US3824029A - Centrifugal supersonic compressor - Google Patents

Centrifugal supersonic compressor Download PDF

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Publication number
US3824029A
US3824029A US00243371A US24337172A US3824029A US 3824029 A US3824029 A US 3824029A US 00243371 A US00243371 A US 00243371A US 24337172 A US24337172 A US 24337172A US 3824029 A US3824029 A US 3824029A
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United States
Prior art keywords
rotor
diffuser
compressor
discs
blades
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
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US00243371A
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English (en)
Inventor
J Fabri
J Friberg
R Siestrunck
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Alcatel CIT SA
Nokia Inc
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Nokia Inc
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Publication date
Application filed by Nokia Inc filed Critical Nokia Inc
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Publication of US3824029A publication Critical patent/US3824029A/en
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    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/288—Part of the wheel having an ejecting effect, e.g. being bladeless diffuser
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D21/00—Pump involving supersonic speed of pumped fluids

Definitions

  • This compressor comprises an axial input stator, a rotor provided with a rotating diffuser, and a fixed diffuser which is a volute extended by a nozzle rectilinear in section.
  • the rotating diffuser of the rotor consists of two coaxial discs connected together by radial blades, the radial dimensions of the blades and of the discs being such that the speed at the output of the diffuser rotating alone is slightly supersonic thereby obtaining a shock wave at the inlet of the nozzle.
  • FIGS 1 CENTRIFUGAL SUPERSONIC COMPRESSOR RELATED APPLICATIONS A claim of priority under 35 U.S.C. 119 is made based on French application filed Apr. 13, 1971 No. EN 71 12 891 (Seine).
  • This invention relates to a centrifugal supersonic compressor, particularly to one enabling a high pressure ratio between the outlet and the inlet of the machine to be obtained.
  • This invention provides a centrifugal supersonic compressor in which the friction of the gases against the wall of the stator is slight in relation to that of conventional centrifugal compressors so as to obtain improved efficiency.
  • the compressor according to the invention is, moreover, preferably intended for use in groups. It is desirable that the failure of a compressor in a group should not cause the stoppage of the other compressors of that group. Therefore, another aim of the invention is to produce a centrifugal supersonic compressor which can operate at a variable flow speed.
  • Another aim of the invention is to produce a compressor of the above defined type whose flow speed depends on a single parameter, which is consequently easy to determine.
  • Another aim of the invention is to produce a centrifugal supersonic compressor enabling a mach number having a high drive to be obtained, which can be used not only for the compression of heavy gases in which the speed of sound is relatively low, but also for the compression of air and other gases having relatively low density, being simply constructed and strong and having reliable operation and being free from surging.
  • the compressor in question comprises in combination, a rotor provided with a rotating diffuser, a stator having an axial inlet provided with a fixed diffuser mounted as an extension to the rotating diffuser in the direction of a gas flow which is to be compressed, the fixed diffuser consisting of a volute extended by a nozzle tangentially connected to the said volute, the said rotating diffuser consisting of two coaxial discs connected by radial blades, the radius of the discs being greater than that of the blades, characterized in that the mutual radial dimensions of the blades and of the discs are such that the speed at the outlet of the rotating diffuser is slightly supersonic, the nozzle which has a sonic inlet section being a rectilinear diverging nozzle causing a recompression shock wave in the flow of the fluid in the vicinity of the connection nose of the noule and of the volute.
  • the use, in a rotating compressor, of a fixed rectilinear diffuser is known, but in that known technique, diffusers of that type are partitioned, generally by a great number of blades; on the contrary, in the compressor according to the invention, the fixed diffuser, both in its portion in the shape of a volute as in its rectilinear portion, has a smooth wall.
  • FIG. 1 is a sectional view of a centrifugal compressor according to the invention along line Il of FIG. 2;
  • FIG. 2 is a horizontal sectional view along line II-II in FIG. 1;
  • FIG. 3 is a sectional view taken along line IIIIII of FIG. 4 and showing a modification
  • FIG. 4 is a cross-sectional view along line IV-IV of FIG. 3 of the modification.
  • FIG. 5 is a diagram showing the speed of the variation of the flow as a function of the compression ratio for an example of an embodiment of the compressor according to the invention.
  • the compressor comprises a stator 1 having an axial inlet 2.
  • a stator In this stator, is a rotor 3 mounted on a shaft 4, bearing, on the one hand, a front turbine 5 fitted with blades 5a and a drum 6 comprising two discs 7 and 8 connected together by a series of radial blades 9 defining, between them, rotating radial channels 9a.
  • These blades have a smaller radial length than those of the discs, so that an annular diffuser space 10 is arranged at the periphery of that rotor.
  • This rotating diffuser leads into a chamber having a spiral or volute shape 11 formed inside the stator, whose lateral walls are, either parallel or, as shown, slightly divergent.
  • This volute l1 constitutes a first portion of a fixed diffuser, which is connected to a second portion 12 of that fixed diffuser; this second portion consists of a rectilinear diverging nozzle whose inlet cross-section S, situated approximately at the connection nose between the volute' and the rectilinear nozzle, has a crosssection which is at least sonic, at the rated output of the machine.
  • the compression at that point is provided by a shock wave generated at the volute nose.
  • the rotor comprises, moreover, auxiliary blades such as 13 and 14, fixed respectively to the outside walls of the disc 7 and 8 and recessed partly in cavities l5 and 16 having an appropriate shape arranged in the inside wall of the stator.
  • This embodiment of the compressor operates as follows.
  • the fluid to be compressed enters through the axial inlet 2, and is driven by the front turbine 5 and enters the rotating channels 9a where it is subjected to centrifugal force which drives it out towards the rotating annular diffuser 10.
  • This fluid on leaving the channels 9a begins to slow down-with slight losses, the movement of the gas, in relation to the mobile walls which limit it, being appreciably subsonic.
  • the wakes behind the blades and the undisturbed gas currents coming from the mobile channels mix together and the kinetic energy imparted to the fluid by the blades 9 of the rotor begins to be transformed into pressure energy; the losses caused by that transformation,
  • the fixed diffuser 11, 12, which is not partitioned, fulfills the essential function of channeling the fluid leaving the rotating diffuser, this fluid still moving at high speed, and of recuperating that kinetic energy as much as possible.
  • the continuously varied shape of the lateral walls chosen for this diffuser enables energy losses to be avoided as much as possible.
  • the regulating of the flow can be determined'easily by the accurate choice of a single passage section S, whereas in partitioned diffuser compressors, the flow is limited by the sum of the minimum sections between the blades.
  • the single channel solution is particularly easy to implement, and experience shows that the absence of blades prevents the non-adherence of the fluid which constitutes a cause of instability at low output. Therefore a supersonic compressor of a new type, simple, having a high efficiency, and whose output can be predetermined accurately is thus obtained by combining a rotating diffuser and a fixed diffuser comprising a volute and a diverging nozzle. Experience shows that this machine is, moreover, free from surging.
  • the additional blades l3and l4 prevent leakages and enable a high compression ratio to be maintained.
  • a freon 114 compressor in which the sound propagation speed is, at 50 C, l30/Sec.
  • a pressure ratio of 8 with a peripheral speed equal to 230 m/sec. at the blade tips to be provided between the outlet and the inlet.
  • the efficiencyof the machine is improved due to the fact that, in the rotating diffuser, the tangential flow speed of the fluid is reduced to a level which is only slightly greater than mach l, the efficiency for that transformation being high, for example, in the order of 0.9.
  • the friction on the walls of the stator is lower than that which is found in conventional designs.
  • the use of the rotor diffuser makes it possible to avoid surging, and consequently enables a variable output and more particularly enables the operation of the compressor when one of the compressors of the group of compressors to which the compressor in question belongs ,breaks down.
  • FIG. 5 is an example of a curve obtained by means of a compressor according to the invention in a constant speed test; the flow speeds are marked in the abscissa, and the compression ratios P are marked in the ordinates.
  • the continuous portion of the line represents the normal operation zone of the compressor, in which the flow (DN) is practically independent from the compression ratio; this flow can therefore be considered as constant, and constitutes a characteristic of the machine.
  • the device in the form of a modification shown in FIGS. 3 and 4 comprising an ejector 21 in which the flowing gas, driven out by the volute at S, is used as a primary flow driving a recycling flow to be re-injected.
  • the device comprises a reinjection nozzle 22 which leads into the nose S of the rectilinear nozzle 12, the flow to be re-injected being brought to f, and being driven by the primary flow F leaving the volute and entering the nozzle.
  • a gas, or possibly two different gases can be sucked in through two inlets at different pressures, there being a single output. Different pressure ratios can therefore be obtained for the two gases f and F, for example 8 for the main flow F, 1.2 for secondary flow f.
  • a centrifugal compressor which is supersonic at rated output, said compressor comprising in combination:
  • a rotor mounted for rotation about its axis within said stator
  • said rotor being in the form of a drum and including spaced opposed discs whose similarly curved inner surfaces relative to each other define therebetween a gas flow path which changes from axial'to radial,
  • said discs having their periphery extending radially outward beyond the outboard edges of said blades to form disc extensions defining a rotary diffuser
  • stator including a fixed diffuser positioned as an extension to the rotary diffuser in a direction of a gas flow which is to be compressed,
  • said fixed diffuser comprising a vaneless volute circumferentially surrounding said rotor and a rectilinear diverging nozzle connected tangentially to said volute, said vaneless volute having a peripheral spiral wall of continuously increasing diameter leading to said nozzle, and said nozzle having a sonic inlet means at the end of said volute at rated compressor output,
  • auxiliary blades being received within said annular recesses to create dynamic seals therebetween and eliminate backflow of the pressurized fluid to the compressor inlet.
  • Compressor according to claim 1 in which the rotor includes a front turbine with a set of blades mounted on the upstream side of the rotating drum rotor and attached to the rotor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00243371A 1971-04-13 1972-04-12 Centrifugal supersonic compressor Expired - Lifetime US3824029A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7112891A FR2133195A5 (enrdf_load_stackoverflow) 1971-04-13 1971-04-13

Publications (1)

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US3824029A true US3824029A (en) 1974-07-16

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Application Number Title Priority Date Filing Date
US00243371A Expired - Lifetime US3824029A (en) 1971-04-13 1972-04-12 Centrifugal supersonic compressor

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US (1) US3824029A (enrdf_load_stackoverflow)
JP (1) JPS5750950B2 (enrdf_load_stackoverflow)
BE (1) BE781721A (enrdf_load_stackoverflow)
CA (1) CA966104A (enrdf_load_stackoverflow)
DE (1) DE7213730U (enrdf_load_stackoverflow)
FR (1) FR2133195A5 (enrdf_load_stackoverflow)
GB (1) GB1382108A (enrdf_load_stackoverflow)
IT (1) IT954645B (enrdf_load_stackoverflow)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4479755A (en) * 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
US4547123A (en) * 1979-10-29 1985-10-15 Tokyo Shibaura Denki Kabushiki Kaisha Multi-stage hydraulic machine and method of operating same
US4613281A (en) * 1984-03-08 1986-09-23 Goulds Pumps, Incorporated Hydrodynamic seal
US4886417A (en) * 1988-12-06 1989-12-12 Sundstrand Corporation Fuel pump and radial-flow impeller therefor
US4917571A (en) * 1984-03-20 1990-04-17 John Hyll Flow-stabilizing volute pump and liner
US5046919A (en) * 1989-07-17 1991-09-10 Union Carbide Industrial Gases Technology Corporation High efficiency turboexpander
US5127800A (en) * 1984-03-20 1992-07-07 Baker Hughes Incorporated Flow-stabilizing volute pump and liner
US5277232A (en) * 1992-04-21 1994-01-11 Borsheim Lewis A Positive discharge contaminant evacuator
US5793395A (en) * 1992-02-26 1998-08-11 Canon Kabushiki Kaisha Ink supply device and ink jet recording apparatus using said device
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US6953321B2 (en) 2002-12-31 2005-10-11 Weir Slurry Group, Inc. Centrifugal pump with configured volute
US20050271500A1 (en) * 2002-09-26 2005-12-08 Ramgen Power Systems, Inc. Supersonic gas compressor
US20060021353A1 (en) * 2002-09-26 2006-02-02 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
US20060034691A1 (en) * 2002-01-29 2006-02-16 Ramgen Power Systems, Inc. Supersonic compressor
US20060093477A1 (en) * 2004-11-03 2006-05-04 Jones Daniel W Centrifugal compressor having rotatable compressor case insert
US20060275113A1 (en) * 2002-08-13 2006-12-07 Hua Chen Compressor
US20110083420A1 (en) * 2008-03-25 2011-04-14 Clay Rufus G Subsonic and Stationary Ramjet Engines
EP2439414A3 (en) * 2010-10-08 2015-02-18 General Electric Company Supersonic compressor startup support system
US20150086371A1 (en) * 2012-05-23 2015-03-26 Entsorgafin S.P.A. Impeller for a Ventilation Unit and Ventilation Unit Comprising said Impeller
US20160281741A1 (en) * 2015-03-27 2016-09-29 Dresser-Rand Company Heat shield for pressure casing
US20170022999A1 (en) * 2015-03-27 2017-01-26 Dresser-Rand Company Electrically heated balance piston seal
CN106640768A (zh) * 2016-10-18 2017-05-10 美的集团股份有限公司 离心风机和具有其的吸尘器
CN112824685A (zh) * 2019-11-21 2021-05-21 泛仕达机电股份有限公司 一种带有提效装置的离心叶轮
US11053951B2 (en) * 2015-05-15 2021-07-06 Nuovo Pignone Srl Centrifugal compressor impeller and compressor comprising said impeller
CN114876865A (zh) * 2022-06-07 2022-08-09 上海齐耀动力技术有限公司 一种超临界二氧化碳压缩机叶轮封严结构及压缩机
US12066027B2 (en) 2022-08-11 2024-08-20 Next Gen Compression Llc Variable geometry supersonic compressor

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS53123607U (enrdf_load_stackoverflow) * 1977-03-09 1978-10-02
US4212595A (en) * 1978-10-04 1980-07-15 Avco Corporation Air pump with primary and secondary inlet flow channels
JPS583648A (ja) * 1981-06-30 1983-01-10 のむら産業株式会社 穀類の吸引による乾燥方法
GB2118295B (en) * 1982-04-05 1985-09-18 Hatch Ass Ltd Vortical fluid withdrawal
GB2444939A (en) * 2006-12-22 2008-06-25 Dyson Technology Ltd A shaped member for an impeller rotor assembly
DE102013207220B3 (de) * 2013-04-22 2014-09-18 Siemens Aktiengesellschaft Turbomaschine
CN113685365B (zh) * 2021-10-25 2022-01-18 宁波佳音机电科技股份有限公司 一种抽气泵

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US1237007A (en) * 1916-06-01 1917-08-14 Alfred Wilstam Centrifugal pump.
US1670065A (en) * 1926-05-08 1928-05-15 Gen Electric Centrifugal pump and compressor
US2390504A (en) * 1943-10-20 1945-12-11 Adolph L Berger Centrifugal air compressor
DE809758C (de) * 1949-03-29 1951-08-02 Walter Moehle Zentrifugalpumpe
FR1055017A (fr) * 1952-04-18 1954-02-16 Neu Sa Compresseur centrifuge
GB733533A (en) * 1952-08-26 1955-07-13 Establissements Neu Sa Des Improvements in or relating to centrifugal blowers, compressors, pumps and the like
US2786261A (en) * 1952-10-28 1957-03-26 Garrett Corp Method of forming passage structure
US2845216A (en) * 1952-11-15 1958-07-29 Neu Sa Centrifugal apparatus for the circulation of fluids
FR1188110A (fr) * 1957-12-04 1959-09-18 Snecma Compresseur centrifuge supersonique
US2962206A (en) * 1953-09-11 1960-11-29 Chrysler Corp Centrifugal compressor for a gas turbine engine
FR1294817A (fr) * 1961-04-18 1962-06-01 Compresseur centrifuge supersonique ou non
FR1313594A (fr) * 1962-02-05 1962-12-28 Neu Sa Perfectionnement aux appareils centrifuges pour la circulation des fluides
US3099221A (en) * 1960-03-23 1963-07-30 Earl A Thompson Centrifugal pump
US3460748A (en) * 1967-11-01 1969-08-12 Gen Electric Radial flow machine
DE1428169A1 (de) * 1963-03-18 1970-01-15 Gutchoffnungshuette Sterkrade Radialverdichter mit Laufrad und Umlauf-Diffusor
US3647314A (en) * 1970-04-08 1972-03-07 Gen Electric Centrifugal pump
US3658437A (en) * 1970-03-27 1972-04-25 Caterpillar Tractor Co Diffuser including vaneless and vaned sections
US3692426A (en) * 1970-03-31 1972-09-19 Weir Pumps Ltd Fluid machines
US3759627A (en) * 1972-02-14 1973-09-18 Allis Chalmers Compressor assembly

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US704756A (en) * 1901-08-03 1902-07-15 James Spiers Jr Centrifugal-pump runner.
US1237007A (en) * 1916-06-01 1917-08-14 Alfred Wilstam Centrifugal pump.
US1670065A (en) * 1926-05-08 1928-05-15 Gen Electric Centrifugal pump and compressor
US2390504A (en) * 1943-10-20 1945-12-11 Adolph L Berger Centrifugal air compressor
DE809758C (de) * 1949-03-29 1951-08-02 Walter Moehle Zentrifugalpumpe
FR1055017A (fr) * 1952-04-18 1954-02-16 Neu Sa Compresseur centrifuge
GB733533A (en) * 1952-08-26 1955-07-13 Establissements Neu Sa Des Improvements in or relating to centrifugal blowers, compressors, pumps and the like
US2786261A (en) * 1952-10-28 1957-03-26 Garrett Corp Method of forming passage structure
US2845216A (en) * 1952-11-15 1958-07-29 Neu Sa Centrifugal apparatus for the circulation of fluids
US2962206A (en) * 1953-09-11 1960-11-29 Chrysler Corp Centrifugal compressor for a gas turbine engine
FR1188110A (fr) * 1957-12-04 1959-09-18 Snecma Compresseur centrifuge supersonique
US3099221A (en) * 1960-03-23 1963-07-30 Earl A Thompson Centrifugal pump
FR1294817A (fr) * 1961-04-18 1962-06-01 Compresseur centrifuge supersonique ou non
FR1313594A (fr) * 1962-02-05 1962-12-28 Neu Sa Perfectionnement aux appareils centrifuges pour la circulation des fluides
DE1428169A1 (de) * 1963-03-18 1970-01-15 Gutchoffnungshuette Sterkrade Radialverdichter mit Laufrad und Umlauf-Diffusor
US3460748A (en) * 1967-11-01 1969-08-12 Gen Electric Radial flow machine
US3658437A (en) * 1970-03-27 1972-04-25 Caterpillar Tractor Co Diffuser including vaneless and vaned sections
US3692426A (en) * 1970-03-31 1972-09-19 Weir Pumps Ltd Fluid machines
US3647314A (en) * 1970-04-08 1972-03-07 Gen Electric Centrifugal pump
US3759627A (en) * 1972-02-14 1973-09-18 Allis Chalmers Compressor assembly

Cited By (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4547123A (en) * 1979-10-29 1985-10-15 Tokyo Shibaura Denki Kabushiki Kaisha Multi-stage hydraulic machine and method of operating same
US4479755A (en) * 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
US4613281A (en) * 1984-03-08 1986-09-23 Goulds Pumps, Incorporated Hydrodynamic seal
US5127800A (en) * 1984-03-20 1992-07-07 Baker Hughes Incorporated Flow-stabilizing volute pump and liner
US4917571A (en) * 1984-03-20 1990-04-17 John Hyll Flow-stabilizing volute pump and liner
US4886417A (en) * 1988-12-06 1989-12-12 Sundstrand Corporation Fuel pump and radial-flow impeller therefor
US5046919A (en) * 1989-07-17 1991-09-10 Union Carbide Industrial Gases Technology Corporation High efficiency turboexpander
US5793395A (en) * 1992-02-26 1998-08-11 Canon Kabushiki Kaisha Ink supply device and ink jet recording apparatus using said device
US5277232A (en) * 1992-04-21 1994-01-11 Borsheim Lewis A Positive discharge contaminant evacuator
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US7334990B2 (en) 2002-01-29 2008-02-26 Ramgen Power Systems, Inc. Supersonic compressor
US20060034691A1 (en) * 2002-01-29 2006-02-16 Ramgen Power Systems, Inc. Supersonic compressor
US8550775B2 (en) * 2002-08-13 2013-10-08 Honeywell International Inc. Compressor
US20060275113A1 (en) * 2002-08-13 2006-12-07 Hua Chen Compressor
US7293955B2 (en) 2002-09-26 2007-11-13 Ramgen Power Systrms, Inc. Supersonic gas compressor
US20060021353A1 (en) * 2002-09-26 2006-02-02 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
US20050271500A1 (en) * 2002-09-26 2005-12-08 Ramgen Power Systems, Inc. Supersonic gas compressor
US7434400B2 (en) 2002-09-26 2008-10-14 Lawlor Shawn P Gas turbine power plant with supersonic shock compression ramps
US6953321B2 (en) 2002-12-31 2005-10-11 Weir Slurry Group, Inc. Centrifugal pump with configured volute
WO2006052586A3 (en) * 2004-11-03 2006-11-23 Accessible Technologies Inc Centrifugal compressor having rotatable compressor case insert
US20060093477A1 (en) * 2004-11-03 2006-05-04 Jones Daniel W Centrifugal compressor having rotatable compressor case insert
US7189052B2 (en) * 2004-11-03 2007-03-13 Accessible Technologies, Inc. Centrifugal compressor having rotatable compressor case insert
US20110083420A1 (en) * 2008-03-25 2011-04-14 Clay Rufus G Subsonic and Stationary Ramjet Engines
US9022730B2 (en) 2010-10-08 2015-05-05 General Electric Company Supersonic compressor startup support system
EP2439414A3 (en) * 2010-10-08 2015-02-18 General Electric Company Supersonic compressor startup support system
US9683582B2 (en) * 2012-05-23 2017-06-20 Entsorgafin S.P.A. Impeller for a ventilation unit and ventilation unit comprising said impeller
US20150086371A1 (en) * 2012-05-23 2015-03-26 Entsorgafin S.P.A. Impeller for a Ventilation Unit and Ventilation Unit Comprising said Impeller
US10208768B2 (en) * 2015-03-27 2019-02-19 Dresser-Rand Company Heat shield for pressure casing
US20170022999A1 (en) * 2015-03-27 2017-01-26 Dresser-Rand Company Electrically heated balance piston seal
US20160281741A1 (en) * 2015-03-27 2016-09-29 Dresser-Rand Company Heat shield for pressure casing
US10584709B2 (en) * 2015-03-27 2020-03-10 Dresser-Rand Company Electrically heated balance piston seal
US11053951B2 (en) * 2015-05-15 2021-07-06 Nuovo Pignone Srl Centrifugal compressor impeller and compressor comprising said impeller
CN106640768A (zh) * 2016-10-18 2017-05-10 美的集团股份有限公司 离心风机和具有其的吸尘器
CN112824685A (zh) * 2019-11-21 2021-05-21 泛仕达机电股份有限公司 一种带有提效装置的离心叶轮
CN112824685B (zh) * 2019-11-21 2022-08-09 泛仕达机电股份有限公司 一种带有提效装置的离心叶轮
CN114876865A (zh) * 2022-06-07 2022-08-09 上海齐耀动力技术有限公司 一种超临界二氧化碳压缩机叶轮封严结构及压缩机
US12066027B2 (en) 2022-08-11 2024-08-20 Next Gen Compression Llc Variable geometry supersonic compressor
US12338829B2 (en) 2022-08-11 2025-06-24 Next Gen Compression Llc Variable geometry supersonic compressor

Also Published As

Publication number Publication date
FR2133195A5 (enrdf_load_stackoverflow) 1972-11-24
JPS4736107A (enrdf_load_stackoverflow) 1972-11-28
BE781721A (fr) 1972-07-31
JPS5750950B2 (enrdf_load_stackoverflow) 1982-10-29
CA966104A (en) 1975-04-15
DE7213730U (de) 1972-08-10
GB1382108A (en) 1975-01-29
IT954645B (it) 1973-09-15

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