US3588270A - Diffuser for a centrifugal fluid-flow turbomachine - Google Patents

Diffuser for a centrifugal fluid-flow turbomachine Download PDF

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Publication number
US3588270A
US3588270A US844000A US3588270DA US3588270A US 3588270 A US3588270 A US 3588270A US 844000 A US844000 A US 844000A US 3588270D A US3588270D A US 3588270DA US 3588270 A US3588270 A US 3588270A
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United States
Prior art keywords
vanes
row
diffuser
rows
axes
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Expired - Lifetime
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US844000A
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English (en)
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Albin Boelcs
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Sulzer Escher Wyss AG
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Escher Wyss AG
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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
    • F04D29/40—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
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • a centrifugal fluid-flow turbomachine has a diffuser provided with two coaxially arranged rows of rotatable guide vanes through which the fluid flows in succession. The pivot axes of the vanes of said two rows are displaceable in relation to one another in the circumferential direction of the TOWS.
  • Diffusers which are provided with guide vanes and are arranged downstream of the impeller in centrifugal fluid-flow turbomachines such as compressors or pumps, are intended to decelerate the flowing medium issuing at high speed from the impeller and thus to convert the kinetic energy contained in the said medium into pressure energy.
  • centrifugal fluid-flow turbomachines such as compressors or pumps
  • a known measure for reducing the risk of flow separation and tee flow losses occurring in the diffuser, and for increasing the pressure production possible in the diffuser consists in that the slowing-down of the flow is shared by two coaxial cir cular rows of vanes through which the fluid flows in succession. If it is ensured that the undisturbed portion of the flow issuing from the first row of vanes flows on to the vanes of the second row, there forms at the vanes of the second vane lattice a new boundary layer which can then be capable of accompanying the further pressure increase without flow separation.
  • the choice of the positions of the two rows of vanes relatively to one another is of essential importance for the satisfactory operation of the diffuser.
  • the diffuser To adapt the diffuser to varying operating conditions of the machine, it is also known to provide the diffuser with rotatable guide vanes. If this measure is applied to a diffuser having two rows of vanes through which the fluid flows in succession, on rotation of the guide vanes the direction of the flow issuing from the first row of vanes will be varied. The guide vanes of the second row, therefore, can get into a substantially more unfavorable position then before with regard to the boundary layers starting from the vanes of the first row. The sharing of pressure production by two rows of vanes in this case no longer affords any advantage, and the efficiency of the diffuser is made worse. The adaptability of the diffuser to varying operating conditions, which is aimed at by making the guide vanes rotatable, is thus achieved only to a limited extent.
  • the invention has for its aim to provide an improvement in this respect.
  • a diffuser arranged in a centrifugal fluid-flow turbomachine and having two coaxial circular rows of rotatable guide vanes through which the fluid flows in succession, for this purpose the pivoting axes of the vanes of one row of vanes are displaceable relatively to the pivoting axes of the vanes of the other row of vanes in the peripheral direction thereof.
  • the adjusting mechanism for the relative displacement of the pivoting axes of the vanes is connected with the adjusting mechanism for the rotation of the vanes of at least one vane row about their axes for establishing a definite relationship between the pivoting of the vanes and the relative displacement of the axes.
  • FIG. la shows a partial sectional view at right angles to the machine axis through the two rows of vanes
  • FIG. lb shows a corresponding partial sectional view with the vanes pivoted relatively to the position shown in FIG. la and the rows of vanes displaced relatively to one another in the peripheral direction;
  • FIG. 2 shows an axial longitudinal sectional view through the machine in the region of the adjusting mechanism for the diffuser vane system and FIGS. 3aand 3b each show a section taken on the line III-III of FIG. 2, in the positions of the diffuser vanes shown in FIGS. la and 1b respectively.
  • the diffuser has two circular rows of guide vanes which are arranged coaxially relatively to one another and through which the fluid flows in succession, namely an inner row 1 of vanes 4 and an outer row 2 of an identical number of vanes 7.
  • the fluid issuing from the impeller 3 of a centrifugal compressor, said impeller rotating in the arrowed direction, arrives at the inner row 1 of the vanes 4 directly.
  • the vanes 4 are pivotable about axes 6 which are parallel to the machine axis and are arranged uniformly distributed over a circle concentric therewith.
  • the fluid issuing from the row 1 of the vanes 4 passes into the row 2 of the vanes 7, which are likewise pivotable and whose pivoting axes are arranged on a circle 8 and designated as 9.
  • the position of the vanes 4 and 7 of the diffuser shown in FIG. la is intended for an operating condition with a relatively considerable delivery quantity.
  • the vanes 4 of the row 1 are so arranged in relation to the vanes 7 of the row 2 that their inlet edges are contacted by a flow line which passes approximately centrally between two vanes 4 of the row 1.
  • the vanes 7 are thus acted upon by a part of the fluid which is off the region of the boundary layers forming ,at the vanes 4 of the row 1.
  • a new boundary layer forms at the vanes 7 which is capable of accompanying the further pressure increase aimed at in the row of vanes 2 without becoming subjected to flow separation.
  • the vanes 4 and 7 of the rows 1 and 2, respectively are set at a shallower angle a, and a relatively to the peripheral direction as compared with the position in FIG. la. If this pivoting of the guide vanes 4 and 7 were effected with the positions of the axes 6 and 9 unchanged, there would soon be a state wherein the flow line emanating from the outlet edge of a vane 4 would impinge on the inlet edge of the next vane 7 in succession of the row 2. Thus low-energy portions of the boundary layer of the vanes 4 would arrive at the vanes 7 and be further retarded at their surface. Separation of the boundary layer would then be expected soon.
  • the row 1 of the vanes 4 can be rotated relatively to the row 2 of the vanes 7 in their entirety about the compressor axis.
  • the pivoting axes 6 of the vanes 4 of the row 1 are displaceable relatively to the pivoting axes 9 of the vanes 7 of the row 2 in the peripheral direction thereof.
  • FIG. lb shows, by displacing the axes 6 by an amount a relatively to the original position in the peripheral direction, the result is achieved that even with the vane angles shown in FIG. lb the vanes 7 are not impinged upon by the boundary layer material emanating from the vanes 4 of the row 1.
  • the measure described makes it possible to bring the vanes of the two rows 1 and 2 into the most advantageous position relatively to one another in every operating condition.
  • FIGS. 2, 3a and 3b show with what constructional means the aforesaid displaceability of the pivoting axes of the vanes of one row can be achieved relatively to the pivoting axes of the vanes of the other row, by way of example.
  • the vanes 4 of the inner row 1 are provided with pivot pins 12 which are inserted in an annular vane carrier, namely a disc 13 rotatable about the machine axis, and whose axes form the axes of rotation 6 for the vanes 4.
  • the varies 7 of the outer row 2 have pivot pins 14 which are arranged in a ring 15 connected fast to the housing 10 and the axe-s of which form the pivoting axes 9 for the vanes 7.
  • the pivot pins 12 and 14 are provided with adjusting levers 20 and 21 respectively, the outer ends of which, owing to the action of torsion springs 22 and 23 respectively, are always pressed against surfaces of revolution 24 and 25 formed by the member 19 and serving as guide ways for the levers 20, 21.
  • FIGS. 3a and 3b the position of the adjusting levers 20 and 21 is shown for the varying positions of the member 19 according to FIG. 2.
  • a centrifugal fluid-flow turbomachine having a housing with an impeller rotatably mounted therein for inducing radial fluid flow therethrough, said housing defining an annular discharge passage for the fluid leaving said impeller with an outward flow component: a diffuser vane system arranged in said discharge passage for the deceleration of the discharging fluid, comprising two coaxial circular rows of spaced rotatable vanes having respective pivot axes, namely an inner row and an outer row through which rows the fluid flows in succession in the order stated; and actuating means to displace the pivot axes of the vanes of one row relatively to the pivot axes of the vanes of the other row in the circumferential direction of said rows.
  • said means for establishing a definite relationship between said pivoting movements and said relative displacement comprise an annular member arranged coaxially with the machine axis and axially displaceable, said member having guide ways as surfaces of revolution and the pivots of the vanes having levers guided by said guide ways, spring means being provided for pressing said levers against said guide ways; and screw means disposed to cause said annular member to displace axially on relative circumferential displacement of the pivots of the vanes of said two rows.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US844000A 1968-08-20 1969-07-23 Diffuser for a centrifugal fluid-flow turbomachine Expired - Lifetime US3588270A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1248668A CH486636A (de) 1968-08-20 1968-08-20 Diffusor einer Zentrifugalfördermaschine

Publications (1)

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US3588270A true US3588270A (en) 1971-06-28

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US844000A Expired - Lifetime US3588270A (en) 1968-08-20 1969-07-23 Diffuser for a centrifugal fluid-flow turbomachine

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US (1) US3588270A (enExample)
CH (1) CH486636A (enExample)
DE (1) DE6928037U (enExample)
FR (1) FR2015956A1 (enExample)
GB (1) GB1270330A (enExample)
NL (1) NL6911420A (enExample)

Cited By (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3799694A (en) * 1972-11-20 1974-03-26 Gen Motors Corp Variable diffuser
US3816021A (en) * 1971-12-11 1974-06-11 Lucas Aerospace Ltd Control vane arrangement for a gas turbine engine
US3957392A (en) * 1974-11-01 1976-05-18 Caterpillar Tractor Co. Self-aligning vanes for a turbomachine
US3972644A (en) * 1975-01-27 1976-08-03 Caterpillar Tractor Co. Vane control arrangement for variable area turbine nozzle
US3992128A (en) * 1975-06-09 1976-11-16 General Motors Corporation Variable diffuser
US4378194A (en) * 1980-10-02 1983-03-29 Carrier Corporation Centrifugal compressor
US4428714A (en) 1981-08-18 1984-01-31 A/S Kongsberg Vapenfabrikk Pre-swirl inlet guide vanes for compressor
US4558987A (en) * 1980-07-08 1985-12-17 Mannesmann Aktiengesellschaft Apparatus for regulating axial compressors
USRE32756E (en) * 1981-08-18 1988-09-27 A/S Kongsberg Vapenfabrikk Pre-swirl inlet guide vane for compressor
US4824325A (en) * 1988-02-08 1989-04-25 Dresser-Rand Company Diffuser having split tandem low solidity vanes
DE3835622A1 (de) * 1987-10-19 1989-05-03 Sundstrand Corp Radialverdichter
US4850795A (en) * 1988-02-08 1989-07-25 Dresser-Rand Company Diffuser having ribbed vanes followed by full vanes
US4874287A (en) * 1986-02-28 1989-10-17 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Variable-geometry turbocompressor
US4874289A (en) * 1988-05-26 1989-10-17 United States Of America As Represented By The Secretary Of The Air Force Variable stator vane assembly for a rotary turbine engine
US4877369A (en) * 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser control
US4877370A (en) * 1987-09-01 1989-10-31 Hitachi, Ltd. Diffuser for centrifugal compressor
US4877373A (en) * 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser with small straightening vanes
US4902200A (en) * 1988-04-25 1990-02-20 Dresser-Rand Company Variable diffuser wall with ribbed vanes
US4932835A (en) * 1989-04-04 1990-06-12 Dresser-Rand Company Variable vane height diffuser
US5152661A (en) * 1988-05-27 1992-10-06 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
US5207559A (en) * 1991-07-25 1993-05-04 Allied-Signal Inc. Variable geometry diffuser assembly
US5347401A (en) * 1989-06-07 1994-09-13 Hermann Hugenell Reflecting telescope and its production process
US5417547A (en) * 1992-12-25 1995-05-23 Ebara Corporation Vaned diffuser for centrifugal and mixed flow pumps
US5730580A (en) * 1995-03-24 1998-03-24 Concepts Eti, Inc. Turbomachines having rogue vanes
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US20040238691A1 (en) * 2003-05-28 2004-12-02 Harold Hipsky Compressor for use in aircraft fuel tank air purge system
US20050141988A1 (en) * 2003-12-30 2005-06-30 Acoustiflo, Ltd. Centrifugal fan diffuser
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
US20080050228A1 (en) * 2006-08-25 2008-02-28 Industrial Technology Research Institute Impeller Structure and the Centrifugal Fan Device Using the Same
US20100129204A1 (en) * 2006-10-30 2010-05-27 Hirotaka Higashimori Variable diffuser and compressor
US20110250047A1 (en) * 2010-04-08 2011-10-13 International Business Machines Corporation Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower
US20110250048A1 (en) * 2010-04-08 2011-10-13 International Business Machines Corporation Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower
WO2011128587A1 (fr) * 2010-04-14 2011-10-20 Turbomeca Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre
US20110305556A1 (en) * 2010-05-24 2011-12-15 Antonio Asti Methods and systems for variable geometry inlets nozzles for use in turboexpanders
EP2626573A1 (en) * 2012-02-09 2013-08-14 Lg Electronics Inc. Centrifugal compressor
US20130205795A1 (en) * 2012-02-09 2013-08-15 General Electric Company Turbomachine flow improvement system
US8641361B2 (en) 2010-04-08 2014-02-04 International Business Machines Corporation Airflow from a blower with one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower
US20140086725A1 (en) * 2011-08-15 2014-03-27 Wuxi Kaidi Supercharger Accessories Co., Ltd. Turbocharger with a double-vane nozzle system
US20190345838A1 (en) * 2018-05-11 2019-11-14 Rolls-Royce Corporation Variable diffuser having a respective penny for each vane
US11280212B2 (en) * 2019-01-24 2022-03-22 MTU Aero Engines AG Guide vane cascade for a turbomachine
US11401947B2 (en) * 2020-10-30 2022-08-02 Praxair Technology, Inc. Hydrogen centrifugal compressor
WO2024166963A1 (ja) * 2023-02-10 2024-08-15 株式会社Ihi 回転機械および過給機
US12066027B2 (en) 2022-08-11 2024-08-20 Next Gen Compression Llc Variable geometry supersonic compressor
KR102785454B1 (ko) * 2024-08-09 2025-03-25 (주)대주기계 균일한 압력분포를 유도하는 원심압축기의 베인 디퓨저
KR20250092418A (ko) * 2023-12-15 2025-06-24 (주)대주기계 원심압축기의 분할형 베인 디퓨저
US12460651B2 (en) 2022-08-11 2025-11-04 Next Gen Compression Llc Method for efficient part load compressor operation

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5677598A (en) * 1979-11-30 1981-06-25 Nissan Motor Co Ltd Variable-position diffuser for centrifugal compressor
RU2173797C2 (ru) * 1996-06-07 2001-09-20 Кэрриер Корпорейшн Центробежный компрессор
RU2395726C1 (ru) * 2009-03-23 2010-07-27 Общество с ограниченной ответственностью "Научно-производственная фирма "АЭРОМЕХ" (ООО "НПФ "АЭРОМЕХ") Центробежный вентилятор с регулятором мощности воздушного потока ("корона" в.с. сухина)
FR3025564B1 (fr) * 2014-09-04 2019-08-16 Safran Aircraft Engines Systeme d'aubes a calage variable pour une turbomachine

Cited By (66)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3816021A (en) * 1971-12-11 1974-06-11 Lucas Aerospace Ltd Control vane arrangement for a gas turbine engine
US3799694A (en) * 1972-11-20 1974-03-26 Gen Motors Corp Variable diffuser
US3957392A (en) * 1974-11-01 1976-05-18 Caterpillar Tractor Co. Self-aligning vanes for a turbomachine
US3972644A (en) * 1975-01-27 1976-08-03 Caterpillar Tractor Co. Vane control arrangement for variable area turbine nozzle
US3992128A (en) * 1975-06-09 1976-11-16 General Motors Corporation Variable diffuser
US4558987A (en) * 1980-07-08 1985-12-17 Mannesmann Aktiengesellschaft Apparatus for regulating axial compressors
US4378194A (en) * 1980-10-02 1983-03-29 Carrier Corporation Centrifugal compressor
US4428714A (en) 1981-08-18 1984-01-31 A/S Kongsberg Vapenfabrikk Pre-swirl inlet guide vanes for compressor
USRE32756E (en) * 1981-08-18 1988-09-27 A/S Kongsberg Vapenfabrikk Pre-swirl inlet guide vane for compressor
US4874287A (en) * 1986-02-28 1989-10-17 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Variable-geometry turbocompressor
US4877370A (en) * 1987-09-01 1989-10-31 Hitachi, Ltd. Diffuser for centrifugal compressor
US4859145A (en) * 1987-10-19 1989-08-22 Sundstrand Corporation Compressor with supercritical diffuser
DE3835622A1 (de) * 1987-10-19 1989-05-03 Sundstrand Corp Radialverdichter
US4877369A (en) * 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser control
US4850795A (en) * 1988-02-08 1989-07-25 Dresser-Rand Company Diffuser having ribbed vanes followed by full vanes
US4877373A (en) * 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser with small straightening vanes
US4824325A (en) * 1988-02-08 1989-04-25 Dresser-Rand Company Diffuser having split tandem low solidity vanes
US4902200A (en) * 1988-04-25 1990-02-20 Dresser-Rand Company Variable diffuser wall with ribbed vanes
US4874289A (en) * 1988-05-26 1989-10-17 United States Of America As Represented By The Secretary Of The Air Force Variable stator vane assembly for a rotary turbine engine
US5152661A (en) * 1988-05-27 1992-10-06 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
US4932835A (en) * 1989-04-04 1990-06-12 Dresser-Rand Company Variable vane height diffuser
US5347401A (en) * 1989-06-07 1994-09-13 Hermann Hugenell Reflecting telescope and its production process
US5207559A (en) * 1991-07-25 1993-05-04 Allied-Signal Inc. Variable geometry diffuser assembly
US5417547A (en) * 1992-12-25 1995-05-23 Ebara Corporation Vaned diffuser for centrifugal and mixed flow pumps
US5730580A (en) * 1995-03-24 1998-03-24 Concepts Eti, Inc. Turbomachines having rogue vanes
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
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
US20040238691A1 (en) * 2003-05-28 2004-12-02 Harold Hipsky Compressor for use in aircraft fuel tank air purge system
US7001140B2 (en) 2003-12-30 2006-02-21 Acoustiflo, Ltd. Centrifugal fan diffuser
US7357621B2 (en) 2003-12-30 2008-04-15 Acoustiflo, Llc Centrifugal fan diffuser
US20050141988A1 (en) * 2003-12-30 2005-06-30 Acoustiflo, Ltd. Centrifugal fan diffuser
US20060153671A1 (en) * 2003-12-30 2006-07-13 Acoustiflo, Ltd. Centrifugal fan diffuser
US20080050228A1 (en) * 2006-08-25 2008-02-28 Industrial Technology Research Institute Impeller Structure and the Centrifugal Fan Device Using the Same
US20100129204A1 (en) * 2006-10-30 2010-05-27 Hirotaka Higashimori Variable diffuser and compressor
US8591167B2 (en) * 2010-04-08 2013-11-26 International Business Machines Corporation Airflow from a blower with one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower
US20110250047A1 (en) * 2010-04-08 2011-10-13 International Business Machines Corporation Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower
US20110250048A1 (en) * 2010-04-08 2011-10-13 International Business Machines Corporation Airflow From A Blower With One Or More Adjustable Guide Vanes That Are Affixed To The Blower At One Or More Pivot Points Located In An Outlet Of The Blower
US8657558B2 (en) * 2010-04-08 2014-02-25 International Business Machines Corporation Airflow from a blower with one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower
US8641361B2 (en) 2010-04-08 2014-02-04 International Business Machines Corporation Airflow from a blower with one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower
FR2958967A1 (fr) * 2010-04-14 2011-10-21 Turbomeca Procede d'adaptation de debit d'air de turbomachine a compresseur centrifuge et diffuseur de mise en oeuvre
EP2558728B1 (fr) 2010-04-14 2019-07-24 Safran Helicopter Engines Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre
JP2013524099A (ja) * 2010-04-14 2013-06-17 ターボメカ 遠心圧縮機を有するタービンエンジンの空気流を適合するための方法およびその実施のためのディフューザ
CN102834622B (zh) * 2010-04-14 2016-02-10 涡轮梅坎公司 涡轮发动机离心压缩机内气流的调整方法和实施所述方法的扩散器
CN102834622A (zh) * 2010-04-14 2012-12-19 涡轮梅坎公司 涡轮发动机离心压缩机内气流的调整方法和实施所述方法的扩散器
RU2564158C2 (ru) * 2010-04-14 2015-09-27 Турбомека Способ регулирования расхода воздуха в центробежном компрессоре турбомашины и диффузор для его осуществления
WO2011128587A1 (fr) * 2010-04-14 2011-10-20 Turbomeca Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre
US8882438B2 (en) * 2010-05-24 2014-11-11 Nuovo Pignone S.P.A. Methods and systems for variable geometry inlets nozzles for use in turboexpanders
US20110305556A1 (en) * 2010-05-24 2011-12-15 Antonio Asti Methods and systems for variable geometry inlets nozzles for use in turboexpanders
US20140086725A1 (en) * 2011-08-15 2014-03-27 Wuxi Kaidi Supercharger Accessories Co., Ltd. Turbocharger with a double-vane nozzle system
US20130205795A1 (en) * 2012-02-09 2013-08-15 General Electric Company Turbomachine flow improvement system
EP2626573A1 (en) * 2012-02-09 2013-08-14 Lg Electronics Inc. Centrifugal compressor
US10883379B2 (en) * 2018-05-11 2021-01-05 Rolls-Royce Corporation Variable diffuser having a respective penny for each vane
US20190345838A1 (en) * 2018-05-11 2019-11-14 Rolls-Royce Corporation Variable diffuser having a respective penny for each vane
US11280212B2 (en) * 2019-01-24 2022-03-22 MTU Aero Engines AG Guide vane cascade for a turbomachine
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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
US12460651B2 (en) 2022-08-11 2025-11-04 Next Gen Compression Llc Method for efficient part load compressor operation
WO2024166963A1 (ja) * 2023-02-10 2024-08-15 株式会社Ihi 回転機械および過給機
KR20250092418A (ko) * 2023-12-15 2025-06-24 (주)대주기계 원심압축기의 분할형 베인 디퓨저
KR102785454B1 (ko) * 2024-08-09 2025-03-25 (주)대주기계 균일한 압력분포를 유도하는 원심압축기의 베인 디퓨저

Also Published As

Publication number Publication date
FR2015956A1 (enExample) 1970-04-30
DE6928037U (de) 1970-11-19
CH486636A (de) 1970-02-28
NL6911420A (enExample) 1970-02-24
GB1270330A (en) 1972-04-12

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