US3799694A - Variable diffuser - Google Patents

Variable diffuser Download PDF

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Publication number
US3799694A
US3799694A US00308160A US30816072A US3799694A US 3799694 A US3799694 A US 3799694A US 00308160 A US00308160 A US 00308160A US 30816072 A US30816072 A US 30816072A US 3799694 A US3799694 A US 3799694A
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United States
Prior art keywords
vanes
movable
passage
walls
compressor
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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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US00308160A
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English (en)
Inventor
J Duzan
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.)
Motors Liquidation Co
Original Assignee
General Motors Corp
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 General Motors Corp filed Critical General Motors Corp
Priority to US00308160A priority Critical patent/US3799694A/en
Priority to CA178,361A priority patent/CA996524A/en
Priority to GB5183673A priority patent/GB1437105A/en
Priority to JP12980473A priority patent/JPS5322964B2/ja
Application granted granted Critical
Publication of US3799694A publication Critical patent/US3799694A/en
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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
    • F04D29/46—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

Definitions

  • a variable diffuser for a centrifugal compressor has a set of fixed vanes remote from the compressor rotor and a set of movable vanes nearer the rotor.
  • movable vane for each two fixed vanes, and the movable vanes are swingable about axes adjacent their leading edges between a position in which the trailing edges of these vanes block the passage between two adjacent fixed vanes and a position in which the trailing edges of the movable vanes are substantially spaced from the fixed vanes.
  • a centrifugal compressor is a device in which a rotating rotor or impeller delivers air at relatively high velocity by the effect of centrifugal force on the gas within the impeller.
  • a compressor also includes a diffuser, which normally is an annular space surrounding the periphery of the impeller and which usually is provided with vanes to guide the gas flow and minimize turbulence and frictional losses in the diffuser.
  • the air or other gas (which will be referred to hereafter as air) is delivered from the impeller with a substantial radial component of velocity and ordinarily a substantially greater tangential component.
  • the function of the diffuser is to decelerate the air smoothly and to recover as static head the dynamic head of the air due to its velocity.
  • the vanes usually provided in the diffuser divide the air into a number of streams flowing circumferentially and radially of the diffuser, each stream flowing through a passage which diverges gradually so as to facilitate the efficient conversion of the volves changing the geometry of the diffuser, and
  • the direction of'flow of the air fuser vanes may be viewed alternatively as a diffuser in which there is an inner row of movable vanes and an outer row of hollow vanes and in which there is a diffusing passage between adjacent hollow outer vanes, as well as a passage through the interior of each hollow vane which may be closed by the movable from the rotor will vary with the rotational speed of the rotor and with the amount of air flow, which also generally depends upon the speed of the rotor.
  • the compressor discharges through combustion apparatus to a turbine nozzle which may be of fixed or variable area.
  • the gas turbine operate efficiently over a normal operating range to deliver power and also in idling operation in which the rotationspeed and air flow of the engine are greatly reduced. This is particularly the case in automotive vehicles in which the engine may be idling during standstill of the vehicle or may be operating at relatively low power during non-accelerating low-speed cruising of the vehicle.
  • My invention is directed to the provision of a diffuser in which the diffuser vanes are movable so that the vanes may be aligned with the direction of flow from the impeller and thus minimize disturbances of flow caused by off-design incidence of the flow on the leading edge of the vanes.
  • It also provides for varying the area of the effective part of the diffuser between a relatively large area condition for high air flow and a relatively small area condition for low flow, while minimizing undesirable variations in the ratio between entrance and exit areas of the effective part of the diffuser.
  • This is effected by the provision of an outer row of fixed vanes and an inner row of movable vanes, with the angle of the inner row vanes being variable, and with the inner row of vanes serving to block flow through alternate passages in the outer row of vanes in one condition or setting of the difvanes.
  • variable diffusers for compressors have been proposed and may call attention as examples to those shown in US. Pats. as follows: Elling, No. 908,227, Dec. 29, 1908; Birmann, No. 2,428,830, Oct. 14, 1947; and Bauger et al., No. 2,645,410, July 14, 1953.
  • Elling No. 908,227, Dec. 29, 1908
  • Birmann No. 2,428,830, Oct. 14, 1947
  • Bauger et al. No. 2,645,410, July 14, 1953.
  • my type of variable diffuser described above is not suggested by the prior art.
  • FIG. 1 is a sectional view of a centrifugal compressor taken on a plane containing the axis of rotation thereof.
  • FIG. 2 is a partial elevation view, with parts cut away and in section, taken on the plane indicated by the line 2-2 in FIG. 1.
  • the drawings illustrate a centrifugal compressor which is intended to be a part of a gas turbine engine which, as is well known, includes a combustion apparaare illustrated.
  • the front wall has a. circular opening at 6 within which is piloted an annular mounting plate 7.
  • An annular'diffuser front plate 8 is fixed to the mounting plate 7 by a ring of bolts 10.
  • a fixed impeller forward shroud l 1 is mounted on the front plate 8 by a cap screw'l 2.
  • a diffuser outer ring 14 is fixed to plate 8 by a ring of studs 15 welded to the diffuser ring and secured by nuts.
  • Adiffuser rear plate 16 of annular form is fixed to the outer ring 14 by a ring of cap screws 18.
  • the diffuser rear plate is fixed by a ring of cap screws 19 to a flange 20 at the forward end of a shaft housing 22.
  • An annular compressor inlet outer wall 23 is fixed to mounting plate 7 by a ring of cap screws 24.
  • An annular compressor inlet inner wall 26 is joined by struts 27 to a ring secured by cap screws 28 to an annular plate 29.
  • Plate 29 is fixed to the mounting plate 7 by a ring of cap screws 30 which also mount the housing 31 of an air cleaner (not illustrated).
  • Walls 23 and 26 define between them a converging air inlet 32 into the compressor.
  • the swirl or circumferential velocity component of air entering the compressor through the inlet 32 may be varied by variable setting inlet vanes 34 each of which is connected by an arm 35'to some suitable mechanism for actuating the inlet vanes 34 in unison which is not illustrated, since it is not material to my invention.
  • This actuating mechanism may be mounted on a plate 36 bolted to the inner wall 26. While the adjustable inlet guide vanes 34 are a desirable part of the overall compressor or engine, they are not relevant to my invention which has to do with the diffuser of the compressor rather than its inlet.
  • a drive shaft 38 which may be connected to the turbine is "mounted in the shaft housing 22 and supported by a fixed bearing or journal block 39 within which a journal 40 of the shaft rotates.
  • Bearing 39 is fixed to an inwardly extending flange 42 of the shaft housing.
  • Thrust bearings 43 and 44 on the shaft 38 engage the faces of journal block 39. These are located on the shaft by abutments at which the shaft changes diameter. Oil is supplied to the bearings from a line 46. The lubrication of the bearing will now be further described as the details are immaterial.
  • a seal ring 47 abuts the thrust bearing 44 through a washer and is in turn abutted by the impeller 48 of the compressor which is piloted upon and splined to an extension 50 of shaft 38 and secured thereto by nut 51 and sleeve 52. Seal ring 47 cooperates with a seal mounted in a ring 53 bolted to the forward end of the shaft housing 22.
  • the impeller 48 comprises a disk 55 and radially extending vanes 56, and may follow standard practice in the design of such impellers. Details are immaterial to my invention. Air entering the compressor through the inlet 32 is driven outwardly and circumferentially by the vanes 56 into a diffuser 58 bounded by plate 8, ring 14, and plate 16, the diffuser having an outlet at 59.
  • the stationary parts of the compressor are fixed to the shaft housing 22, which is suitably located, by means not illustrated, in the case 2.
  • the mounting plate 7 is located axially of the case and may slide relative to the front wall 4 to accommodate differential expansion of the parts as required.
  • a heat insulating ring 60 is mounted on the rear face of the mounting plate 7.
  • the outer diffuser ring 14 is a brazed structure made up of a forward part and a rear part.
  • the forward part comprises a ring 62 (FIG. 1) from which vanes or walls 63 and 64 extend axially of the compressor. These vanes or walls are thin sheets of metal provided by machining grooves across ring 62. The rear edges of the vanes are brazed to a rear ring 66.
  • the diffuser outer ring 14, as previously pointed out, is fixed to the diffuser front plate 8 by studs and to the rear plate 16 by cap screws 18. Constantly open diffusing passages 67 are defined between vanes 64 and 63 adjacent in the direction of rotation of the impeller and closable diffuser passages 68 are defined between vanes 63 and 64 adjacent in the direction of rotation of the impeller.
  • Each vane comprises a wedge-shaped body 71 having a thin leading edge 72 and a broad trailing edge 74.
  • the leading edge portion of each vane is brazed to a cylindrical pivot 75, each of which is inserted in a socket or journal 76 in the diffuser rear plate 16.
  • a chordwise-extending slot 78 in each vane accommodates an actuating pin 79 fixed in a unison ring 80.
  • This unison ring is' radially located by engagement with the inner surface of diffuser rear ring 66 and a shoulder 83 on plate 16, and is axially located by its mounting between vanes 70 and the rear diffuser plate 16. Vanes 70 in turn bear against the diffuser front plate 8.
  • a bearing surface 82 is disposed on the rear face of the unison ring 80.
  • the unison ring is in turn rotated by an actuating ring 84 mounted on the rear side of rear plate 16 and supported by three rollers 86 disposed at 120 intervals and rotatably supported on bolts 87 fixed in the plate 16.
  • the ring 84 may be rotated by any suitable actuating mechanism such as a pneumatic or oil servo or electromechanicalservo, and the mechanism for rotating this is not illustrated.
  • Actuating ring 84 is coupled to unison ring 80 by six posts 88 extending rearwardly from the unison ring through circumferential slots 90 (see also FIG. 2) in the rear plate 16. Ring 84 is fixed to these posts by cap screws 91.
  • each movable diffuser vane 70 is terminated at an angle such as to fit against the leading edges of the vanes 63 and 64 with which it cooperates. Also, a small abutment 92 on each movable vane engages a vane 63 to limit and fix the open position of the movable vanes.
  • Any suitable actuator rotates ring 84 which rotates ring 80 through posts 88.
  • the pins 79 onring 80 moves the vanes 70 about their pivots 75, with the pins moving in the slots 78 of the vanes.
  • the position for maximum flow is that illustrated at the right of FIG. 2 in which the opening between adjacent movable vanes is a maximum and the succeeding vanes or walls 63 and 64 of the outer set continue the diffusing passages which may be considered to be the passage indicated at 94 in FIG. 2 and continuing through passage 67.
  • a more constricted diffusing passage 95 is defined between the vane bodies 71.
  • the walls or vanes 63 and 64 perform no particular diffusing function, the smaller diffuser having sufficient area ratio between vanes 70.
  • the diffuser may operate over a range between minimum and maximum area, being varied as air flow varies by any suitable control. The diffuser works well over the intermediate range as well as at the extremes.
  • vanes 63 and 64 define the walls of diffusing passages for the higher flow condition and are immaterial to the diffusion in the minimum flow condition in which the smaller diffuser area between the closed vanes 70 is sufficient for diffusion. In intermediate conditions, some diffusion occurs in passages 67 and 68 in the outer ring.
  • An annular diffuser for a radial-flow gas compressor comprising, in combination, front and back walls extending substantially radially from the axis of rotation of the compressor, the walls defining between them a diffusing passage for the gas; a circumferentially spaced set of generally radially and circumferentially extending fixed vanes bridging the passage in a radially outer zone and defining diverging passages between adjacent vanes; and a circumferentially spaced set of generally radially and circumferentially extending movable vanes bridging the passages in a radially inner zone and defining diverging passages between adjacent vanes; each movable vane being mounted so as to be rotatable about an axis generally parallel to the axis of rotation of the compressor; the movable vanes diverging in thickness from the leading edge and each having a trailing edge movable to engage the leading edge of two mutually adjacent fixed vanes so as to close the passage between the fixed vanes so engaged and provide a continuous diffusing passage through the
  • An annular diffuser for a radial-flow gas compressor comprising, in combination, front and back walls extending substantially radially from the axis of rotation of the compressor, the walls defining between them a diffusing passage for the gas; a circumferentially spaced set of generally radially and circumferentially extending fixed vanes bridging the passage in a radially outer zone and defining diverging passages between adjacent vanes; and a circumferentially spaced set of generally radially and circumferentially extending movable vanes bridging the passage in a radially inner zone and defining diverging passages between adjacent vanes; each movable vane being mounted so as to be rotatable about an axis adjacent to its leading edge generally parallel to the axis of rotation of the compressor; the movable vanes diverging in thickness from the leading edge and each having a trailing edge movable to engage the a leading edge of two mutually adjacent fixed vanes so as to close the passage between the fixed vanes so engaged and provide a
  • An annular diffuser for a radial-flow gas compressor comprising, in combination, front and back walls extending substantially radially from the axis of rotation of the compressor, the walls defining between them a diffusing passage for the gas; a circumferentially spaced annular set of generally radially and circumferentially extending movable vanes bridging the passage ina radially inner zone and defining diverging passages between adjacent vanes; each movable vane being mounted so as to be rotatable about an axis adjacent to its leading edge; common actuating means operable to rotate the movable vanes concurrently to vary the entrance and discharge areas of the passages between the movable vanes and thus define a diffuser adjustable for small and large flows between the movable vanes; the movable vanes diverging in thickness from the leading edge and each having a thick trailing edge; and a circumferentially spaced annular set of generally radially and circumferentially extending fixed walls bridging the passage in a zone radially
  • An annular diffuser for a radial-flow gas compressor comprising, in combination, front and back walls extending substantially radially from the axis of rotation of the compressor, the walls defining between them a diffusing passage for the gas; a circumferentially spaced annular set of generally radially and circumferentially extending movable vanes bridging the passage in a radially inner zone and defining diverging passages between adjacent vanes; each movable vane being mounted so as to be rotatable about an axis adjacent to its leading edge; common actuating means operable to rotate the movable vanes concurrently including a unison ring rotatable about the axis of rotation of the compressor and pins on the unison ring engaging in slots in the movable vanes remote from the axis of vane rotation to vary the entrance and discharge areas of the passages between the movable vanes and thus define a diffuser adjustable for small and large flows between the movable vanes; the movable vanes diverging in

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00308160A 1972-11-20 1972-11-20 Variable diffuser Expired - Lifetime US3799694A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US00308160A US3799694A (en) 1972-11-20 1972-11-20 Variable diffuser
CA178,361A CA996524A (en) 1972-11-20 1973-08-08 Variable diffuser for centrifugal compressor
GB5183673A GB1437105A (en) 1972-11-20 1973-11-08 Annular diffuser for a radial-flow gas compressor
JP12980473A JPS5322964B2 (en(2012)) 1972-11-20 1973-11-20

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Application Number Priority Date Filing Date Title
US00308160A US3799694A (en) 1972-11-20 1972-11-20 Variable diffuser

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Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3963369A (en) * 1974-12-16 1976-06-15 Avco Corporation Diffuser including movable vanes
US3992128A (en) * 1975-06-09 1976-11-16 General Motors Corporation Variable diffuser
US4280788A (en) * 1978-05-22 1981-07-28 Tokyo Shibaura Denki Kabushiki Kaisha Multistage hydraulic machine system and a method for controlling the operation thereof
US4288198A (en) * 1979-03-12 1981-09-08 Hitachi, Ltd. Method of controlling multistage centrifugal compressor equipment
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
US4492520A (en) * 1982-05-10 1985-01-08 Marchand William C Multi-stage vane stator for radial inflow turbine
US4514976A (en) * 1980-06-02 1985-05-07 Rockwell International Corporation Integrated auxiliary power and environmental control unit
WO1985004692A1 (en) * 1984-04-11 1985-10-24 Turbo Tech Inc. Variable area turbine
GB2193256A (en) * 1986-06-02 1988-02-03 Teledyne Ind Centrifugal compressors
US4770605A (en) * 1981-02-16 1988-09-13 Mitsubishi Jukogyo Kabushiki Kaisha Diffuser device in a centrifugal compressor and method for manufacturing the same
USRE32756E (en) * 1981-08-18 1988-09-27 A/S Kongsberg Vapenfabrikk Pre-swirl inlet guide vane for compressor
US4799142A (en) * 1986-07-11 1989-01-17 The Toro Company Irrigation controller
US4978279A (en) * 1988-09-06 1990-12-18 Sundstrand Corporation Simplified inlet guide vane construction for a rotary compressor
US5207559A (en) * 1991-07-25 1993-05-04 Allied-Signal Inc. Variable geometry diffuser assembly
US5569078A (en) * 1995-03-06 1996-10-29 Colorado State University Research Foundation Air diffuser having fixed and variable outlet ports
US6513330B1 (en) 2000-11-08 2003-02-04 Allison Advanced Development Company Diffuser for a gas turbine engine
US20040076513A1 (en) * 2002-10-22 2004-04-22 Carrier Corporation Rotating vane diffuser for a centrifugal compressor
US20050123397A1 (en) * 2003-12-03 2005-06-09 Mcardle Nathan J. Compressor diffuser
WO2005064168A1 (en) * 2003-12-29 2005-07-14 Nuovo Pignone Holding S.P.A. Vane system equipped with a guiding mechanism for cen­trifugal compressor
US20060062666A1 (en) * 2004-09-22 2006-03-23 Hamilton Sundstrand Variable area diffuser
WO2006048042A1 (en) * 2004-11-08 2006-05-11 Honeywell International, Inc. Variable geometry compressor
US20080276613A1 (en) * 2007-05-09 2008-11-13 Phillipe Noelle Discrete variable geometry compressor
US20090155058A1 (en) * 2005-08-02 2009-06-18 Phillipe Noelle Variable Geometry Compressor Module
US20100187164A1 (en) * 2009-01-29 2010-07-29 Wark Rickey E Static classifier cage
WO2012012926A1 (zh) * 2010-07-28 2012-02-02 Wang Hang 电动复合多级离心压气机装置
US8540484B2 (en) 2010-07-23 2013-09-24 United Technologies Corporation Low mass diffuser vane
US8668444B2 (en) 2010-09-28 2014-03-11 General Electric Company Attachment stud for a variable vane assembly of a turbine compressor
US8714916B2 (en) 2010-09-28 2014-05-06 General Electric Company Variable vane assembly for a turbine compressor
CN104081062A (zh) * 2012-02-23 2014-10-01 三菱重工业株式会社 压缩机
FR3009348A1 (fr) * 2013-08-02 2015-02-06 Snecma Diffuseur pour un compresseur radial ou mixte d'un moteur comprenant un flasque dont une partie est mobile
US9080578B2 (en) 2008-09-02 2015-07-14 Hamilton Sundstrand Corporation Compact drive for compressor variable diffuser
WO2015069841A3 (en) * 2013-11-11 2015-07-16 Dresser, Inc. System and method to position variable diffuser vanes in a compressor device
US20170305559A1 (en) * 2016-04-22 2017-10-26 Hamilton Sundstrand Corporation Environmental control system utilizing enhanced compressor
US10753370B2 (en) 2017-05-23 2020-08-25 Rolls-Royce Corporation Variable diffuser with axially translating end wall for a centrifugal compressor
US10753369B2 (en) 2018-05-11 2020-08-25 Rolls-Royce Corporation Variable diffuser having a respective penny for each vane
US10883379B2 (en) 2018-05-11 2021-01-05 Rolls-Royce Corporation Variable diffuser having a respective penny for each vane

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US1771711A (en) * 1928-01-19 1930-07-29 Voith Gmbh J M Split guide blade for centrifugal pumps
DE547491C (de) * 1930-09-18 1932-04-01 Escher Wyss Maschf Ag Leitvorrichtung mit drehbaren Schaufeln fuer Kreiselmaschinen, insbesondere Kreiselpumpen
US2392200A (en) * 1944-11-27 1946-01-01 Gen Electric Centrifugal compressor
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US1771711A (en) * 1928-01-19 1930-07-29 Voith Gmbh J M Split guide blade for centrifugal pumps
DE547491C (de) * 1930-09-18 1932-04-01 Escher Wyss Maschf Ag Leitvorrichtung mit drehbaren Schaufeln fuer Kreiselmaschinen, insbesondere Kreiselpumpen
US2392200A (en) * 1944-11-27 1946-01-01 Gen Electric Centrifugal compressor
US2645410A (en) * 1947-05-05 1953-07-14 Construction De Moteurs D Avia Gaseous fluid compressor
US3162421A (en) * 1961-01-24 1964-12-22 Kuehnle Kopp Kausch Ag Gas turbine construction
US3356289A (en) * 1964-05-14 1967-12-05 Hispano Suiza Sa Supersonic compressors of the centrifugal or axial flow and centrifugal types
US3588270A (en) * 1968-08-20 1971-06-28 Escher Wyss Ltd Diffuser for a centrifugal fluid-flow turbomachine

Cited By (53)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3963369A (en) * 1974-12-16 1976-06-15 Avco Corporation Diffuser including movable vanes
US3992128A (en) * 1975-06-09 1976-11-16 General Motors Corporation Variable diffuser
US4280788A (en) * 1978-05-22 1981-07-28 Tokyo Shibaura Denki Kabushiki Kaisha Multistage hydraulic machine system and a method for controlling the operation thereof
US4288198A (en) * 1979-03-12 1981-09-08 Hitachi, Ltd. Method of controlling multistage centrifugal compressor equipment
US4514976A (en) * 1980-06-02 1985-05-07 Rockwell International Corporation Integrated auxiliary power and environmental control unit
US4378194A (en) * 1980-10-02 1983-03-29 Carrier Corporation Centrifugal compressor
US4770605A (en) * 1981-02-16 1988-09-13 Mitsubishi Jukogyo Kabushiki Kaisha Diffuser device in a centrifugal compressor and method for manufacturing the same
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
US4492520A (en) * 1982-05-10 1985-01-08 Marchand William C Multi-stage vane stator for radial inflow turbine
US4657476A (en) * 1984-04-11 1987-04-14 Turbotech, Inc. Variable area turbine
WO1985004692A1 (en) * 1984-04-11 1985-10-24 Turbo Tech Inc. Variable area turbine
GB2193256A (en) * 1986-06-02 1988-02-03 Teledyne Ind Centrifugal compressors
US4780049A (en) * 1986-06-02 1988-10-25 Palmer Lynn D Compressor
GB2193256B (en) * 1986-06-02 1991-03-06 Teledyne Ind Compressor
US4799142A (en) * 1986-07-11 1989-01-17 The Toro Company Irrigation controller
US4978279A (en) * 1988-09-06 1990-12-18 Sundstrand Corporation Simplified inlet guide vane construction for a rotary compressor
US5207559A (en) * 1991-07-25 1993-05-04 Allied-Signal Inc. Variable geometry diffuser assembly
US5569078A (en) * 1995-03-06 1996-10-29 Colorado State University Research Foundation Air diffuser having fixed and variable outlet ports
US6513330B1 (en) 2000-11-08 2003-02-04 Allison Advanced Development Company Diffuser for a gas turbine engine
US20040076513A1 (en) * 2002-10-22 2004-04-22 Carrier Corporation Rotating vane diffuser for a centrifugal compressor
US6814540B2 (en) * 2002-10-22 2004-11-09 Carrier Corporation Rotating vane diffuser for a centrifugal compressor
US20050123397A1 (en) * 2003-12-03 2005-06-09 Mcardle Nathan J. Compressor diffuser
WO2005064168A1 (en) * 2003-12-29 2005-07-14 Nuovo Pignone Holding S.P.A. Vane system equipped with a guiding mechanism for cen­trifugal compressor
NO339532B1 (no) * 2003-12-29 2016-12-27 Nuovo Pignone Spa Ledeskovlsystem utstyrt med en styremekanisme for en sentrifugalkompressor
US7520716B2 (en) 2003-12-29 2009-04-21 Nuovo Pignone Holding S.P.A. Vane system equipped with a guiding mechanism for centrifugal compressor
US20070166149A1 (en) * 2003-12-29 2007-07-19 Remo Tacconelli Vane system equipped with a guiding mechanism for centrifugal compressor
WO2006137863A3 (en) * 2004-09-22 2007-08-09 Hamilton Sundstrand Corp Variable area diffuser for a radial c0mpress0r
US20060062666A1 (en) * 2004-09-22 2006-03-23 Hamilton Sundstrand Variable area diffuser
US7407367B2 (en) 2004-09-22 2008-08-05 Hamilton Sundstrand Corporation Variable area diffuser
US7854585B2 (en) 2004-11-08 2010-12-21 Honeywell International Inc. Variable geometry compressor
WO2006048042A1 (en) * 2004-11-08 2006-05-11 Honeywell International, Inc. Variable geometry compressor
US20080118349A1 (en) * 2004-11-08 2008-05-22 Dominique Petitjean Variable Geometry Compressor
US20090155058A1 (en) * 2005-08-02 2009-06-18 Phillipe Noelle Variable Geometry Compressor Module
US8240984B2 (en) * 2005-08-02 2012-08-14 Honeywell International Inc. Variable geometry compressor module
US20080276613A1 (en) * 2007-05-09 2008-11-13 Phillipe Noelle Discrete variable geometry compressor
US9080578B2 (en) 2008-09-02 2015-07-14 Hamilton Sundstrand Corporation Compact drive for compressor variable diffuser
US20100187164A1 (en) * 2009-01-29 2010-07-29 Wark Rickey E Static classifier cage
US8231007B2 (en) * 2009-01-29 2012-07-31 Wark Rickey E Static classifier cage
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US10753369B2 (en) 2018-05-11 2020-08-25 Rolls-Royce Corporation Variable diffuser having a respective penny for each vane
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Also Published As

Publication number Publication date
JPS5322964B2 (en(2012)) 1978-07-12
JPS4981907A (en(2012)) 1974-08-07
GB1437105A (en) 1976-05-26
CA996524A (en) 1976-09-07

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