US3365120A - Turbine radial diffuser - Google Patents

Turbine radial diffuser Download PDF

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Publication number
US3365120A
US3365120A US454585A US45458565A US3365120A US 3365120 A US3365120 A US 3365120A US 454585 A US454585 A US 454585A US 45458565 A US45458565 A US 45458565A US 3365120 A US3365120 A US 3365120A
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US
United States
Prior art keywords
diffuser
compressor
wall
space
spaces
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
Application number
US454585A
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English (en)
Inventor
Jassniker Kurt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sulzer AG
Original Assignee
Sulzer AG
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 Sulzer AG filed Critical Sulzer AG
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Publication of US3365120A publication Critical patent/US3365120A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial 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
    • 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
    • F04D29/464—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps adjusting flow cross-section, otherwise than by using adjustable stator blades
    • 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

Definitions

  • This wall remote from the diffuser space is divided into two parts by an annular partition. These two parts constitute each a part of the boundary of a separate substantially closed space and means are provided to apply separate fluid pressures in these two spaces, so as to permit a substantial balancing of the total axial stresses operative on the movable wall.
  • the present invention relates to turbines and more particularly to apparatus for effecting adjustment of the cross-section of the radial diffuser of a turbo-compressor.
  • the invention provides apparatus of this character in which one of the axially limiting walls of the diffuser is axially movable by means of an annular piston which surrounds the compressor inlet coaxially of the compressor, the piston operating on the movable diffuser wall via an annular linkage member which likewise coaxially surrounds the compressor inlet.
  • a turbo-compressor such as the closed cycle of the working substance of a refrigeration plant
  • this adjustrnent must be effected against forces operating on the wall which may amount to several tens.
  • Dependable and satisfactory adjustment of the diffuser cross-section by motion of one of its end walls against forces of this kind has hitherto presented substantial difficulties.
  • the rear side of the adjustable wall i.e., the side thereof away from the diffuser space
  • certain portions of the housing are constructed to enclose together a hollow closed space, this space being filled with fluid under pressure so that the stresses operative axially of the machine on the movable wall will be nearly in equilibrium.
  • the rear side of the adjustable wall is fitted with an axially-extending partition which divides the hollow space into at least two parts sealed off from each other, these two parts each being bounded in part by a separate portion of the rear surface of the movable diffuser wall. With suitable pressures applied in these hollow spaces, the total axial stresses operative on the movable wall nearly balance each other out.
  • one of these hollow spaces is connected to the diffuser outlet whereas the other may be connected to a point downstream of the compressor-rotor or with the suction side of the compressor.
  • FIG. 1 is an axial section through a single stage compressor according to the invention.
  • FIG. 2 is an axial section similar to that of FIG. 1 but showing another form of single stage compressor according to the invention.
  • the compressor-rotor 1 is driven from the shaft 2 by a motor not shown.
  • the gas to be compressed passes axially through the suction inlet line 3 and thence to the compressor inlet space 4. It is then forced radially outward by means of the rotor blades 5. From the outward limit of the rotor the working substance passes into the diffuser 6, flowing between the diffuser walls 7 and 8 to the spiral 21.
  • one of the diffuser walls 7 is built to be adjustable in position. By adjustment of the position of this wall, control is effected on the rate of flow of gas or other working substance through the compressor.
  • the inlet conduit 4 together with the compressor housing 9 encloses a space 10 in which an annular piston 11 is movably disposed.
  • the two parts 10a and 10b of this space defined by the piston are connected to a'hydraulic system not shown, by means of which oil under pressure can be supplied to and withdrawn from the spaces 10a and 10b at will in order to effect axial motion of the piston 11.
  • Piston 11 is coupled to the movable diffuser 'wall 7 by means of a linkage which is likewise preferably coaxial with the compressor and which likewise preferably surrounds compressor inlet 4.
  • this linkage comprises a cylindrical tube 12 which surrounds the inlet 4, together with a conical coupling element 13 which connects the tube 12 with the wall 7.
  • the linkage comprising elements 12 and 13 together with the rear face 22 of the diffuser wall 7 and the compressor housing 9 enclose a hollow space which is divided into two parts 16 and 17 by means of a radial partition 14 in the housing and an axially extending cylindrical partition 15 formed on the rear side of the dividing wall 7.
  • the spaces 16 and 17 are sealed off gas-tight from each other by means of a rubber ring packing 18 accommodated in a circular groove of the cylindrical partition 15, the packing being engaged with the radial partition 14.
  • a fluid under pressure is provided in each of the spaces 16 and 17.
  • This fluid may be provided by the working substance to be compressed, withdrawn at a suitable point from the flow cycle thereof.
  • the space 17 is connected to the diffuser outlet via the circular slot 19 whereas the space 16 is connected with the inlet to the diffuser by openings 20 in the conical coupling member 13.
  • unlike pressures are maintained in the spaces 16 and 17 so that the space 16 is subjected to the pressure existing at the inlet to the diffuser whereas the space 17 experiences that existing at the outlet from the diffuser.
  • the forces exerted by the fluid being compressed on the side of the wall 7 exposed to the diffuser space may be substantially balanced outwith the aid of the pressures in the spaces 16 and 17.
  • the adjustment of position of the wall 7 is in this way much facilitated.
  • FIG. 2 is similar to that of FIG. 1 except that in the embodiment of FIG. 2 the space 16 is connected to the inlet line 3 of the turbo-compressor by means of a conduit 23 and not to the inlet to the diffuser 6, the openings 20 of FIG. 1 being absent in FIG. 2.
  • the space 16 is therefore subjected to the inlet pressure of the turbo-compressor rather than to the pressure at the inlet to the diffuser immediately downstream of the rotor blades 5.
  • a turbo-compressor comprising a rotor and a stator, the combination therewith of a diffuser having a fixed wall and a movable Wall, motor means coupled to said movable Wall, a cylindrical partition affixed to said movable wall on the side thereof remote from said fixed wall, stationary means defining with said partition two annular spaces each bounded in part by a separate portion of said side of said movable Wall, and means to apply pressures to said spaces.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US454585A 1964-05-11 1965-05-10 Turbine radial diffuser Expired - Lifetime US3365120A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH608764A CH413201A (de) 1964-05-11 1964-05-11 Einstellvorrichtung für verstellbaren Radialdiffusor

Publications (1)

Publication Number Publication Date
US3365120A true US3365120A (en) 1968-01-23

Family

ID=4304045

Family Applications (1)

Application Number Title Priority Date Filing Date
US454585A Expired - Lifetime US3365120A (en) 1964-05-11 1965-05-10 Turbine radial diffuser

Country Status (4)

Country Link
US (1) US3365120A (de)
CH (1) CH413201A (de)
GB (1) GB1106107A (de)
NL (2) NL6406513A (de)

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3426964A (en) * 1966-10-11 1969-02-11 Dresser Ind Compressor apparatus
US3478955A (en) * 1968-03-11 1969-11-18 Dresser Ind Variable area diffuser for compressor
US4070132A (en) * 1976-11-02 1978-01-24 Baltimore Aircoil Company, Inc. Variable performance pump
US4219305A (en) * 1978-12-26 1980-08-26 Carrier Corporation Diffuser control
US4257733A (en) * 1978-12-26 1981-03-24 Carrier Corporation Diffuser control
US4378194A (en) * 1980-10-02 1983-03-29 Carrier Corporation Centrifugal compressor
EP0134748A2 (de) * 1983-09-12 1985-03-20 Carrier Corporation Leiträder mit variabler Breite
US4544325A (en) * 1980-10-22 1985-10-01 Teledyne Industries, Inc. Variable geometry device for turbine compressor outlet
US4552308A (en) * 1980-10-22 1985-11-12 Teledyne Industries, Inc. Turbine engine variable geometry device
US4643639A (en) * 1984-12-24 1987-02-17 Sundstrand Corporation Adjustable centrifugal pump
US4850795A (en) * 1988-02-08 1989-07-25 Dresser-Rand Company Diffuser having ribbed vanes followed by full vanes
US4869642A (en) * 1988-06-09 1989-09-26 Allied-Signal Inc. Variable output vortex pump
US4877369A (en) * 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser control
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
US5059091A (en) * 1989-07-21 1991-10-22 Rolls-Royce Plc Gas turbine engine compressor assembly
US5082428A (en) * 1990-08-16 1992-01-21 Oklejas Robert A Centrifugal pump
EP1304447A1 (de) * 2001-10-19 2003-04-23 BorgWarner Inc. Durchsatzregelung für einen Turbolader
US20040238691A1 (en) * 2003-05-28 2004-12-02 Harold Hipsky Compressor for use in aircraft fuel tank air purge system
WO2005054683A1 (en) * 2003-11-12 2005-06-16 Honeywell International, Inc. Compressor having an adjustable diffuser wall and method therefor
US20050141988A1 (en) * 2003-12-30 2005-06-30 Acoustiflo, Ltd. Centrifugal fan diffuser
US20110232282A1 (en) * 2008-12-11 2011-09-29 Borgwarner Inc. Simplified variable geometry turbocharger with variable nozzle
DE102011018240A1 (de) 2011-04-19 2011-11-24 Tcg Unitech Systemtechnik Gmbh Radialpumpe mit einem in einem Gehäuse drehbar gelagerten Laufrad
EP2392828A3 (de) * 2010-06-07 2013-01-23 Schaeffler Technologies AG & Co. KG Abdichtung für eine regelbare Kühlmittelpumpe
US20140328667A1 (en) * 2012-11-09 2014-11-06 Susan J. NENSTIEL Variable geometry diffuser having extended travel and control method thereof
US20150275917A1 (en) * 2014-03-26 2015-10-01 Kabushiki Kaisha Toyota Jidoshokki Centrifugal Compressor
US20160208808A1 (en) * 2013-08-26 2016-07-21 Gree Electric Appliances, Inc. Of Zhuhai Regulator assembly and centrifugal compressor
US20170356301A1 (en) * 2016-06-13 2017-12-14 Nuovo Pignone Tecnologie Srl Variable geometry assembly for a turbomachine and turbomachine comprising said assembly
CN110778515A (zh) * 2018-07-30 2020-02-11 丹佛斯公司 用于制冷剂流动控制的机电致动器
WO2020125193A1 (zh) * 2018-12-17 2020-06-25 珠海格力电器股份有限公司 离心式压缩机及扩压装置
US20210079928A1 (en) * 2019-09-18 2021-03-18 Massachusetts Institute Of Technology Adaptive volutes for centrifugal pumps
US11415148B2 (en) * 2018-04-09 2022-08-16 Carrier Corporation Variable diffuser drive system

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4460310A (en) * 1982-06-28 1984-07-17 Carrier Corporation Diffuser throttle ring control
EP0654587B1 (de) * 1993-11-19 1999-01-20 Holset Engineering Company Limited Turbine mit variabler Einlassgeometrie
DE102022120820A1 (de) 2022-08-17 2024-02-22 Rolls-Royce Solutions GmbH Verdichtergehäuse, Radialverdichter mit einem solchen Verdichtergehäuse, Radialverdichteranordnung, Abgasturbolader und Brennkraftmaschine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE234751C (de) * 1911-05-19
CH133892A (de) * 1928-07-18 1929-06-30 Sulzer Ag Zentrifugalpumpe.
US2684634A (en) * 1946-04-16 1954-07-27 Sfindex Guiding means for liquids and gases
US2861774A (en) * 1950-02-16 1958-11-25 Alfred J Buchi Inlet control for radial flow turbines
US3032259A (en) * 1957-12-23 1962-05-01 Sulzer Ag Turbocompressor having a radial diffuser
US3150650A (en) * 1961-09-29 1964-09-29 Caterpillar Tractor Co Variable area diffuser for compressor
US3204863A (en) * 1961-05-13 1965-09-07 Hausammann Werner Compressor

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE234751C (de) * 1911-05-19
CH133892A (de) * 1928-07-18 1929-06-30 Sulzer Ag Zentrifugalpumpe.
US2684634A (en) * 1946-04-16 1954-07-27 Sfindex Guiding means for liquids and gases
US2861774A (en) * 1950-02-16 1958-11-25 Alfred J Buchi Inlet control for radial flow turbines
US3032259A (en) * 1957-12-23 1962-05-01 Sulzer Ag Turbocompressor having a radial diffuser
US3204863A (en) * 1961-05-13 1965-09-07 Hausammann Werner Compressor
US3150650A (en) * 1961-09-29 1964-09-29 Caterpillar Tractor Co Variable area diffuser for compressor

Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3426964A (en) * 1966-10-11 1969-02-11 Dresser Ind Compressor apparatus
US3478955A (en) * 1968-03-11 1969-11-18 Dresser Ind Variable area diffuser for compressor
US4070132A (en) * 1976-11-02 1978-01-24 Baltimore Aircoil Company, Inc. Variable performance pump
US4219305A (en) * 1978-12-26 1980-08-26 Carrier Corporation Diffuser control
US4257733A (en) * 1978-12-26 1981-03-24 Carrier Corporation Diffuser control
US4378194A (en) * 1980-10-02 1983-03-29 Carrier Corporation Centrifugal compressor
US4544325A (en) * 1980-10-22 1985-10-01 Teledyne Industries, Inc. Variable geometry device for turbine compressor outlet
US4552308A (en) * 1980-10-22 1985-11-12 Teledyne Industries, Inc. Turbine engine variable geometry device
EP0134748A2 (de) * 1983-09-12 1985-03-20 Carrier Corporation Leiträder mit variabler Breite
EP0134748A3 (en) * 1983-09-12 1985-07-03 Carrier Corporation Variable width diffuser
US4643639A (en) * 1984-12-24 1987-02-17 Sundstrand Corporation Adjustable centrifugal pump
US4850795A (en) * 1988-02-08 1989-07-25 Dresser-Rand Company Diffuser having ribbed vanes followed by full vanes
US4877369A (en) * 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser control
US4902200A (en) * 1988-04-25 1990-02-20 Dresser-Rand Company Variable diffuser wall with ribbed vanes
US4869642A (en) * 1988-06-09 1989-09-26 Allied-Signal Inc. Variable output vortex pump
US4932835A (en) * 1989-04-04 1990-06-12 Dresser-Rand Company Variable vane height diffuser
US5059091A (en) * 1989-07-21 1991-10-22 Rolls-Royce Plc Gas turbine engine compressor assembly
US5082428A (en) * 1990-08-16 1992-01-21 Oklejas Robert A Centrifugal pump
EP1304447A1 (de) * 2001-10-19 2003-04-23 BorgWarner Inc. Durchsatzregelung für einen Turbolader
US20040238691A1 (en) * 2003-05-28 2004-12-02 Harold Hipsky Compressor for use in aircraft fuel tank air purge system
WO2005054683A1 (en) * 2003-11-12 2005-06-16 Honeywell International, Inc. Compressor having an adjustable diffuser wall and method therefor
US7001140B2 (en) 2003-12-30 2006-02-21 Acoustiflo, Ltd. 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
US7357621B2 (en) 2003-12-30 2008-04-15 Acoustiflo, Llc Centrifugal fan diffuser
US8590305B2 (en) * 2008-12-11 2013-11-26 Borgwarner Inc. Simplified variable geometry turbocharger with variable nozzle
US20110232282A1 (en) * 2008-12-11 2011-09-29 Borgwarner Inc. Simplified variable geometry turbocharger with variable nozzle
EP2392828A3 (de) * 2010-06-07 2013-01-23 Schaeffler Technologies AG & Co. KG Abdichtung für eine regelbare Kühlmittelpumpe
DE102011018240A1 (de) 2011-04-19 2011-11-24 Tcg Unitech Systemtechnik Gmbh Radialpumpe mit einem in einem Gehäuse drehbar gelagerten Laufrad
US11092166B2 (en) 2012-11-09 2021-08-17 Johnson Controls Technology Company Variable geometry diffuser having extended travel and control method thereof
US20140328667A1 (en) * 2012-11-09 2014-11-06 Susan J. NENSTIEL Variable geometry diffuser having extended travel and control method thereof
US10378553B2 (en) * 2012-11-09 2019-08-13 Johnson Controls Technology Company Variable geometry diffuser having extended travel and control method thereof
US20160208808A1 (en) * 2013-08-26 2016-07-21 Gree Electric Appliances, Inc. Of Zhuhai Regulator assembly and centrifugal compressor
US10082147B2 (en) * 2013-08-26 2018-09-25 Gree Electric Appliances, Inc. Of Zhuhai Regulator assembly and centrifugal compressor
US20150275917A1 (en) * 2014-03-26 2015-10-01 Kabushiki Kaisha Toyota Jidoshokki Centrifugal Compressor
US9874226B2 (en) * 2014-03-26 2018-01-23 Kabushiki Kaisha Toyota Jidoshokki Centrifugal compressor
US20170356301A1 (en) * 2016-06-13 2017-12-14 Nuovo Pignone Tecnologie Srl Variable geometry assembly for a turbomachine and turbomachine comprising said assembly
US10927700B2 (en) * 2016-06-13 2021-02-23 Nuovo Pignone Tecnologie Srl Variable geometry assembly for a turbomachine and turbomachine comprising said assembly
US11415148B2 (en) * 2018-04-09 2022-08-16 Carrier Corporation Variable diffuser drive system
CN110778515A (zh) * 2018-07-30 2020-02-11 丹佛斯公司 用于制冷剂流动控制的机电致动器
WO2020125193A1 (zh) * 2018-12-17 2020-06-25 珠海格力电器股份有限公司 离心式压缩机及扩压装置
US11578733B2 (en) 2018-12-17 2023-02-14 Gree Electric Appliances, Inc. Of Zhuhai Centrifugal compressor and diffuser
US20210079928A1 (en) * 2019-09-18 2021-03-18 Massachusetts Institute Of Technology Adaptive volutes for centrifugal pumps
US11708841B2 (en) * 2019-09-18 2023-07-25 Massachusetts Institute Of Technology Adaptive volutes for centrifugal pumps

Also Published As

Publication number Publication date
CH413201A (de) 1966-05-15
NL126489C (de)
NL6406513A (de) 1965-11-12
GB1106107A (en) 1968-03-13

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