EP0761977A1 - Rotor aus hochtemperaturbeständige Verbundwerkstoff, insbesondere mit kleinem Diameter und sein Herstellungsverfahren - Google Patents

Rotor aus hochtemperaturbeständige Verbundwerkstoff, insbesondere mit kleinem Diameter und sein Herstellungsverfahren Download PDF

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Publication number
EP0761977A1
EP0761977A1 EP96401835A EP96401835A EP0761977A1 EP 0761977 A1 EP0761977 A1 EP 0761977A1 EP 96401835 A EP96401835 A EP 96401835A EP 96401835 A EP96401835 A EP 96401835A EP 0761977 A1 EP0761977 A1 EP 0761977A1
Authority
EP
European Patent Office
Prior art keywords
blades
turbine
flange
composite material
preform
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.)
Granted
Application number
EP96401835A
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English (en)
French (fr)
Other versions
EP0761977B1 (de
Inventor
Jean-Pierre Maumus
Guy Martin
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Europeenne de Propulsion SEP SA
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 Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA
Publication of EP0761977A1 publication Critical patent/EP0761977A1/de
Application granted granted Critical
Publication of EP0761977B1 publication Critical patent/EP0761977B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49325—Shaping integrally bladed rotor

Definitions

  • the present invention relates to turbines, and more particularly those intended to operate at high temperatures, typically above 1000 ° C.
  • these turbines are made of metal, generally made up of several elements assembled by welding.
  • the use of metal has several drawbacks.
  • the high mass of the rotating parts requires large shaft lines and very powerful motors and imposes anyway a limitation of the speed of rotation.
  • a temperature limitation is added due to the risk of metal creep.
  • the sensitivity of the metal to thermal shock can cause cracks or deformation. This results in imbalances in the rotating mass favoring a reduction in the service life of the turbines and their drive motors.
  • significant thermal shocks can occur, in particular in the event of massive injection of a cold gas, to cause the temperature to drop rapidly inside an oven in order to reduce the duration treatment cycles.
  • thermostructural composite materials In order to avoid the problems encountered with metals, other materials have already been proposed for making turbines, in particular thermostructural composite materials. These materials generally consist of a fibrous reinforcement texture, or preform, densified by a matrix and are characterized by their mechanical properties which make them suitable for constituting structural elements and by their capacity to maintain these properties up to high temperatures.
  • thermostructural composite materials are carbon-carbon composites (CC) made of carbon fiber reinforcement and a carbon matrix, and ceramic matrix composites (CMC) made of carbon fiber reinforcement carbon or ceramic and a ceramic matrix.
  • thermostructural composite materials Compared to metals, thermostructural composite materials have the essential advantages of a much lower density and great stability at high temperatures. The reduction in mass and the elimination of risk of creep can allow high speeds of rotation and, by the same token, very high ventilation rates without requiring oversizing of the drive members. In addition, thermostructural composite materials have a very high resistance to thermal shock.
  • Thermostructural composite materials therefore have significant performance advantages, but their use is limited due to their fairly high cost. In addition to the materials used, the cost comes essentially from the difficulties encountered in producing fibrous preforms, in particular when the parts to be manufactured have complex shapes, which is the case with turbines, and by the duration of the densification cycles.
  • an object of the present invention is to provide a turbine architecture particularly suited to its production in thermostructural composite material in order to benefit from the advantages of this material but with a manufacturing cost as reduced as possible.
  • the turbine is for its essential part formed of only two parts, which simplifies assembly, and each part is produced from a fibrous preform having a simple shape.
  • This is so for the second part, since it simply forms a flange, so that the second fibrous preform can be constituted by a plate.
  • the first part it is produced by machining from a first preform constituted by a plate.
  • the first fibrous preform is machined in the consolidated state, partially densified, and the densification by the matrix is continued after machining.
  • small diameter turbine here is meant a turbine whose diameter of the outer ring does not exceed about 500 mm.
  • the turbine is assembled only by mutual tightening of the first part and the second part at their central parts. It has been found that this single tightening ensures the assembly of the turbine in all operating configurations, thanks to the rigidity of the composite material. This is all the more true as the diameter of the turbine is smaller. It is therefore not necessary to use clamping elements of the screw type entering the two parts. This is an important advantage because, otherwise, the hardware used should have been made of composite material, to withstand high temperatures and have a coefficient of thermal expansion compatible with that of the assembled parts, which would have increased the cost so significant.
  • the fiber preforms are produced using techniques known per se.
  • the first fibrous preform, as well as the second can be produced from a flat stack of strata of a two-dimensional fibrous texture and bonding of the strata together by needling.
  • the first fibrous preform can be produced from a winding of a strip of two-dimensional fibrous texture in superimposed layers and bonding of the layers to each other by needling.
  • the invention relates to a turbine comprising a plurality of blades arranged between two flanges and delimiting circulation passages between an inner ring and an outer ring, the blades and flanges being of thermostructural composite material, the turbine being characterized in that it comprises a first and a second part, each made in a single monobloc part of thermostructural composite material, the first part forming a first flange and the blades, while the second part forms the second applied flange against the blades of the first part.
  • FIG. 1 illustrates in section a turbine 10 comprising two monoblock parts 20, 30 of thermostructural composite material assembled by mutual clamping on a shaft 12.
  • the material constituting the parts 20 and 30 is for example a carbon-carbon composite material (CC) or a ceramic matrix composite material such as a C-SiC composite material (carbon fiber reinforcement and silicon carbide matrix).
  • the part 20 (FIGS. 1 to 3) comprises a plurality of blades 22 which are located on an internal face 24a of an annular flange 24 in the form of a disc.
  • the blades 22 extend between the outer circumference and the inner circumference of the flange 24, substantially perpendicular thereto.
  • the heels 22 has blades 22 are connected to a central part forming a hub 26 whose inner diameter is substantially less than that of the flange 24.
  • the hub 26 also has a thickness less than the length of the blades 22, and is spaced from the flange 24, along the axis a of the turbine, so that the outer face 24b of the flange, on the one hand, and the external face 26 b of the hub with the longitudinal edges 22b of the blades 22, on the other hand, form the opposite faces of the part 20.
  • the part 30 constitutes an annular flange in the form of a disc whose external diameter is equal to that of the flange 24 and whose internal diameter is equal to that of the hub 26.
  • the part 30 is applied against the external face 26b of the hub 26 and against the longitudinal edges 22b of the blades 22.
  • the mutual tightening of the parts 20 and 30 is carried out by locking between a shoulder 12a of the shaft 12 and a ring 14, at by means of a nut 15.
  • the suction by the turbine is carried out from the space 16 which is located between the flange 24 and the hub 26, and is surrounded by the inner ring 17 of the turbine at the feet of the blades 22.
  • the ejection of the sucked fluid is carried out through the outer ring 19 of the turbine at the ends of the blades 22, after circulation through the passages 18 delimited by the blades 22 and the flanges 24 and 30.
  • thermostructural composite material means that the only clamping force at the level of the central parts of the parts 20 and 30 is sufficient to keep them assembled, including during the operation of the turbine, no detachment being observed. As already indicated, this is all the more true since the present invention applies preferably to turbines of small diameter, that is to say of external diameter not exceeding about 500 mm.
  • the surfaces of the hub 26 and of the flange 30 on which the shoulder 12a and the ring 14 are supported have a frustoconical shape, as do the corresponding faces of the shoulder 12a and of the ring 14
  • These frustoconical bearing faces have substantially coincident vertices located on the axis A of the turbine.
  • the part 20 is produced from a fibrous structure in the form of a plate 200 (phase 41).
  • a fibrous structure is manufactured by example by flat stacking of layers of two-dimensional fibrous texture, such as sheet of wires or cables, fabric, etc., and bonding of the layers between them by needling.
  • a process for manufacturing such fibrous structures is described in document FR-A-2 584 106.
  • a first preform 201 of annular shape is cut from the plate 200, the dimensions of the preform 201 being chosen as a function of those of the part 20 to be produced (phase 42).
  • the preform 201 is subjected to a first stage of densification by the matrix of the thermostructural composite material to be produced (phase 43). Densification is carried out so as to consolidate the preform, that is to say to bond together the fibers of the preform sufficiently to allow the handling and machining of the consolidated preform. Densification is carried out in a manner known per se by chemical vapor infiltration, or by liquid, that is to say impregnation with a precursor of the matrix in the liquid state and transformation of the precursor.
  • the consolidated preform is subjected to a first machining phase during which the blades are formed from one face of the preform (phase 44), then to a second machining phase during which it is hollowed out. its center from the opposite face, so as to form the suction zone while leaving the hub part (phase 45).
  • the consolidated and machined preform 202 is then subjected to one or more densification cycles until the desired degree of densification by the matrix is obtained (phase 46).
  • phase 47 The preform thus finally densified is subjected to a final machining to bring it to the precise dimensions of the part 20 (phase 47).
  • the preform of the part 20 is produced from a cylindrical fibrous structure 200 ′ produced by winding a strip of two-dimensional fibrous texture in layers superimposed on a mandrel and bonding of the layers together by needling (phase 51).
  • a process for manufacturing fibrous structures of this type is described in document FR-A-2 584 107.
  • Preforms 201 'of annular shape are cut from the cylindrical structure 200' along radial planes (phase 52).
  • Each preform 201 ′ is then treated in the same way as the preform 201 in FIG. 4.
  • the part 30 is produced from a fibrous structure in the form of a plate 300.
  • This structure is for example produced by stacking flat layers of two-dimensional fibrous texture and bonding the strata together by needling ( phase 61).
  • a preform 301 of annular shape is cut from the plate 300, the dimensions of the preform being chosen as a function of those of the part 30 to be produced (phase 62).
  • the preform 301 is densified by the matrix, the densification being carried out by chemical infiltration in the vapor phase or by the liquid route (phase 63).
  • the densified preform is subjected to final machining in order to be brought to the dimensions of the part 30 (phase 64).
  • the turbine 110 of FIG. 7 is essentially formed from two parts 120, 130 of thermostructural composite material. It differs from the turbine of FIG. 1 in that, in part 120, the blades 122 have a decreasing height between the inner ring 117 and the outer ring 119 of the turbine. This decreasing height makes it possible to compensate for the fact that the width of the passages 118 bordered by the blades 122 increases between the inner ring and the outer ring, so that the inlet and outlet sections of the passages 118 are substantially equal.
  • the flange 130 applied against the part 120 then has a disc shape in its central part 130a applied against the hub 126 and a frustoconical shape in its peripheral part applied against the blades 122.
  • the flange 130 For the production of the flange 130, it is possible to start from an annular fibrous preform in the form of a disc which is put into the desired shape by means of a tool, and consolidated by partial densification while being maintained in the tool. After consolidation, the preform can be removed from the tooling to continue densification.
  • the present invention applies more particularly to turbines having relatively small diameters.
  • the flow of the turbine can be increased or decreased, for a given diameter, by increasing or decreasing the height of the passages, that is to say the thickness of the turbine.
  • the loss of material during the machining of the blades being greater the higher their height, it is preferable for cost reasons to limit the thickness of the turbine, for example by not exceeding about 100 mm .
  • a solution for increasing the flow rate then consists in coupling two turbines 10 ', 10 "on the same axis as illustrated in FIG. 8.
  • Each turbine 10', 10" comprises two monobloc pieces of thermostructural composite material, a first piece 20 ', 20 “forming blades 22 ', 22", flange 24', 24 "and hub 26 ', 26", and a second part 30', 30 "forming flange.
  • the turbine 10 ' is similar to the turbine 10 in FIG. 1, while the turbine 10 "is distinguished by the arrangement of the blades.
  • the arrangement of the blades 22" on the part 20 is symmetrical with respect to a radial plane of the arrangement of the blades 22 'on the part 20'.
  • the blades 22 ', 22 define circulation passages oriented in the same way around the axis common to the turbines.
  • the parts 20 ', 30', 30 "and 20" are assembled by mutual tightening on a common shaft 12 'between a shoulder 12'a and a ring 14', by means of a nut 15 '.
  • the surfaces of the hubs 26 'and 26 "on which the shoulder 12' a and the ring 14 'rest have a frustoconical shape, as do the corresponding faces of the shoulder 12'a and the ring 14'.
  • An additional ring 14 "of triangular section is interposed between the flanges 30 'and 30", the surfaces of these bearing on the ring 14 "having a frustoconical shape.
  • the frustoconical bearing surfaces of the flange 30 'on the ring 14 "and of the hub 26' on the shoulder 12'a have substantially coincident vertices situated on the axis of the turbines, as do the bearing surfaces of the flange 30 "on the ring 14" and the hub 26 "on the ring 14 '. In this way, dimensional variations of thermal origin between the parts of the turbines, on the one hand, and the shaft and the clamping rings, on the other hand, can be compensated by sliding parallel to the frustoconical bearing surfaces, in the same way as with the turbine 10 in FIG. 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Composite Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP96401835A 1995-08-30 1996-08-28 Rotor aus hochtemperaturbeständige Verbundwerkstoff, insbesondere mit kleinem Diameter und sein Herstellungsverfahren Expired - Lifetime EP0761977B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9510205 1995-08-30
FR9510205A FR2738303B1 (fr) 1995-08-30 1995-08-30 Turbine en materiau composite thermostructural, en particulier a petit diametre, et procede pour sa fabrication

Publications (2)

Publication Number Publication Date
EP0761977A1 true EP0761977A1 (de) 1997-03-12
EP0761977B1 EP0761977B1 (de) 2001-01-17

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EP96401835A Expired - Lifetime EP0761977B1 (de) 1995-08-30 1996-08-28 Rotor aus hochtemperaturbeständige Verbundwerkstoff, insbesondere mit kleinem Diameter und sein Herstellungsverfahren

Country Status (8)

Country Link
US (2) US5775878A (de)
EP (1) EP0761977B1 (de)
JP (1) JP3484299B2 (de)
DE (1) DE69611582T2 (de)
ES (1) ES2155178T3 (de)
FR (1) FR2738303B1 (de)
RU (1) RU2141564C1 (de)
UA (1) UA28036C2 (de)

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US7322793B2 (en) 2002-07-22 2008-01-29 Behr Systems, Inc. Turbine motor of a rotary atomizer
EP2426313A1 (de) * 2010-09-07 2012-03-07 Chun-Chieh Chen Wandler mit zentrifugalen Impellern
CN103008990A (zh) * 2012-12-10 2013-04-03 成都锦江电子系统工程有限公司 一种微型多维精密切削加工方法
WO2015122799A1 (ru) * 2014-02-11 2015-08-20 Михаил Валерьевич КОШЕЧКИН Газотурбинная установка

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FI101565B (fi) * 1997-01-17 1998-07-15 Flaekt Woods Ab Haihdutinpuhallin ja sen siipipyörä
FI101564B1 (fi) 1997-01-17 1998-07-15 Flaekt Oy Korkeapainepuhallin
DE19708825C2 (de) * 1997-03-05 2001-11-15 Deutsch Zentr Luft & Raumfahrt Vorrichtung zum Fördern eines Mediums
US6511294B1 (en) 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6261056B1 (en) 1999-09-23 2001-07-17 Alliedsignal Inc. Ceramic turbine nozzle including a radially splined mounting surface
US6270310B1 (en) 1999-09-29 2001-08-07 Ford Global Tech., Inc. Fuel pump assembly
US6524070B1 (en) 2000-08-21 2003-02-25 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
DE10042700C2 (de) * 2000-08-31 2002-10-17 Mtu Friedrichshafen Gmbh Verfahren zur plastischen Verformung einer Nabenbohrung eines schnelllaufenden Turbomaschinenteils
US6471474B1 (en) 2000-10-20 2002-10-29 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US6663343B1 (en) 2002-06-27 2003-12-16 Sea Solar Power Inc Impeller mounting system and method
JP4504860B2 (ja) * 2005-04-05 2010-07-14 株式会社丸山製作所 遠心送風機用の羽根車
US20070096589A1 (en) * 2005-10-31 2007-05-03 York Michael T Electric machine rotor fan and pole retention feature
US7687952B2 (en) * 2006-03-30 2010-03-30 Remy Technologies, L.L.C. Brushless alternator with stationary shaft
CN100374686C (zh) * 2006-08-14 2008-03-12 吴法森 聚能脉冲式蒸汽轮机
JP4432989B2 (ja) * 2007-03-16 2010-03-17 ソニー株式会社 遠心羽根車、ファン装置及び電子機器
IT1394295B1 (it) * 2009-05-08 2012-06-06 Nuovo Pignone Spa Girante centrifuga del tipo chiuso per turbomacchine, componente per tale girante, turbomacchina provvista di tale girante e metodo di realizzazione di tale girante
IT1397057B1 (it) 2009-11-23 2012-12-28 Nuovo Pignone Spa Girante centrifuga e turbomacchina
IT1397058B1 (it) 2009-11-23 2012-12-28 Nuovo Pignone Spa Stampo per girante centrifuga, inserti per stampo e metodo per costruire una girante centrifuga
DE102010011486A1 (de) * 2010-03-16 2011-09-22 Bosch Mahle Turbo Systems Gmbh & Co. Kg Rotor für eine Ladeeinrichtung
ITCO20110064A1 (it) * 2011-12-14 2013-06-15 Nuovo Pignone Spa Macchina rotante comprendente un rotore con una girante composita ed un albero metallico
ITCO20130067A1 (it) 2013-12-17 2015-06-18 Nuovo Pignone Srl Girante con elementi di protezione e compressore centrifugo
JP5884844B2 (ja) * 2014-02-21 2016-03-15 株式会社ノーリツ 給湯装置
US9933185B2 (en) * 2014-02-24 2018-04-03 Noritz Corporation Fan and water heater provided with the same, and impeller and water heater provided with the same
US11643948B2 (en) * 2019-02-08 2023-05-09 Raytheon Technologies Corporation Internal cooling circuits for CMC and method of manufacture
CN111975290B (zh) * 2020-07-23 2022-02-25 哈尔滨电气动力装备有限公司 核电主泵叶轮安装工艺

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FR1143291A (fr) * 1954-12-24 1957-09-27 Thomson Houston Comp Francaise Montage d'une roue à aubes
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EP2426313A1 (de) * 2010-09-07 2012-03-07 Chun-Chieh Chen Wandler mit zentrifugalen Impellern
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WO2015122799A1 (ru) * 2014-02-11 2015-08-20 Михаил Валерьевич КОШЕЧКИН Газотурбинная установка

Also Published As

Publication number Publication date
RU2141564C1 (ru) 1999-11-20
FR2738303A1 (fr) 1997-03-07
EP0761977B1 (de) 2001-01-17
JP3484299B2 (ja) 2004-01-06
ES2155178T3 (es) 2001-05-01
DE69611582D1 (de) 2001-02-22
JPH09125901A (ja) 1997-05-13
UA28036C2 (uk) 2000-10-16
FR2738303B1 (fr) 1997-11-28
US6029347A (en) 2000-02-29
US5775878A (en) 1998-07-07
DE69611582T2 (de) 2001-08-23

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