WO2019063384A1 - Diffuseur pour compresseur - Google Patents

Diffuseur pour compresseur Download PDF

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Publication number
WO2019063384A1
WO2019063384A1 PCT/EP2018/075355 EP2018075355W WO2019063384A1 WO 2019063384 A1 WO2019063384 A1 WO 2019063384A1 EP 2018075355 W EP2018075355 W EP 2018075355W WO 2019063384 A1 WO2019063384 A1 WO 2019063384A1
Authority
WO
WIPO (PCT)
Prior art keywords
diffuser
passage
base
passages
adjacent
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.)
Ceased
Application number
PCT/EP2018/075355
Other languages
German (de)
English (en)
Inventor
Christian Kreienkamp
Daniel Bernhard RUSCH
Joel Müller
Joshua Frei
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems 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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Publication of WO2019063384A1 publication Critical patent/WO2019063384A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • 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
    • F05D2250/70—Shape
    • F05D2250/73—Shape asymmetric
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the present invention relates to a diffuser for a compressor, in particular for a centrifugal compressor.
  • the term radial compressor also includes so-called mixed-flow compressors with an axial inflow and a radial outflow of the compressor impeller.
  • the scope of the present invention also extends to compressors with a purely radial or diagonal inflow or outflow of the compressor wheel.
  • the present invention relates to a diffuser for a centrifugal compressor, wherein the centrifugal compressor is used in a turbocharger, and wherein the turbocharger may comprise an axial turbine or a radial or a so-called mixed flow turbine.
  • Diffusers are known in the prior art for use in centrifugal compressors for turbocharger applications.
  • a fluid for example air
  • the fluid is first drawn in axially via a compressor wheel connected upstream of the diffuser and accelerated and precompressed in the compressor wheel.
  • the fluid is thereby supplied with energy, which is in the form of pressure, temperature and kinetic energy.
  • At the outlet of the compressor impeller prevail high flow velocities.
  • the accelerated and compressed air leaves the compressor wheel tangentially in the direction of the diffuser.
  • the kinetic energy of the accelerated air is converted into pressure. This is done by delaying the flow in the diffuser. By radial expansion of the flow cross-section of the diffuser is increased. The fluid is thus delayed and pressure is built up.
  • the diffusers used therein can be provided with a blading.
  • An example of a bladed diffuser is shown in DE 10 2008 044 505.
  • the blast diffusers known from the prior art are generally designed as radial bladed parallel-walled diffusers, as shown, for example, in US 4,131,389.
  • the flow in the diffuser can be delayed more. The flow velocities in the spiral are thereby reduced, whereby the wall friction losses decrease and the efficiency of the compressor stage is improved becomes.
  • the delay or pressure increase achievable in the diffuser by geometrical variation for a given operating point is limited, since excessive retardation leads to flow instabilities due to boundary layer delamination in the diffuser.
  • the limits of the stable operating range of the diffuser thus determine the position of the surge limit of the compressor in the compressor map. If a diffuser with sidewall divergence is used instead of a parallel-walled diffuser - such a diffuser is described, for example, in WO 2012/116880 A1 - the efficiency increases at the same compressor pressure ratios, but at the same time the pumping limit with respect to the compressor shifts for a given compressor pressure ratio parallel-walled diffuser to larger mass flows. This effect is undesirable.
  • the compressor map width is thereby reduced and the usability of the compressor stage for turbocharger applications is thereby limited.
  • One solution is to fluidly connect a diffuser duct section of a bladed diffuser via pressure equalization ports to an annular passageway serving as a stabilizer space to allow pressure equalization between individual diffuser passages of the diffuser formed by adjacent diffuser vanes and to stabilize operation of the diffuser.
  • the invention relates to a diffuser having a flow channel, which is formed in the flow direction of a first side wall and a second side wall, said side walls are at least partially divergent to each other.
  • This sidewall divergence is preferably due to the fact that one of the side walls has a diffuser base plate whose outer surface facing the flow channel at least partially does not extend in the radial direction.
  • This diffuser base plate may be disposed on the air inlet side of the compressor or on the bearing housing side of the compressor.
  • the present invention is based on the object, in the event that the divergence must be formed on the interface between diffuser base plate and diffuser blade root, a bladed diffuser sidewall divergence such that its manufacturing cost is reduced.
  • a diffuser according to the invention comprises:
  • a flow channel which is delimited in the direction of flow by a first side wall and a second side wall, wherein these side walls are at least partially divergent and wherein one of the side walls has a diffuser base plate whose outer surface facing the flow channel does not run at least partially in the radial direction,
  • a diffuser vane ring having a plurality of spaced apart diffuser vanes at least partially disposed in the flow channel, each of the diffuser vanes having a pressure side and a suction side,
  • each diffuser passage being disposed between two adjacent diffuser vanes and having a base between the two adjacent diffuser vanes, and wherein
  • a non-tangential transition is provided between a first plane formed by the base of a first diffuser passage and a second plane formed by the base of a second, adjacent diffuser passage, or a non-tangent transition is provided in the base of the diffuser passage provided between the two adjacent diffuser blades.
  • the invention makes it possible to manufacture sidewall-divergent diffusers based on a targeted aerodynamic design of the diffuser geometry to a conventionally millable geometry.
  • the same thermodynamic properties can be achieved as with a sidewall divergent diffuser with ideal geometry, without negatively affecting the manufacturing costs and throughput times of the diffuser.
  • the diffuser base plate is provided on the air inlet side.
  • the diffuser base plate is provided on the bearing housing side.
  • diffuser passages are associated with pressure exit ports which are connected to a diffuser cavity.
  • the non-tangent transition is executed a step or a kink or rounded.
  • the non-tangential transition is provided in an extension region of a diffuser passage defining the diffuser passage.
  • the non-tangent transition is provided within a diffuser passage defining the diffuser passage.
  • a non-tangential transition is provided in each case between the bases of all the diffuser passages.
  • the bases of the diffuser passages are inclined in the flow direction.
  • the base surfaces of the diffuser passages fall linearly in the flow direction, in a curve radius or in a free-form surface.
  • the base surfaces of the diffuser passages are each inclined between the suction side of a diffuser blade delimiting the respective diffuser passage and the pressure side of the adjacent diffuser blade delimiting the respective diffuser passage.
  • the base surfaces of the diffuser passages extend between the suction side of a diffuser blade defining the respective diffuser passage and the pressure side of the adjacent diffuser blade delimiting the respective diffuser passage.
  • the heights of the transitions are in line coincide with each other adjacent bases of adjacent diffuser passages.
  • a compressor has a diffuser according to the invention.
  • a turbocharger has a compressor according to the invention.
  • FIG. 3 shows a sketch to illustrate a diffuser blades having diffuser vane ring
  • FIG. 4 shows diagrams illustrating exemplary embodiments for non-tangential transitions between the plane formed by the base of a diffuser passage and a second plane formed by the base of a respectively adjacent diffuser passage
  • FIG. 7 is a sectional view for illustrating the structure of a diffuser according to the invention
  • Fig. 8 is a sketch illustrating a second embodiment of the invention
  • FIG. 9 is a diagram illustrating an alternative embodiment.
  • FIG. 1 shows sectional views of a bladed diffuser having radial compressor of an exhaust gas turbocharger, which further includes an exhaust turbine and a bearing housing.
  • a radial compressor is shown, the diffuser of which has a diffuser base plate 23a arranged on the bearing housing side.
  • the diffuser base plate 23a of the diffuser is arranged on the air inlet side of the radial compressor.
  • the exhaust gas turbine 50 is shown only schematically. It has a gas inlet 51, via which it is charged with exhaust gases of an internal combustion engine to be charged by means of the exhaust gas turbocharger, and a gas outlet 52.
  • the energy contained in the exhaust stream is converted in the turbine into rotational energy for driving a compressor wheel 9 connected via a shaft 30 to an impeller of the turbine.
  • the compressor wheel 9 comprises a hub 10 and a plurality of compressor wheel blades 11 arranged on the hub.
  • the shaft 30 is rotatably mounted in the bearing housing 40.
  • the compressor wheel is disposed in the compressor housing 2 adjacent to the bearing housing 40.
  • the compressor housing 2 in the illustrated embodiment includes an outer compressor housing 22, which is a volute, and an inner compressor housing 20 inserted into the outer compressor housing. Together with the hub 10 of the compressor wheel 9 and the wall portions of the bearing housing 40 define the various Parts of the compressor housing 2 the flow channel for the air to be compressed.
  • Compressor housing 20 limited. In this area, the flow experiences a Direction change from the axial to the radial direction. Subsequently, the flow enters the region of the diffuser, which forms the flow channel which extends from the compressor wheel outlet up to the collecting space 24 which is provided in the outer compressor housing 22.
  • This collecting space 24 is spirally formed, wherein at the broad end of the spiral, the air flow leaves the compressor in the direction of a charge air cooler or to an air inlet of the internal combustion engine.
  • the diffuser region is essentially an annular cavity, which is delimited in front of a first side wall 21 and a second side wall 41. From the viewpoint of the compressor wheel blades 11, one speaks of an air inlet side wall 21 and a bearing housing side side wall 41. These two side walls extend from Verêtrradaustritt up to the mouth in the spiral collecting space 24. They are both in the illustrated embodiment at right angles to the shaft axis 30 and thus parallel to each other.
  • diffuser vanes 25 of a diffuser vane ring are positioned along the circumference of the diffuser.
  • This diffuser vane ring has a number of spaced diffuser vanes, which are at least partially disposed in the flow channel 23.
  • Each diffuser vane has an entry edge 251.
  • the two side walls 21 and 41 of the diffuser, between which the flow channel 23 extends, may alternatively extend at least in sections divergently to one another in the embodiment shown in FIG.
  • a sketch of such a sidewall divergent diffuser is shown in FIG.
  • the flow channel 23, the first side wall 21 and the second side wall 41 are shown, wherein it can be seen that these two side walls are divergent to each other.
  • the diffuser channel 23 Between these two side walls runs the diffuser channel 23.
  • diffuser vanes 25 of a diffuser vane ring are positioned.
  • the diffuser sketched in FIG. 2 has pressure compensation openings 26 which connect the diffuser channel 23 to a diffuser cavity 27, which may be an annular channel serving as a stabilizer chamber.
  • FIG. 3 shows a sketch for illustrating a diffuser blade ring having diffuser blades and the distribution of the diffuser blades along the entire circumferential area of the diffuser blade ring. It can be seen that when shown Embodiment along the entire peripheral region of the diffuser vane ring a number of spaced apart diffuser vanes 25 is arranged. Between each two adjacent diffuser vanes 25 there is a diffuser passage 28 in each case. The flow direction of the fluid through these diffuser passages is designated by reference numeral 29. The diffuser vanes 25 shown are along the entire
  • Each of the diffuser vanes has a pressure side 25a and a suction side 25b, as illustrated in FIG. 3 in one of the diffuser vanes.
  • Each diffuser passage has, as will be explained below with reference to the other figures, a base that forms a plane. In FIG. 3, three of these base areas are marked by reference numerals 28a, 28b and 28c.
  • pressure equalization openings 26 are associated with the diffuser passages 28, wherein these pressure equalization openings are arranged, for example, in the region of the diffuser passages between the pressure side of a diffuser blade and the suction side of the respectively adjacent diffuser blade.
  • pressure equalization openings 26 are associated with the diffuser passages 28, wherein these pressure equalization openings are arranged, for example, in the region of the diffuser passages between the pressure side of a diffuser blade and the suction side of the respectively adjacent diffuser blade.
  • FIG 3 are some of these
  • Pressure compensation openings 26 exemplified. These pressure compensation openings 26 are connected to a diffuser cavity 27, which is formed for example as a diffuser ring and is positioned in the figure 3 below the diffuser vane ring. A part of this diffuser cavity is indicated by dashed lines in FIG.
  • the cavity can either be a continuous annular space or connect only individual passages.
  • the preferred embodiment is a continuous annular space.
  • the pressure compensation openings 26 shown there have a circular cross-sectional area and are positioned in a diffuser passage 28 between two adjacent diffuser blades.
  • the pressure compensation openings can also be realized as a circumferential or perforated slot in front of the respective blade leading edge, as a bore at the narrowest flow cross section (throat) of a diffuser passage 28 or as a slot at the narrowest flow cross section (throat) of a diffuser passage 28.
  • a non-tangential transition is provided between a first plane formed by the base of a first diffuser passage and a second plane formed by the base of a second, adjacent diffuser passage.
  • lines A and B are shown, with their use in the following FIG. 4, the non-tangent transitions between a first plane formed by the base of a first diffuser passage and a second through the base of a second diffuser passage Diffuser passage formed second level can be explained.
  • FIG. 4 shows diagrams for illustrating embodiments for non-tangential transitions between the plane formed by the base of a diffuser passage and a second plane formed by the base of a respectively adjacent diffuser passage.
  • the height curve h of the diffuser ring surface is plotted upwards and the circumferential direction 0 of the diffuser blade ring is applied to the top.
  • a curve is shown with the letter A, which does not have tangential transitions U1, U2 and U3.
  • the transition U1 is provided in the circumferential direction of the diffuser vane ring in front of the base surface 28a forming inclined plane.
  • the transition U2 is provided between the base surface 28a forming, inclined plane and the base 28a forming, also inclined plane extending.
  • the transition U3 is provided between the base surface 28b forming inclined plane and the base 28c forming, also inclined plane extending. It is important that the line A characterizes a region corresponding to an extension region of the diffuser vanes, i. the diffuser blades do not cut.
  • the non-tangent-continuous transitions are respectively provided in the extension region of the diffuser blade delimiting the respective diffuser passage.
  • the advantage of this embodiment is that no transitions are necessary within the planes forming the bases of the diffuser passages.
  • a curve is shown with the letter B which does not have tangential transitions U2 'and U3'.
  • the transition U2 'in the circumferential direction of the diffuser vane ring between the base 28a forming, inclined plane and the base surface 28b forming, also inclined plane is provided.
  • the non-tangential transitions are respectively provided within a diffuser blade delimiting the diffuser passage.
  • the advantage of this Embodiment is also that within the base surfaces of the diffuser passages forming levels, no transitions are necessary.
  • FIG. 5 shows a sketch to illustrate a first embodiment of the invention.
  • This first embodiment substantially corresponds to the lower representation of FIG. 4. It can be seen that between the plane forming the base surface 28a and the plane forming the base surface 28b a non-tangential transition U2 and between the plane forming the base surface 28b and the base surface 28c forming a non-tangent transition U3 is provided. It can also be seen that these transitions U2 and U3 are each provided in the extension region of a diffuser blade 25 and that consequently no transitions are necessary within the planes forming the base surfaces. The flow direction of the fluid through the diffuser passages is again denoted by the reference numeral 29.
  • FIG. 6 shows an enlarged view of a portion of FIG. 5.
  • the transition U3 between the plane forming the base surface 28b and the plane forming the base surface 28c is illustrated. It can be seen that this transition U3 is provided in the extension area of a diffuser blade 25.
  • FIG. 7 shows a sectional view for illustrating the structure of a diffuser according to the invention.
  • a non-cut diffuser vane 25 a cut portion of a plane forming the bottom surface 28b, a cut portion of the obliquely extending base plate 23a of the diffuser, as shown in Figure 7 below the bottom surface 28b, are a cut portion of the diffuser cavity provided in this side wall 27 and the flow direction 29 of the fluid are shown.
  • the bases of the diffuser passages are inclined in the flow direction 29, in particular drop off linearly.
  • the base areas of the diffuser passages fall off in a curve radius or in a free-form surface.
  • FIG. 8 shows a sketch to illustrate a second embodiment of the invention.
  • This second embodiment corresponds essentially to the upper illustration of FIG. 4. It can be seen that between the plane forming the base surface 28a and the plane forming the base surface 28b a non-tangential transition U2 'and between the plane forming the base surface 28b and the base surface 28c forming plane is a non-tangent transition U3 'is provided. It can also be seen that these transitions U2 'and U3' each within a diffuser blade 25th are provided and that consequently no transitions are necessary within the planes forming the bases.
  • the present invention after all, defines the divergence angle along the streamline within the diffuser passages, which roughly corresponds to the toolpath and does not represent a straight line in the turbocharger axial plane, but a curve of variable curvature. This results in a tangent-discontinuity between the bases of adjacent diffuser passages. This discontinuity is placed according to the present invention in the extension area of a diffuser vane bounding the diffuser passage or in a diffuser vane bounding the diffuser passage. As a result, efficiency losses are minimized.
  • FIG. 9 shows an alternative embodiment in which non-tangent transitions U4 and U5 are provided in the base surfaces of the diffuser blades provided between the two adjacent diffuser blades 25.
  • the total of n diffuser blades are milled on planes which are not purely radial, so that an n-flat is produced in the diffuser base plate.
  • the diffuser blades are prismatically flank-milled and perpendicular to the respective plane. Since the bases are not purely radial, there are discontinuous transitions, which can be rounded if necessary with additional milling paths. Furthermore, the discontinuities at the entrance and exit edges of the diffuser plate can be further uniformed by rotary operations. This procedure allows flank milling of prismatic diffuser vanes whose axis is not parallel to the rotor axis of the turbocharger. By these measures, the production cost is reduced compared to point milled diffusers.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un diffuseur destiné à un compresseur et comportant : - un canal d'écoulement qui est délimité dans le sens de l'écoulement par une première paroi latérale et une seconde paroi latérale, lesdites parois latérales s'étendant de manière au moins partiellement divergente l'une par rapport à l'autre, et une des parois présentant une plaque de base (23a) de diffuseur dont la surface extérieure faisant face au canal d'écoulement (23) ne s'étend pas en direction radiale, - une couronne d'aubes de diffuseur munie d'un certain nombre d'aubes de diffuseur à distance les unes des autres qui sont agencées au moins partiellement dans le canal d'écoulement, chacune des aubes de diffuseur présentant un côté pression et un côté aspiration, - et un certain nombre de passages de diffuseur, chaque passage de diffuseur étant agencé entre deux aubes de diffuseur voisines et présentant une surface de base entre les deux aubes de diffuseur voisines. Une transition non continuellement tangentielle est ménagée entre un premier plan formé par la surface de base d'un premier passage de diffuseur et un second plan formé par la surface de base d'un second passage de diffuseur voisin, ou une transition non continuellement tangentielle est ménagée dans la surface de base du passage de diffuseur présente entre les deux aubes de diffuseur voisines.
PCT/EP2018/075355 2017-09-28 2018-09-19 Diffuseur pour compresseur Ceased WO2019063384A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017122524.2 2017-09-28
DE102017122524.2A DE102017122524A1 (de) 2017-09-28 2017-09-28 Diffusor für einen Verdichter

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Publication Number Publication Date
WO2019063384A1 true WO2019063384A1 (fr) 2019-04-04

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PCT/EP2018/075355 Ceased WO2019063384A1 (fr) 2017-09-28 2018-09-19 Diffuseur pour compresseur

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WO (1) WO2019063384A1 (fr)

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CN112943700A (zh) * 2021-02-25 2021-06-11 上海汽车集团股份有限公司 一种发动机及其离心式压气机、叶片扩压器
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
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

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DE102017101590A1 (de) * 2017-01-27 2018-08-02 Man Diesel & Turbo Se Radialverdichter und Turbolader
DE102018115446A1 (de) * 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh Abgasturbolader
GB202019182D0 (en) * 2020-12-04 2021-01-20 Cummins Ltd Compressor
WO2022117215A1 (fr) 2020-12-04 2022-06-09 Cummins Ltd Agencement d'aube, compresseur, programme informatique, et procédés de fabrication et de conception associés
DE102022118713A1 (de) 2022-07-26 2024-02-01 Rolls-Royce Solutions GmbH Verdichteranordnung, Turbolader und Brennkraftmaschine

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