Fig. 1 , which additionally lines and fluid flows.
  • Fig. 1 schematically illustrates a multistage turbo machine system 200 according
  • Said system 200 comprises a first sealing line G1 configured to divert part (or fraction) of operating fluid c from said third supply line S3 to supply it, as sealing fluid t, to said drive unit 112 of said first turbo machine 110.
  • Said system 200 comprises a second sealing line G2 configured to divert part (or fraction) of cooling fluid m from said fifth cooling line L5 to supply it, as sealing fluid s, to said drive unit 122 of said second turbo machine 120. Sealing gas provided in this way can also be used for cooling purposes and be re-used afterwards.

Abstract

L'invention concerne un système de turbomachine à étages multiples (100) comprenant : une première turbomachine (110) avec une unité d'entraînement (112), une seconde turbomachine (120) avec une unité d'entraînement (122), une première ligne d'alimentation (S1) conçue pour fournir un fluide de fonctionnement (a) à une entrée de ladite première turbomachine (110), une deuxième ligne d'alimentation (S2) conçue pour fournir un fluide de fonctionnement (b), qui est prévue au niveau d'une sortie de ladite première turbomachine (110), à une entrée de ladite seconde turbomachine (120) et une troisième ligne d'alimentation (S3) pour un fluide de fonctionnement (c), qui est prévue au niveau d'une sortie de ladite seconde turbomachine (120), ledit système (100) comprenant en outre : une première ligne de refroidissement (L1) conçue pour dévier une partie du fluide de fonctionnement (b) dans ladite deuxième ligne d'alimentation (S2) et le fournir, en tant que fluide de refroidissement (g), à ladite unité d'entraînement (112) de ladite première turbomachine (110) et une deuxième ligne de refroidissement (L2) conçue pour fournir un fluide de refroidissement (h) de ladite unité d'entraînement (112) de ladite première turbomachine (110) à ladite première ligne d'alimentation (S1), ledit système (100) comprenant en outre : une troisième ligne de refroidissement (L3) conçue pour dévier une partie du fluide de fonctionnement (c) dans ladite troisième ligne d'alimentation (S3) et le fournir, en tant que fluide de refroidissement (k), à ladite unité d'entraînement (122) de ladite seconde turbomachine (120) et une quatrième ligne de refroidissement (L4) conçue pour fournir un fluide de refroidissement (I) de ladite unité d'entraînement (122) de ladite seconde turbomachine (120) à ladite deuxième ligne d'alimentation (S2). L'invention concerne également un procédé de fonctionnement d'un tel système.
PCT/EP2023/025046 2022-02-10 2023-02-02 Système de turbomachine à étages multiples et procédé de fonctionnement WO2023151862A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP22315031 2022-02-10
EP22315031.9 2022-02-10

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WO2023151862A1 true WO2023151862A1 (fr) 2023-08-17

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2856981A1 (fr) * 2012-05-25 2015-04-08 Kturbo Inc. Système turbocompresseur possédant au moins deux moteurs d'entraînement
WO2019077212A1 (fr) 2017-10-16 2019-04-25 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Dispositif et procédé de compression et machine de réfrigération
WO2019077213A1 (fr) 2017-10-16 2019-04-25 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Dispositif et procédé de compression

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2856981A1 (fr) * 2012-05-25 2015-04-08 Kturbo Inc. Système turbocompresseur possédant au moins deux moteurs d'entraînement
WO2019077212A1 (fr) 2017-10-16 2019-04-25 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Dispositif et procédé de compression et machine de réfrigération
WO2019077213A1 (fr) 2017-10-16 2019-04-25 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Dispositif et procédé de compression

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