US3719430A - Diffuser - Google Patents

Diffuser Download PDF

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Publication number
US3719430A
US3719430A US00174335A US3719430DA US3719430A US 3719430 A US3719430 A US 3719430A US 00174335 A US00174335 A US 00174335A US 3719430D A US3719430D A US 3719430DA US 3719430 A US3719430 A US 3719430A
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Prior art keywords
passages
diffuser
cross
annulus
section
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Expired - Lifetime
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US00174335A
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English (en)
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L Blair
A Bryans
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General Electric Co
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General Electric Co
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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
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • 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 diffuser annulus includes a plurality of passages therethrough, wherein the passages gradually merge radially outward from a curvilinear cross-section to a rectilinear cross-section.
  • T he diffuser annulus may be optimized for maximum efficiency by varying the axially extending width of the passages at the outer periphery of the annulus independently of the diameter of the passages at the inner periphery of the annulus.
  • This invention relates to a diffuser and more particularly to a centrifugal compressor diffuser which may be optimized for maximum efficiency regardless of the number and length of passages therethrough.
  • centrifugal compressor diffuser In most centrifugal compressors, a rotating impeller is arranged to add energy by accelerating the flow of gas therethrough.
  • the centrifugal compressor diffuser is ordinarily characterized by an annular space surrounding the impeller in which the velocity of the fluid leaving the impeller is decreased and its static pressure is correspondingly increased.
  • Circumferentially spaced apart guide vanes have generally been provided in most conventional diffusers to produce passages expanding in area for the purpose of diffusing the flow.
  • Diffusers having circumferentially spaced apart passages which are curvilinear in cross-section are well known to the art. Diffusers of this type are of particular advantage for use with todays gas turbine engines which are designed to accommodate extremely high flow velocities.
  • the advantage to such diffusers lies in the reduction of flow separation and boundary layers which are precipitated within the corners of rectangular passages.
  • flow exiting past a series of blunt edges as found between curvilinear passages becomes turbulent and incurs substantial flow losses.
  • thin edged vanes as found between rectilinear passages are most desirable.
  • the length of the passages determines the radius of the annulus, and hence the outer circumference of the annulus.
  • the total number of passages may also be predetermined by other design criteria so that when the outer circumference of the annulus is divided by the total number of passages, the circumferential dimension of the rectangular outlet cross-section becomes fixed and can not be varied.
  • the other axially extending dimension of the rectangular passage outlet could not be made smaller than the diameter of the circular inlet cross-section without incurring a complicated and expensive machining operation or the addition of bulky extra hardware. Therefore, the designer was not always able to adjust the passage outlet area to inlet area ratio so as to achieve the maximum efficiency of conversion of kinetic energy to static pressure energy.
  • FIG. 1 shows a partial cross-sectional view of a conventional diffuser in combination with a centrifugal compressor.
  • FIG. 1(a) shows a cross-sectional view taken along the line lar-1a of FIG. 1.
  • FIG. 2 shows a graph divided into various areas of diffuser efficiency, and including a curvic representation for one diffuser having a predetermined number of passages.
  • IFIG. 3 shows a partially sectioned side View of the diffuser of this invention in combination with a centrifugal compressor.
  • FIG. 3(a) shows a cross-sectional view taken along the line 3a-3a of FIG. 3.
  • FIG. 4 shows a partially cut away perspective view of the diffuser of FIG. 3.
  • FIG. 5 shows a partial cross-sectional view taken along the central axis of the diffuser of FIGS. 3 and 4 in combination with a compressor and gas turbine engine.
  • FIGS. 1 and 1(11) there is shown a portion of a centrifugal compressor wherein an impeller 1l) ⁇ is mounted for axial rotation about a center shaft 12.
  • the impeller 10 includes a plurality of blades 14 circumferentially supported in spaced relationship by a web 16.
  • the conventional diffuser includes inner and outer peripheral surfaces 20 and 22, the inner Surface being closely adjacent to the outer -periphery of the impeller shown.
  • the conventional diffuser includes a plurality of ciricumferentially spaced apart passages 24 extending through the annulus wherein the cross-sectional areas of the passages gradually widen in an outward radial direction. The passages convert the high kinetic energy with which the flowing medium leaves the impeller into static pressure energy exiting from the outer peripheral surface 22.
  • inlet cross-sectional areas (Ai) of the passages 24 may be determined from the following equation:
  • outlet cross-sectional area (Ao) may be determined from the following equation:
  • FIG. 2 there is shown a graph having a plurality of curvilinear plots thereon, wherein the areas between each plot are representative of a level of efciency for conversion of kinetic energy into static pressure.
  • the ordinate of the graph is a logarithmic scale calibrated to display varying ratios of outlet cross-sectional areas (A) to inlet cross-sectional areas (Ai) and the abscissa is a logarithmic scale calibrated to display varying ratios ofppassage lengths (L) to inlet cross-sectional radii (r1).
  • the phantom curve A represents a characteristic plot for a difuser wherein the number of passages (Np) have been predetermined and remain constant and the axially extending width (W) has been minimized so as to equal 2r1. As may be readily observed, the curve A does not intersect the area of maximum efficiency, (80%) and therefore ditusers having this particular number of passages cannot be optimized for peak efficiency.
  • the number of diffuser passages may be changed so as to shift the curve A into intersection with the enclosed area of maximum efficiency; however, varying the number of diiuser passages to achieve optimum eiiiciency may not always be possible due to other design criteria.
  • width (W) of each passage Another parameter that may be varied to shift the location of the curve A is the axially extending width (W) of each passage.
  • W width
  • the width (W) may be decreased in order to decrease the ratio (A0)/ (Ai) for a particular ratio of passage length (L) to inlet cross-sectional radius (r1).
  • the curve A could then be shifted toward the absicssa and away from the ordinate so as to intersect the area of maximum eciency.
  • the width (W) has already been minimized to equal twice the radius (r1) of the circular inlet cross-sectional area in the conventional diiuser.
  • the diffuser of this invention allows a decrease in the width (W) to less than twice the radius (r1) thereby permitting etiiciency optimization for any diffuser regardless of the number of diffuser passages.
  • FIGS. 3 and 3(a) where the numerals refer to previously described elements, there is shown a portion of a conventional centrifugal compressor in cornbination with the annular diffuser 30 of this invention.
  • the annular diffuser 30, a portion of which is also shown in FIG. 4, is mounted externally so as to surround the outer tips of the blades 14.
  • the annular diffuser includes inner and outer peripheral surfaces 31 and 32, the inner surface being closely adjacent to the outer periphery of the impeller as shown.
  • the diffuser 30 includes a plurality of ciricumferentially spaced apart passages 34 extending through the annulus so as to provide flow connection from the inner peripheral surface 31 to the outer peripheral surface 32.
  • the cross-sectional areas of the passages gradually widen in an outward radial direction so as to convert the high kinetic energy with which the flowing medium leaves the impeller into static pressure energy.
  • the passages 34 have been shown as initially assuming circular inlet cross-Sections 36 on the inner peripheral surface 31 and gradually merging into rectangular outlet cross-sections 3S on the outer peripheral surface 32.
  • passages 34 initially assume a circular inlet cross-section, as previously discussed, reduces the boundary layer separation characteristic of square cornered rectangular forms which cause detachment of flow together with loss of eiciency.
  • the passages 34 must also merge into rectangular cross-sections so that the uid exits past narrow, axially extending, trailing edges 40 and commingles in a smooth and uniform ow without the ow separation and losses associated with dumping a uid past a series of blunt edges.
  • the passages In order to minimize the flow losses associated with rectangular forms, it has been found preferable not only to have the passages initially assume a circular inlet crosssection, but to also maintain the circular cross-section for the greater length of the passage and to confine the merging portion of the passage to the outmost radial end.
  • the limiting factor as to how small the length of the merging portion of the passage may be in relation to the overall passage length is the angle of divergence of the passage walls from the centerline of the passage. As the length of the merging portion of the passage is decreased, the angle of divergence of the passage walls from the centerline increases until a point is reached where How separation from the walls becomes significant.
  • the passages 34 of the diffuser 30 into what are generally conical passages 44 between the circular inlet cross-sections 36 and intermediate circular cross-sections indicated by phantom lines 42 and what are generally merging passages 46 between the intermediate cross-sections 42 and the rectangular outlet crosssections 38 on the outer periphery 32.
  • the merging passages 46 are initially circular in cross-section and gradually merge the ow into a rectangular cross-section 38.
  • passages 44 have been shown as preferred, it is within the intended scope of invention that the passages may alternatively be any other formation that is curvilinear in cross-section.
  • centerlines 47 of the passages 34 are shown as substantially straight, they may also be curved, and although the centerlines of the passages are shown as being in a transverse radial plane, they may also be inclined at a moderate angle to this plane without departing from the scope of the invention.
  • the outside circumferential edges of the diffuser 30 have been bevelled so as to provide two converging, scalloped, frusto-conical surfaces 48, 48', which are best shown in FIG. 4.
  • the scalloped frusto-conical surfaces 48, 48 are contiguously engaged by annular frusto-conical discs 50, 50' respectively which converge in a generally outward radial direction.
  • the outer radial edges 52, 52' of the annular frusto-conical discs 50, 50' cooperate with the axially extending trailing edges 40 to define the rectangular outlet cross-sections 38 on the outer periphery 32 of the annulus.
  • the inward radial penetration for the scalloped, frusto-conical surfaces 48, 48 preferably should not extend beyond the length of the merging passages 46.
  • the discs 50, 50 may be attached to the scalloped, frusta-conical surfaces 48, 48' by conventional means such as brazing. Also of particular advantage is the fact that the passages may be machined by conventionl techniques such as milling or electrochemical machining.
  • each rectangular outlet cross-section may be made smaller than the circular cross-section diameter 2r1.
  • decreasing (W) effects a corresponding decrease in the ratio (Ao)/(Ai) without effecting a corresponding change in the abscissa coordinate of curve A of FIG. 2.
  • curve A shifting away from the ordinate and toward the abscissa so as to intersect the enclosed area of maximum eflciency (80%) on the graph.
  • the commingling of flow exiting from the transitional passages is accomplished in a smooth and uniform manner with a minimum of turbulence and loss.
  • Flow in the annular manifold 60 may include an undesirable swirl component which can be removed by circumferentially spaced apart deswirl vanes 62 which act to cancel the residual circumferential velocity component of the flow exiting from the diffuser ring 30.
  • Conduit 64 may direct the ow emanating from the swirl vanes 62 to a combustion chamber (not shown) as used in a gas turbine engine.
  • a diffuser comprises: an annular housing having a plurality of circumferentially spaced apart passages extending through the annulus wherein the passages initially assume curvilinear inlet cross-sections on the inner peripheral surface of the annulus and gradually merge towards rectilinear outlet cross-sections, on the outer peripheral surface of the annulus with at least one outer circumferential edge of the annulus being bevelled to define a scalloped frusto-conical surface;
  • a diffuser surrounding a centrifugal compressor which comprises:
  • annular housing having a plurality of circumferentially spaced apart passages extending in an outward, generally radial direction through the annulus where the passages initially assume curvilinear inlet cross-sections on the inner peripheral surface of the annulus and gradually merge toward rectilinear outlet cross-sections, on the outer peripheral surface of the annulus, with the outer circumferential edges of the annulus bevelled to define two converging, scalloped frusto-conical surfaces; and at least two frusto-conical annuli, each annuli of which is contiguous with a frusto-conical surface and defines one nominally linear edge of the rectilinear outlet crosssection.
  • each rectangular outlet cross-section coincides with the length of each axially extending edge and is of shorter length than the diameter of each inlet cross-section.
  • a merging portion of each passage at the outer radial end is initially of curvilinear cross-section and gradually merges into a rectilinear cross-section with the cross-sectional area of the merging portion remaining substantially constant throughout its length, and the remaining initial portion of each passage is of curvilinear cross-section gradually widening in an outward radial direction so as to convert the high kinetic energy with which the owing medium leaves the compressor into static pressure energy.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00174335A 1971-08-24 1971-08-24 Diffuser Expired - Lifetime US3719430A (en)

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US17433571A 1971-08-24 1971-08-24

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US (1) US3719430A (enrdf_load_stackoverflow)
JP (1) JPS5526317B2 (enrdf_load_stackoverflow)
AU (1) AU456332B2 (enrdf_load_stackoverflow)
BE (1) BE787830A (enrdf_load_stackoverflow)
CH (1) CH544225A (enrdf_load_stackoverflow)
DE (1) DE2240994C2 (enrdf_load_stackoverflow)
FR (1) FR2151390A5 (enrdf_load_stackoverflow)
GB (1) GB1395930A (enrdf_load_stackoverflow)
IT (1) IT964073B (enrdf_load_stackoverflow)
NL (1) NL7211453A (enrdf_load_stackoverflow)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4027997A (en) * 1975-12-10 1977-06-07 General Electric Company Diffuser for a centrifugal compressor
DE2753328A1 (de) * 1976-12-02 1978-06-08 Gen Electric Diffusor fuer zentrifugalverdichter von gasturbinentriebwerken
US4576550A (en) * 1983-12-02 1986-03-18 General Electric Company Diffuser for a centrifugal compressor
US4815935A (en) * 1987-04-29 1989-03-28 General Motors Corporation Centrifugal compressor with aerodynamically variable geometry diffuser
US4966523A (en) * 1989-07-27 1990-10-30 Tiernay Turbines, Incorporated Two-row pipe diffusers with boundary layer control
US5011371A (en) * 1987-04-29 1991-04-30 General Motors Corporation Centrifugal compressor/pump with fluid dynamically variable geometry diffuser
WO2001018404A1 (en) * 1999-09-07 2001-03-15 General Electric Company Deswirler system for centrifugal compressor
US6280139B1 (en) * 1999-10-18 2001-08-28 Pratt & Whitney Canada Corp. Radial split diffuser
US20040091350A1 (en) * 2002-11-13 2004-05-13 Paolo Graziosi Fluidic actuation for improved diffuser performance
US20050039334A1 (en) * 2003-08-22 2005-02-24 Steve Roby Method for the manufacture of a vaned diffuser
EP1568891A4 (en) * 2002-12-04 2006-01-04 Mitsubishi Heavy Ind Ltd DIFFUSER FOR CENTRIFUGAL COMPRESSORS AND MANUFACTURING METHOD THEREFOR
US20080193288A1 (en) * 2007-02-14 2008-08-14 Borg Warner Inc. Diffuser restraint system and method
US20090205360A1 (en) * 2008-02-20 2009-08-20 Haley Paul H Centrifugal compressor assembly and method
US20090205362A1 (en) * 2008-02-20 2009-08-20 Haley Paul F Centrifugal compressor assembly and method
US20090208331A1 (en) * 2008-02-20 2009-08-20 Haley Paul F Centrifugal compressor assembly and method
FR2941742A1 (fr) * 2009-02-05 2010-08-06 Snecma Ensemble diffuseur-redresseur pour une turbomachine
US7975506B2 (en) 2008-02-20 2011-07-12 Trane International, Inc. Coaxial economizer assembly and method
US20180216629A1 (en) * 2017-01-27 2018-08-02 Man Diesel & Turbo Se Radial Compressor and Turbocharger
US11009038B2 (en) * 2017-04-07 2021-05-18 Safran Aircraft Engines Reinforced axial diffuser
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11187243B2 (en) 2015-10-08 2021-11-30 Rolls-Royce Deutschland Ltd & Co Kg Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor
US11261878B2 (en) 2019-08-22 2022-03-01 Mitsubishi Heavy Industries, Ltd. Vaned diffuser and centrifugal compressor
US11286951B2 (en) 2019-05-21 2022-03-29 Pratt & Whitney Canada Corp. Diffuser pipe with exit scallops
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5896417U (ja) * 1981-12-22 1983-06-30 株式会社日立ホームテック 調理器用ちり受皿
JPS58182397U (ja) * 1982-05-31 1983-12-05 株式会社東芝 高周波加熱調理装置
JPS6276816U (enrdf_load_stackoverflow) * 1985-10-31 1987-05-16
FR2927950B1 (fr) * 2008-02-27 2011-12-23 Snecma Ensemble diffuseur-redresseur pour une turbomachine
CN110107505B (zh) * 2019-06-14 2020-07-03 安徽工业大学 一种飞行器增压装置

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE968101C (de) * 1950-03-03 1958-01-16 Escher Wyss Gmbh Einrichtung an radialen Kreiselverdichtern und -pumpen zur Umsetzung von kinetischer Energie des Stroemungsmittels in Druckenergie

Cited By (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4027997A (en) * 1975-12-10 1977-06-07 General Electric Company Diffuser for a centrifugal compressor
DE2640392A1 (de) * 1975-12-10 1977-06-16 Gen Electric Diffusor fuer zentrifugalkompressor
FR2334856A1 (fr) * 1975-12-10 1977-07-08 Gen Electric Diffuseur pour compresseur centrifuge
DE2753328A1 (de) * 1976-12-02 1978-06-08 Gen Electric Diffusor fuer zentrifugalverdichter von gasturbinentriebwerken
FR2372965A1 (fr) * 1976-12-02 1978-06-30 Gen Electric Diffuseur perfectionne pour moteur a turbine a gaz
US4576550A (en) * 1983-12-02 1986-03-18 General Electric Company Diffuser for a centrifugal compressor
US4815935A (en) * 1987-04-29 1989-03-28 General Motors Corporation Centrifugal compressor with aerodynamically variable geometry diffuser
US5011371A (en) * 1987-04-29 1991-04-30 General Motors Corporation Centrifugal compressor/pump with fluid dynamically variable geometry diffuser
US4966523A (en) * 1989-07-27 1990-10-30 Tiernay Turbines, Incorporated Two-row pipe diffusers with boundary layer control
WO2001018404A1 (en) * 1999-09-07 2001-03-15 General Electric Company Deswirler system for centrifugal compressor
US6280139B1 (en) * 1999-10-18 2001-08-28 Pratt & Whitney Canada Corp. Radial split diffuser
US20040091350A1 (en) * 2002-11-13 2004-05-13 Paolo Graziosi Fluidic actuation for improved diffuser performance
US6896475B2 (en) 2002-11-13 2005-05-24 General Electric Company Fluidic actuation for improved diffuser performance
EP1568891A4 (en) * 2002-12-04 2006-01-04 Mitsubishi Heavy Ind Ltd DIFFUSER FOR CENTRIFUGAL COMPRESSORS AND MANUFACTURING METHOD THEREFOR
US20050039334A1 (en) * 2003-08-22 2005-02-24 Steve Roby Method for the manufacture of a vaned diffuser
US7191519B2 (en) * 2003-08-22 2007-03-20 Borgwarner Inc. Method for the manufacture of a vaned diffuser
US20080193288A1 (en) * 2007-02-14 2008-08-14 Borg Warner Inc. Diffuser restraint system and method
DE102008009125A1 (de) 2007-02-14 2008-09-04 Borgwarner Inc., Auburn Hills Diffusor-Rückhaltesystem und Verfahren
US8328535B2 (en) 2007-02-14 2012-12-11 Borgwarner Inc. Diffuser restraint system and method
US20090208331A1 (en) * 2008-02-20 2009-08-20 Haley Paul F Centrifugal compressor assembly and method
US8627680B2 (en) 2008-02-20 2014-01-14 Trane International, Inc. Centrifugal compressor assembly and method
US9683758B2 (en) 2008-02-20 2017-06-20 Trane International Inc. Coaxial economizer assembly and method
US20090205362A1 (en) * 2008-02-20 2009-08-20 Haley Paul F Centrifugal compressor assembly and method
US7856834B2 (en) 2008-02-20 2010-12-28 Trane International Inc. Centrifugal compressor assembly and method
US7975506B2 (en) 2008-02-20 2011-07-12 Trane International, Inc. Coaxial economizer assembly and method
US8037713B2 (en) 2008-02-20 2011-10-18 Trane International, Inc. Centrifugal compressor assembly and method
US9556875B2 (en) 2008-02-20 2017-01-31 Trane International Inc. Centrifugal compressor assembly and method
US9353765B2 (en) 2008-02-20 2016-05-31 Trane International Inc. Centrifugal compressor assembly and method
US20090205360A1 (en) * 2008-02-20 2009-08-20 Haley Paul H Centrifugal compressor assembly and method
WO2010089466A1 (fr) * 2009-02-05 2010-08-12 Snecma Ensemble diffuseur-redresseur pour une turbomachine
CN102308060B (zh) * 2009-02-05 2014-11-19 斯奈克玛 用于涡轮机的散流器-喷嘴组件
US20120018543A1 (en) * 2009-02-05 2012-01-26 Snecma Diffuser/rectifier assembly for a turbine engine
US9512733B2 (en) * 2009-02-05 2016-12-06 Snecma Diffuser/rectifier assembly for a turbine engine with corrugated downstream walls
CN102308060A (zh) * 2009-02-05 2012-01-04 斯奈克玛 用于涡轮机的散流器-喷嘴组件
FR2941742A1 (fr) * 2009-02-05 2010-08-06 Snecma Ensemble diffuseur-redresseur pour une turbomachine
RU2518746C2 (ru) * 2009-02-05 2014-06-10 Снекма Узел диффузор-направляющий аппарат для турбомашины
US11187243B2 (en) 2015-10-08 2021-11-30 Rolls-Royce Deutschland Ltd & Co Kg Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor
US20180216629A1 (en) * 2017-01-27 2018-08-02 Man Diesel & Turbo Se Radial Compressor and Turbocharger
CN108361226A (zh) * 2017-01-27 2018-08-03 曼柴油机和涡轮机欧洲股份公司 径向压缩机和涡轮增压器
US11009038B2 (en) * 2017-04-07 2021-05-18 Safran Aircraft Engines Reinforced axial diffuser
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11286951B2 (en) 2019-05-21 2022-03-29 Pratt & Whitney Canada Corp. Diffuser pipe with exit scallops
US11261878B2 (en) 2019-08-22 2022-03-01 Mitsubishi Heavy Industries, Ltd. Vaned diffuser and centrifugal compressor
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11815047B2 (en) 2020-07-14 2023-11-14 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine

Also Published As

Publication number Publication date
DE2240994C2 (de) 1983-09-15
CH544225A (de) 1973-11-15
BE787830A (fr) 1972-12-18
JPS4831504A (enrdf_load_stackoverflow) 1973-04-25
FR2151390A5 (enrdf_load_stackoverflow) 1973-04-13
AU4506472A (en) 1974-04-26
GB1395930A (en) 1975-05-29
JPS5526317B2 (enrdf_load_stackoverflow) 1980-07-12
AU456332B2 (en) 1974-12-12
DE2240994A1 (de) 1973-03-01
IT964073B (it) 1974-01-21
NL7211453A (enrdf_load_stackoverflow) 1973-02-27

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