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 PDFInfo
- 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
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 32
- 238000004519 manufacturing process Methods 0.000 title claims description 16
- 239000011159 matrix material Substances 0.000 claims abstract description 15
- 238000003754 machining Methods 0.000 claims description 18
- 238000000280 densification Methods 0.000 claims description 17
- 238000000034 method Methods 0.000 claims description 13
- 230000008569 process Effects 0.000 claims description 6
- 230000003247 decreasing effect Effects 0.000 claims description 5
- 238000004804 winding Methods 0.000 claims description 3
- 230000000712 assembly Effects 0.000 claims 1
- 238000000429 assembly Methods 0.000 claims 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 4
- 229910052799 carbon Inorganic materials 0.000 abstract description 4
- 239000000835 fiber Substances 0.000 abstract description 4
- 239000000919 ceramic Substances 0.000 abstract description 3
- 239000012071 phase Substances 0.000 description 15
- 239000000463 material Substances 0.000 description 8
- 230000008901 benefit Effects 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 6
- 230000002787 reinforcement Effects 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- IUHFWCGCSVTMPG-UHFFFAOYSA-N [C].[C] Chemical class [C].[C] IUHFWCGCSVTMPG-UHFFFAOYSA-N 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 239000011153 ceramic matrix composite Substances 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 241000940835 Pales Species 0.000 description 2
- 206010033546 Pallor Diseases 0.000 description 2
- 238000007596 consolidation process Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000008595 infiltration Effects 0.000 description 2
- 238000001764 infiltration Methods 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 239000002243 precursor Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 229910010271 silicon carbide Inorganic materials 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000011282 treatment Methods 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- CREMABGTGYGIQB-UHFFFAOYSA-N carbon carbon Chemical compound C.C CREMABGTGYGIQB-UHFFFAOYSA-N 0.000 description 1
- 239000011203 carbon fibre reinforced carbon Substances 0.000 description 1
- 210000004027 cell Anatomy 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000005470 impregnation Methods 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
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- 230000007935 neutral effect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 239000012808 vapor phase Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Composite Materials (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9510205A FR2738303B1 (fr) | 1995-08-30 | 1995-08-30 | Turbine en materiau composite thermostructural, en particulier a petit diametre, et procede pour sa fabrication |
FR9510205 | 1995-08-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0761977A1 true EP0761977A1 (de) | 1997-03-12 |
EP0761977B1 EP0761977B1 (de) | 2001-01-17 |
Family
ID=9482159
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
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) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
Families Citing this family (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FI101565B1 (fi) * | 1997-01-17 | 1998-07-15 | Flaekt Oy | 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 |
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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 |
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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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US7322793B2 (en) | 2002-07-22 | 2008-01-29 | Behr Systems, Inc. | Turbine motor of a rotary atomizer |
EP1384516A3 (de) * | 2002-07-22 | 2008-03-12 | Dürr Systems GmbH | Turbinenmotor eines Rotationszerstäubers |
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 |
Also Published As
Publication number | Publication date |
---|---|
JP3484299B2 (ja) | 2004-01-06 |
DE69611582T2 (de) | 2001-08-23 |
US5775878A (en) | 1998-07-07 |
DE69611582D1 (de) | 2001-02-22 |
FR2738303A1 (fr) | 1997-03-07 |
UA28036C2 (uk) | 2000-10-16 |
ES2155178T3 (es) | 2001-05-01 |
JPH09125901A (ja) | 1997-05-13 |
US6029347A (en) | 2000-02-29 |
FR2738303B1 (fr) | 1997-11-28 |
RU2141564C1 (ru) | 1999-11-20 |
EP0761977B1 (de) | 2001-01-17 |
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