WO2016059199A1 - Turbomachine centrifuge à deux étages disposés dos-à-dos et avec un conduit de transfert annulaire entre les étages - Google Patents

Turbomachine centrifuge à deux étages disposés dos-à-dos et avec un conduit de transfert annulaire entre les étages Download PDF

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Publication number
WO2016059199A1
WO2016059199A1 PCT/EP2015/073978 EP2015073978W WO2016059199A1 WO 2016059199 A1 WO2016059199 A1 WO 2016059199A1 EP 2015073978 W EP2015073978 W EP 2015073978W WO 2016059199 A1 WO2016059199 A1 WO 2016059199A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbomachine
duct
outlet
assembly
inlet
Prior art date
Application number
PCT/EP2015/073978
Other languages
English (en)
Inventor
Manuele Bigi
Giuseppe Sassanelli
Andrea Massini
Luciano Mei
Franco Frosini
Original Assignee
Nuovo Pignone Srl
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 Nuovo Pignone Srl filed Critical Nuovo Pignone Srl
Priority to RU2017111845A priority Critical patent/RU2017111845A/ru
Priority to JP2017518847A priority patent/JP2017531129A/ja
Priority to EP15787912.3A priority patent/EP3207259A1/fr
Priority to US15/519,591 priority patent/US20170241433A1/en
Publication of WO2016059199A1 publication Critical patent/WO2016059199A1/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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
    • 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
    • F04D25/0686—Units comprising pumps and their driving means the pump being electrically driven specially adapted for submerged use
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps

Definitions

  • Embodiments of the subject matter disclosed herein correspond to turbomachine assemblies, transfer ducts for connecting turbomachines, and methods of arranging ducts.
  • Fig. l shows, by way of example, a turbomachine assembly 100 comprising a first multistage centrifugal compressor 1 10, a second multistage centrifugal compressor 120 and an electric motor (not shown in the figure); all the machines of the assembly 100 are housed inside a hermetic casing 130.
  • the assembly 100 is intended for subsea installation.
  • the first compressor 1 10 has an inlet 1 1 1 (on the left side in the figure), an outlet 1 12 (on the right side in the figure) and a rotary shaft 1 13 (protruding for example on both sides in the figure).
  • the second compressor 120 has an inlet 121 (on the right side in the figure), an outlet 122 (on the left side in the figure) and a rotary shaft 123 (protruding for example on both sides in the figure); the shafts 1 13 and 123 are (substantially) coaxial and mechanically coupled together (often a unique solid shaft is used).
  • a configuration such as the one shown in Fig. l is called "back-to-back" as the two machines face in opposite directions.
  • the compressors 1 10 and 120 are located adjacent to each other and the outlet 1 12 of the first compressor 1 10 faces the outlet 122 of the second compressor 120 and is close to it; the outlet 1 12 of the first compressor 1 10 and the inlet 121 of the second compressor 120 are fluidly connected but they are remote from each other.
  • the "back-to-back" configuration is advantageous as, during operation of the assembly, the axial thrust exerted by one of the two machines may be (substantially) balanced by the axial thrust of the other one of the two machines and does not load axially the bearings of the machines; the "back-to-back” configuration is even more advantageous when magnetic bearings are used for supporting the two machines as magnetic bearings can not withstand high axial thrust.
  • cascade connection of the two compressors 1 10 and 120 is realized through a transfer piping 140 that is totally external to the casing 130.
  • Piping 140 consists of a shaped pipe 141 with a first flange 142 (on the left in the figure) and a second flange 143 (on the right in the figure) at its two ends.
  • the assembly 100 comprises: a main inlet pipe 131 with a flange 132, a main outlet pipe 133 with a flange 134, an intermediate inlet pipe 135 with a flange 136 and an intermediate outlet pipe 137 with a flange 138; all these pipes protrude from casing 130.
  • Inlet pipe 131 is fluidly connected to inlet 1 1 1 (see arrow in the figure), outlet pipe 133 is fluidly connected to outlet 122 (see arrow in the figure), inlet pipe 135 is fluidly connected to inlet 121 (see arrow in the figure), outlet pipe 137 is fluidly connected to outlet 1 12 (see arrow in the figure).
  • Flange 138 is mechanically connected to flange 142 and flange 136 is mechanically connected to flange 143 so that the outlet of the first compressor 1 10 is fluidly connected to the inlet of the second compressor 120.
  • An external transfer piping like the one of Fig.1 may create problems especially (but not only) when the assembly is placed deep in the sea; there may be leakage from the mechanical connections at its two ends, there may be damages due to collisions and/or erosions and its repairing requires disconnecting and connecting flanges. Furthermore, there may be cooling by the sea water of the working fluid that flows inside it and the working efficiency of the assembly is influenced by such cooling.
  • Another important idea is to shape the transfer duct as an annular duct.
  • Another important idea is to provide one pipe-shape seat inside the transfer duct.
  • Another important idea is to provide one or more struts inside the transfer duct.
  • First embodiments of the subject matter disclosed herein relate to turbomachines assembly.
  • the turbomachine assembly comprises: a first turbomachine having an inlet, an outlet and a rotary shaft, a second turbomachine having an inlet, an outlet and a rotary shaft, a transfer duct fluidly connecting the outlet of the first turbomachine to the inlet of the second turbomachine, and a casing housing the turbomachines and the transfer duct; the turbomachines are located adjacent to each other so that the outlet of the second turbomachine is close to the outlet of the first turbomachine and the inlet of the second turbomachine is remote from the outlet of the first turbomachine; the outlet of the second turbomachine has an end portion shaped like a cochlea; the transfer duct has an annular shape, and surrounds the end portion of the outlet of the second turbomachine.
  • Second embodiments of the subject matter disclosed herein relate to transfer ducts for fluidly connecting the outlet of a first turbomachine to the inlet of a second turbomachine.
  • the transfer duct consists of a single duct; the single duct has an annular shape around an axis; the single duct develops at the begin at least partially radially, in the middle substantially axially and at the end at least partially radially; the single duct has one pipe-shaped seat for housing at least partially another duct crossing it; the single duct has preferably one or more struts for structural reinforcement.
  • Third embodiments of the subject matter disclosed herein relate to methods of arranging a first and a second distinct and separate ducts, the first duct being designed for feeding a first fluid in an axial direction and the second duct being designed for feeding a second fluid in a radial direction.
  • the method comprises: configuring the first duct as a single annular duct so to define an internal space, configuring the second duct as a single spiral duct, positioning the second duct inside the internal space defined by the first duct, prolonging the single spiral duct so to cross the single annular duct.
  • Fig. l is a schematic view of a longitudinal cross-section of a turbomachine assembly according to the prior art
  • Fig.2 is a schematic view of a longitudinal cross-section of a turbomachine assembly according to the present invention
  • Fig.3 is a partial enlarged detailed view of Fig.2 and regards a transfer duct
  • Fig.4 shows a partial longitudinal cross-sectional detailed view of an embodiment of a turbomachine assembly according to the present invention
  • Fig.5 shows a partial transversal cross-section view corresponding to the embodiment of Fig.4.
  • Fig.2 is a schematic view of a longitudinal cross-section of a turbomachine assembly 200; it comprises: a first turbomachine 210 having an inlet 21 1 , an outlet 212 and a rotary shaft 213 (with axis 214), a second turbomachine 220 having an inlet 221 , an outlet 222 and a rotary shaft 223 (with axis 224), a transfer duct 240 fluidly connecting the outlet 212 to the inlet 221 , and a casing 230 housing turbomachines 210 and 220 and transfer duct 240.
  • turbomachines 210 and 220 are located adjacent to each other so that the outlet 222 of the second turbomachine 220 is close to the outlet 212 of the first turbomachine 210 and the inlet 221 of the second turbomachine 220 is remote from the outlet 212 of the first turbomachine 210; in particular, they are in the so-called "back-to-back configuration".
  • shafts 213 and 223 are exactly coaxial and a single axis 204 corresponds to both axis 214 of shaft 213 and axis 224 of shaft 223.
  • shafts 213 and 223 are mechanically coupled together through a rigid joint (not highlighted in the figure); alternatively, for example, a unique solid shaft may be used.
  • the outlet 222 of the second turbomachine 220 has an end portion 225 shaped like a cochlea (i.e. a spiral duct).
  • the transfer duct 240 is preferably a single duct with an annular shape (both internally and externally) and surrounds the end portion 225 of the outlet 222 of the second turbomachine 220; in particular, the transfer duct 240 surrounds axially and radially (i.e. completely) not only portion 225 but the whole second turbomachine 220 (only small zones close to the shaft 223 of the second turbomachine 220 are not surrounded - see right side and left side in Fig.2).
  • the transfer duct 240 is completely internal to the casing 230.
  • the transfer duct 240 develops at the begin 241 at least partially radially (getting far from its axis 204, i.e. increasing its distance) and in the middle 242 substantially axially and at the end 243 at least partially radially (getting close to its axis 204, i.e. decreasing its distance) - see Fig.3 wherein the transfer duct 240 (with its longitudinal axis 204 of symmetry) of Fig.2 is partially shown in cross- section and in enlarged scale.
  • the transfer duct 240 has a first end portion, at the begin 241 , directly fluidly connected to the outlet 212 of the first turbomachine 210 (for example "outlet diffuser") and a second end portion, at the end 243, directly fluidly connected to the inlet 221 of the second turbomachine 220 (for example "inlet guider").
  • the area of the cross-section of the transfer duct 240 increases (i.e. the transfer duct widens); this is shown in Fig.2 and is even more clear in Fig.4.
  • the transfer duct 240 develops as a mantle around the second turbomachine 220 starting at the outlet 222 of the second turbomachine 220 (actually a bit before) and ending at the inlet 221 of the second turbomachine 220 (actually a bit after).
  • Assembly 200 has one inlet duct, in the form of a pipe 231 with a flange 232, and one outlet duct, in the form of a pipe 233 with a flange 234; both ducts, i.e. pipes 231 and 233, protrude from the casing 230.
  • the end portion 225 of the outlet 222 of the second turbomachine 220 is fluidly connected to the outlet duct 233 of the assembly through a connection duct 235.
  • the connection duct 235 passes through the transfer duct 240; more specifically, it goes from one side, i.e. the internal wall, to the other side, i.e. the external wall, of the transfer duct 240.
  • connection duct 235 is a prolongation of the cochlea 225 and is partially housed in a pipe-shaped seat of the transfer duct 240 (see also Fig.5); the transfer duct 240 may have one or more elements (for example connecting its internal wall and its external wall) for structural reinforcement.
  • Fig.4 and Fig.5 should be considered together as they show detailed views of a possible embodiment; they embody technical solutions similar to those described with reference to the schematic views of Fig.2 and Fig.3.
  • Fig.4 highlights a transfer duct (in the form of a single annular duct) that develops at the begin 441 at least partially radially (in an outward direction, i.e. far from the shafts and their axes), in the middle 442 substantially axially and at the end 443 at least partially radially (in an inward direction, i.e. close to the shafts and their axes).
  • a transfer duct in the form of a single annular duct
  • the end portion of the transfer duct at the begin 441 is directly fluidly connected to a duct 412 (for example a "outlet diffuser") that may be considered an outlet of a first turbomachine; the end portion of the transfer duct at the end 443 is directly fluidly connected to a duct 421 (for example a "inlet guider") that may be considered an inlet of a second turbomachine.
  • the transfer duct is completely internal to the casing and surrounds the second turbomachine completely in the radial direction and almost completely in the axial direction (only small zones close to the shaft of the second turbomachine are not surrounded).
  • the radial distance between the transfer duct and the axis of the shaft of the second machine increases along the begin 441 of the transfer duct; this allows to overcome the second turbomachine.
  • the area of the cross-section of the transfer duct increases along the begin 441 of the transfer duct (in other words, the transfer duct widens); this allows to reduce the speed (especially its axial component) of the fluid flowing inside the transfer duct and consequently to recover some pressure; in other words, the initial portion of the transfer duct acts similarly to an outlet cochlea of a turbomachine.
  • Fig.4 highlights also an end portion 425 of an outlet of the second turbomachine (corresponding to end portion 225 of Fig.2) that is shaped like a cochlea; portion 525 may be connected, for example, to an "outlet diffuser" of the second turbomachine.
  • the portion of the transfer duct at the begin 441 surrounds the end portion 425 of the outlet of the second turbomachine completely in the radial direction and completely, only on one side, in the axial direction.
  • Fig.5 highlights a transfer duct 540 in the form of a single annular duct (around an axis 504); this allows to gradually reduce (to an angle in the range e.g. of 10°- 30°) the rotational component of the speed of the fluid flowing inside the transfer duct.
  • the figure seems to show two semi-annular cavities separated by elements 544 and 545; indeed, the annular cavity is only one as elements 544 and 545 have a limited axial extension.
  • the external side or wall of transfer duct 540 is adjacent or very close to the casing of the assembly while the internal side or wall of the transfer duct 540 is adjacent to an end portion 525 of the outlet of a second turbomachine (corresponding to end portion 225 of Fig.2) that is shaped like a cochlea; portion 525 leaves a central space 501 free.
  • Portion 525 is to be fluidly connected to an outlet duct of the assembly; this is the purpose of connection duct 535 (corresponding to duct 235 of Fig.2).
  • Connection duct 535 passes through transfer duct 540; more specifically, it goes from one side, i.e. the internal wall, to the other side, i.e. the external wall, of the transfer duct 540.
  • Connection duct 535 is a prolongation of the cochlea-shape duct 525.
  • Transfer duct 540 has one pipe-shaped seat 544 housing partially (or totally) connection duct 535 crossing it.
  • Transfer duct 540 has one strut 545 (or more than one, for example two or three or four or five or six or seven or ...) for structural reinforcement; such structural element is a (relatively) short solid element that may be arranged radially or substantially radially.
  • Heat insulating material (for example in the form of layers) may be place between the transfer duct and the cochlea-shape duct and/or between connection duct and transfer duct.
  • Fig.4 and Fig.5 have allowed to describe and show in detail a possible configuration and a possible arrangement of a transfer duct according to the present invention.
  • first and a second distinct and separate ducts have been arranged; the first duct is designed for feeding a first fluid in an axial direction and the second duct is designed for feeding a second fluid in a radial direction.
  • the following steps are provided: configuring the first duct as a single annular duct so to define an internal space, configuring the second duct as a single spiral duct, positioning the second duct inside the internal space defined by the first duct, and prolonging the single spiral duct so to cross the single annular duct.
  • Such arrangement is particularly effective when the first and second fluid flows come from outlets of turbomachines; in fact, it allows to minimize load losses and/or heat losses and/or heat exchanges.
  • the present invention is very flexible.
  • the first and second turbomachines mentioned before may be for example compressors or pumps, preferably multistage centrifugal machines (the number of stages of the first machine may be equal to or different from the number of stages of the second machine); but the assembly may comprise further machines, for example an engine such as an electric motor or a turbine; especially when an electric motor is used, the compressors or pumps are fluidly well isolated from the engine.
  • the first turbomachine is a compressor or pump, preferably a multistage centrifugal machine
  • the second turbomachine is a turbine, preferably a multistage machine.
  • all the machines of the assembly are housed inside the same casing.
  • the rotary shafts of these machines are mechanically coupled together; in Fig.2, shaft 213 of machine 210 and shaft 223 of machine 220 are mechanically coupled together through a rigid joint (a unique solid shaft is an alternative).
  • a typical and particularly advantageous application of the present invention is in turbomachine assemblies designed to be installed subsea.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Cette invention concerne un ensemble turbomachine (200), comprenant une première turbomachine (210) présentant un orifice d'entrée (211), un orifice de sortie (212) et un arbre rotatif (213), une seconde turbomachine (220) présentant un orifice d'entrée (221), un orifice de sortie (222) et un arbre rotatif (223), un conduit de transfert (240) assurant le raccordement fluidique de l'orifice de sortie (212) de la première turbomachine (210) à l'orifice d'entrée (221) de la seconde turbomachine (220), et un carter (230) logeant les turbomachines (210, 220) et le conduit de transfert (240). Lesdites turbomachines (201, 220) sont disposées de manière adjacente de sorte que l'orifice de sortie (222) de la seconde turbomachine (220) est proche de l'orifice de sortie (212) de la première turbomachine (210) et l'orifice d'entrée (221) de la seconde turbomachine (220) est éloigné de l'orifice de sortie (212) de la première turbomachine (210). L'orifice de sortie (222) de la seconde turbomachine (220) présente une partie d'extrémité (225) en forme de cochlée (c'est-à-dire de conduit hélicoïdal). Le conduit de transfert (240) présente une forme annulaire et il entoure la partie d'extrémité (225) de l'orifice de sortie (222) de la seconde turbomachine (220).
PCT/EP2015/073978 2014-10-17 2015-10-16 Turbomachine centrifuge à deux étages disposés dos-à-dos et avec un conduit de transfert annulaire entre les étages WO2016059199A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
RU2017111845A RU2017111845A (ru) 2014-10-17 2015-10-16 Центрифужная турбомашина с двумя ступенями, расположенными одна за другой, и с кольцевым трубопроводом между ступенями
JP2017518847A JP2017531129A (ja) 2014-10-17 2015-10-16 背中合わせに２つのステージを配置してステージ間に環状の移送ダクトを備えた遠心ターボ機械
EP15787912.3A EP3207259A1 (fr) 2014-10-17 2015-10-16 Turbomachine centrifuge à deux étages disposés dos-à-dos et avec un conduit de transfert annulaire entre les étages
US15/519,591 US20170241433A1 (en) 2014-10-17 2015-10-16 Centrifugal turbomachine with two stages arranged back-to-back and with an annular transfer duct between the stages

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITCO20140033 2014-10-17
ITCO2014A000033 2014-10-17

Publications (1)

Publication Number Publication Date
WO2016059199A1 true WO2016059199A1 (fr) 2016-04-21

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PCT/EP2015/073978 WO2016059199A1 (fr) 2014-10-17 2015-10-16 Turbomachine centrifuge à deux étages disposés dos-à-dos et avec un conduit de transfert annulaire entre les étages

Country Status (5)

Country Link
US (1) US20170241433A1 (fr)
EP (1) EP3207259A1 (fr)
JP (1) JP2017531129A (fr)
RU (1) RU2017111845A (fr)
WO (1) WO2016059199A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT201800011099A1 (it) * 2018-12-14 2020-06-14 Nuovo Pignone Tecnologie Srl Sistema di de-idrogenazione di propano con un compressore di effluente di reattore a cassa singola e metodo

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3729486C1 (de) * 1987-09-03 1988-12-15 Gutehoffnungshuette Man Kompressoreinheit
EP0726397A1 (fr) * 1995-02-10 1996-08-14 Ebara Corporation Pompe avec passage d'écoulement amélioré
WO2000001935A1 (fr) * 1998-07-02 2000-01-13 Alliedsignal Inc. Turbocompresseur a faible vitesse et a rapport de pression eleve
US20050005606A1 (en) * 2003-07-11 2005-01-13 Gary Vrbas Turbocharger compressor with non-axisymmetric deswirl vanes
US20100239437A1 (en) * 2009-03-20 2010-09-23 Dresser-Rand Co. Fluid channeling device for back-to-back compressors

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3729486C1 (de) * 1987-09-03 1988-12-15 Gutehoffnungshuette Man Kompressoreinheit
EP0726397A1 (fr) * 1995-02-10 1996-08-14 Ebara Corporation Pompe avec passage d'écoulement amélioré
WO2000001935A1 (fr) * 1998-07-02 2000-01-13 Alliedsignal Inc. Turbocompresseur a faible vitesse et a rapport de pression eleve
US20050005606A1 (en) * 2003-07-11 2005-01-13 Gary Vrbas Turbocharger compressor with non-axisymmetric deswirl vanes
US20100239437A1 (en) * 2009-03-20 2010-09-23 Dresser-Rand Co. Fluid channeling device for back-to-back compressors

Also Published As

Publication number Publication date
US20170241433A1 (en) 2017-08-24
RU2017111845A (ru) 2018-11-21
JP2017531129A (ja) 2017-10-19
RU2017111845A3 (fr) 2019-03-07
EP3207259A1 (fr) 2017-08-23

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