EP1462617A2 - Schaufelanordnung für eine axiale Turbomaschine - Google Patents
Schaufelanordnung für eine axiale Turbomaschine Download PDFInfo
- Publication number
- EP1462617A2 EP1462617A2 EP04101062A EP04101062A EP1462617A2 EP 1462617 A2 EP1462617 A2 EP 1462617A2 EP 04101062 A EP04101062 A EP 04101062A EP 04101062 A EP04101062 A EP 04101062A EP 1462617 A2 EP1462617 A2 EP 1462617A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- blades
- rotor
- intermetallic
- blade
- turbomachine
- 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
- 239000000463 material Substances 0.000 claims abstract description 20
- 229910021324 titanium aluminide Inorganic materials 0.000 claims description 13
- 229910000831 Steel Inorganic materials 0.000 claims description 12
- 239000010959 steel Substances 0.000 claims description 12
- 229910045601 alloy Inorganic materials 0.000 claims description 11
- 239000000956 alloy Substances 0.000 claims description 11
- 229910000765 intermetallic Inorganic materials 0.000 claims description 8
- OQPDWFJSZHWILH-UHFFFAOYSA-N [Al].[Al].[Al].[Ti] Chemical compound [Al].[Al].[Al].[Ti] OQPDWFJSZHWILH-UHFFFAOYSA-N 0.000 claims description 7
- 239000000203 mixture Substances 0.000 claims description 5
- 239000000126 substance Substances 0.000 claims description 5
- 229910000601 superalloy Inorganic materials 0.000 claims description 5
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000002347 wear-protection layer Substances 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 239000002184 metal Substances 0.000 abstract 1
- 230000002093 peripheral effect Effects 0.000 abstract 1
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 6
- 208000016261 weight loss Diseases 0.000 description 5
- 150000001875 compounds Chemical class 0.000 description 4
- 229910001220 stainless steel Inorganic materials 0.000 description 4
- 239000010936 titanium Substances 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000000704 physical effect Effects 0.000 description 3
- 239000010935 stainless steel Substances 0.000 description 3
- 239000013585 weight reducing agent Substances 0.000 description 3
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 2
- 229910004349 Ti-Al Inorganic materials 0.000 description 2
- 229910010038 TiAl Inorganic materials 0.000 description 2
- 229910004692 Ti—Al Inorganic materials 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 239000011151 fibre-reinforced plastic Substances 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000004035 construction material Substances 0.000 description 1
- 239000002019 doping agent Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000001513 hot isostatic pressing Methods 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 239000003562 lightweight material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 230000004580 weight loss Effects 0.000 description 1
- 229910006281 γ-TiAl Inorganic materials 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
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
-
- 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
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- 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
- F05D2300/50—Intrinsic material properties or characteristics
Definitions
- the invention relates to the field of power plant technology. It affects an axially flowed thermal turbomachine according to the preamble of claim 1, which compared to the known state of the Technology has a reduced rotor weight.
- Thermal turbomachinery e.g. B. high pressure compressor for gas turbines or Turbines consist essentially of a rotor equipped with blades Rotor and a stator, in which guide vanes are suspended.
- the Blades and the guide blades each have a blade and a blade root.
- Around the blades on the rotor or in the stator to be able to fasten are grooves in the stator and on the rotor shaft stabbed. The feet of the guide and rotor blades are in these grooves inserted and locked there.
- the fixed guide vanes are responsible for the flow of the compressing or to relax the gaseous medium so on the rotating barrel blading to direct that energy conversion with best possible efficiency.
- blades in one piece from a single material, e.g. B. from stainless steel for gas turbine compressors or made of a nickel-based superalloy for gas turbines, to manufacture and with these Shovels to fill a row of shovels.
- Such blades are hereinafter referred to as conventional blades.
- the average mass is one Bucket row limited by the load capacity of the rotor.
- a rotor with integral blading in particular for an engine, disclosed on the circumferentially rotor blades are arranged, the rotor blade for Reduction of vibrations of a metallic blade root, one metallic airfoil section, the at least part of the Blade front edge and the adjacent area of the Blade surface forms, and an airfoil made of fiber-reinforced plastic exhibit.
- the blade is attached Plastic on the metallic airfoil section by gluing / riveting or by clamping.
- EP 0 513 407 B1 describes a turbine blade made of an alloy known on the basis of a dopant-containing gamma titanium aluminide, which are made of airfoil, blade root and if necessary Bucket shroud consists.
- the Castings are partially heat-treated and thermoformed so that the The airfoil subsequently has a coarse-grained structure that is too high Tensile and creep rupture strength leads, and that the blade root and / or that Bucket shroud has a fine grain structure that opposes one leads to increased ductility of the airfoil.
- blades advantageously have the mass the rotor lowered, but a disadvantage of this prior art is that the tips of the blades burst due to their brittleness when they are in use during operation come into contact with the stator. That friction is usually not preventing.
- the aim of the invention is to overcome the disadvantages of the prior art avoid.
- the invention is based on the object of a thermal Turbomachine to develop, which on the one hand by a reduced Total weight of the rotor, and on the other hand Blade brittle fracture is prevented, so that the life of the machine is increased.
- this object is achieved in a thermal turbomachine according to the preamble of claim 1 solved in that at least two equally spaced blades made from a more ductile one Material in a row of blades between the intermetallic blades are arranged, the blades of the more ductile material either are significantly longer than the intermetallic blades or the same Length of a different blade tip shape than the intermetallic blades exhibit.
- the advantages of the invention are that by using the Paddles made of intermetallic compounds on the one hand the weight of the Rotors is reduced, increasing the life of the rotor Rotor / blade connection leads and on the other hand the brittleness of the Intermetallic blades do not pose an increased risk to the operation of the machine means that the blades arranged in the same blade row are made of absorb the friction / wear forces of the more ductile material.
- intermetallic blades and the Intermediate pieces made of an intermetallic ⁇ -TiAl compound or intermetallic orthorhombic TiAl compound exist because of this Material use according to the invention for a considerable weight reduction of the rotor.
- the specific density of the intermetallic titanium aluminide compounds is z. B. only about 50% of the density of stainless Cr-Ni-W steel.
- the blade tips are hard Phase coated or a laser welding Wear protection layer is applied to grind off the To prevent blade tips or to reduce the frictional force.
- Fig. 1 shows a cross section through a schematically shown Blade row of a rotor 1 for a high pressure compressor Gas turbine.
- the rotor 1 is surrounded by a stator 2.
- blades 3, 3 'are mounted in a circumferential groove therein, while guide vanes (not shown here) are suspended in the stator 2.
- the Blades 3, 3 'are for example, at a pressure of approximately 32 bar a temperature of around 600 ° C for several thousand hours exposed.
- the row of blades shown has two different ones Types of blades 3, 3 'equipped.
- the blades 3 ' are made of one more ductile material, such as a stainless Cr-Ni steel, than that Material for the blades 3 made.
- At least two evenly spaced such ductile blades 3 (According to FIG. 1, these are in present embodiment four pieces) are in the row of blades the intermetallic blades 3 arranged.
- the blades 3 'from the more ductile material in this embodiment are significantly longer than the intermetallic blades 3, d. H.
- the rotor blades 3 ′ consist of a stainless steel with the following chemical composition (in% by weight): 0.12 C, ⁇ 0.8 Si, ⁇ 1.0 Mn, 17 Cr, 14.5 Ni, ⁇ 0.5 Mo, 3.3 W, ⁇ 1 Ti, ⁇ 0.045 P, ⁇ 0.03 S, balance Fe.
- the shaft of the rotor 1 is also made of steel. As is known, the density of steel is approximately 7.9 g / cm 3 .
- the intermetallic compound from which the rotor blades 3 are made has the following chemical composition (in% by weight): Ti (30.5-31.5) Al- (8.9-9.5) W- (0.3-0.4) Si.
- the density of this alloy is advantageously only 4 g / cm 3 , so that the rotor 1 according to the invention is considerably lighter than a rotor with exclusively conventional steel blades.
- Fig. 2 shows a further embodiment of the invention in a Detailed display.
- the weight of the rotor 1 can also be reduced if - as shown in Fig. 2 - between two neighboring Blades of a row of blades of the rotor 1 each intermediate pieces 4 an intermetallic compound, here a ⁇ -titanium aluminide compound, are mounted in the circumferential groove of the rotor 1.
- the intermetallic used for the manufacture of the intermediate pieces 4 Compound has the same chemical composition as that for the Paddles 3 used and described connection.
- Intermetallic compounds of titanium with aluminum have some interesting properties which they as construction materials in make the middle and higher temperature range appear attractive. This includes theirs compared to superalloys and stainless Steels lower density. Their technical usability is in the this form often counteracts their brittleness.
- the intermetallic ⁇ -titanium aluminide compound described above is distinguished is about 50% less dense than this Embodiment for the rotor 1 and the blades 3 'steel used. It also has a modulus of elasticity of 171 GPa and at room temperature a thermal conductivity ⁇ of 24 W / mK.
- the weight reduction of the rotor 1 according to the invention has an effect advantageous to increase the life of the machine. It will the stresses in the blade root fixation in the rotor 1 are reduced.
- the manufacture of the intermetallic blades 3 and the intermediate pieces 4 takes place in a known manner by casting, hot isostatic pressing and Heat treatment with minimal post-processing.
- FIG. 3 A further preferred embodiment variant is shown in FIG. 3. It will a rotor blade 3 is shown, the blade tip 5 of which is coated.
- the blade tip can be coated with a hard phase or a wear protection layer can be created by means of laser welding be applied. In both cases, the grinding of the Avoid blade tips or reduce the frictional force.
- an orthorhombic titanium-aluminide alloy with a density of 4.55 g / cm 3 can also be used as the material for the intermetallic blades 3 or the intermediate pieces 4.
- Orthorhombic titanium aluminide alloys are based on the ordered compound Ti 2 AlNb and have the following chemical composition in (% by weight): Ti- (22-27) Al- (21-27) Nb.
- the intermediate pieces 4 can also be made of a cheaper titanium alloy instead of an intermetallic ⁇ -titanium aluminide compound, in which case the weight reduction is not quite as great.
- the invention not only for High pressure compressor rotors is used, but also for Turbine rotors with turbine blades made of known turbine steel, heat-resistant steel or from a super alloy, for example a nickel-based super alloy, where the intermediate pieces between the Blades made of an intermetallic ⁇ -titanium aluminide alloy or an intermetallic orthorhombic titanium aluminide alloy. Weight reductions and an increase can also be advantageous with this reach the life of the machine.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- Fig. 1
- einen Querschnitt durch eine Laufschaufelreihe eines schematisch dargestellten erfindungsgemässen Hochdruckverdichters in einer ersten Ausführungsvariante;
- Fig. 2
- ein Detail einer zweiten Ausführungsvariante der Erfindung, bei welcher zwischen den Laufschaufeln Zwischenstücke aus intermetallischen Verbindungen im Rotor angeordnet sind und
- Fig. 3
- eine TiAl-Schaufel mit einer beschichteten Schaufelspitze als dritte Ausführungsvariante der Erfindung.
Physikalische Eigenschaften der verschiedenen Werkstoffe | ||
Dichte in g/cm3 | Wärmeausdehnungskoeffizient in K-1 | |
γ-Ti-Al | 4 | 10 x 10-6 |
Rostfreier Stahl | 7.9 | 18.6 x 10-6 |
- 1
- Rotor
- 2
- Stator
- 3, 3'
- Laufschaufel
- 4
- Zwischenstück
- 5
- Schaufelspitze
Claims (8)
- Axial durchströmte thermische Turbomaschine mit einem metallischen Rotor (1), bei welchem in einer Umfangsnut Laufschaufeln (3) aus einer intermetallischen Verbindung zu einer Schaufelreihe montiert sind, dadurch gekennzeichnet, dass mindestens zwei gleichmässig voneinander beabstandete Laufschaufeln (3') aus einem duktileren Material in der besagten Schaufelreihe zwischen den intermetallischen Laufschaufeln (3) angeordnet sind, wobei die Laufschaufeln (3') aus dem duktileren Material entweder deutlich länger sind als die intermetallischen Schaufeln (3) oder bei gleicher Länge eine andere Schaufelspitzenform als die intermetallischen Schaufeln (3) aufweisen.
- Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, dass zusätzlich zwischen benachbarten Laufschaufeln (3, 3') einer Schaufelreihe Zwischenstücke (4) aus einem leichteren Material als das Material des Rotors (1), vorzugsweise aus einer intermetallischen Verbindung oder einer Titanlegierung, angeordnet sind.
- Turbomaschine nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die intermetallische Verbindung für die Laufschaufeln (3) und die Zwischenstücke (4) eine γ-Titan-Aluminid-Legierung oder eine orthorhombischen Titan-Aluminid-Legierung ist.
- Turbomaschine nach Anspruch 3, dadurch gekennzeichnet, dass die γ-Titan-Aluminid-Legierung folgende chemische Zusammensetzung (in Gew.-%) aufweist: Ti-(30.5-31.5)Al-(8.9-9.5)W-(0.3-0.4)Si.
- Turbomaschine nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Schaufelspitzen (5) der Laufschaufeln (3) mit einer harten Phase beschichtbar sind.
- Turbomaschine nach Anspruch 5, dadurch gekennzeichnet, dass mittels Laser-Schweissung eine Verschleissschutzschicht auf die Schaufelspitzen aufbringbar ist.
- Turbomaschine nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Turbomaschine ein Hochdruckverdichter einer Gasturbine mit einem Rotor (1) ist, welcher im wesentlichen aus einem rostfreien Cr-Ni-Stahl besteht.
- Turbomaschine nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die im Vergleich zu den intermetallischen Laufschaufeln (3) duktileren Laufschaufeln (3') aus einem rostfreien Cr-Ni-Stahl oder einem warmfesten Turbinenschaufelstahl oder einer Superlegierung bestehen.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10313489 | 2003-03-26 | ||
DE10313489A DE10313489A1 (de) | 2003-03-26 | 2003-03-26 | Axial durchströmte thermische Turbomaschine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1462617A2 true EP1462617A2 (de) | 2004-09-29 |
EP1462617A3 EP1462617A3 (de) | 2006-11-15 |
EP1462617B1 EP1462617B1 (de) | 2012-09-19 |
Family
ID=32798100
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04101062A Expired - Lifetime EP1462617B1 (de) | 2003-03-26 | 2004-03-16 | Schaufelanordnung für eine axiale Turbomaschine |
Country Status (4)
Country | Link |
---|---|
US (1) | US7048507B2 (de) |
EP (1) | EP1462617B1 (de) |
JP (1) | JP4638681B2 (de) |
DE (1) | DE10313489A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1746249A3 (de) * | 2005-07-22 | 2009-01-07 | United Technologies Corporation | Fanrotor |
EP2573326A1 (de) * | 2011-09-23 | 2013-03-27 | United Technologies Corporation | Schaufelspitzendichtungsanordnung |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE502006003197D1 (de) * | 2005-07-12 | 2009-04-30 | Alstom Technology Ltd | Keramische wärmedämmschicht |
ATE553284T1 (de) * | 2007-02-05 | 2012-04-15 | Siemens Ag | Turbinenschaufel |
US8100641B2 (en) * | 2008-09-09 | 2012-01-24 | General Electric Company | Steam turbine having stage with buckets of different materials |
DE102009030398A1 (de) * | 2009-06-25 | 2010-12-30 | Mtu Aero Engines Gmbh | Verfahren zum Herstellen und/oder Reparieren einer Schaufel für eine Strömungsmaschine |
ES2583756T3 (es) * | 2011-04-01 | 2016-09-22 | MTU Aero Engines AG | Disposición de álabes para una turbomáquina |
US10309232B2 (en) * | 2012-02-29 | 2019-06-04 | United Technologies Corporation | Gas turbine engine with stage dependent material selection for blades and disk |
US9429023B2 (en) * | 2013-01-14 | 2016-08-30 | Honeywell International Inc. | Gas turbine engine components and methods for their manufacture using additive manufacturing techniques |
US20150093237A1 (en) * | 2013-09-30 | 2015-04-02 | General Electric Company | Ceramic matrix composite component, turbine system and fabrication process |
FR3018849B1 (fr) * | 2014-03-24 | 2018-03-16 | Safran Aircraft Engines | Piece de revolution pour un rotor de turbomachine |
US10378366B2 (en) * | 2015-04-17 | 2019-08-13 | Mitsubishi Hitachi Power Systems, Ltd. | Steam turbine rotor blade and method for manufacturing steam turbine rotor blade |
US10774668B2 (en) * | 2017-09-20 | 2020-09-15 | General Electric Company | Intersage seal assembly for counter rotating turbine |
DE102017221641A1 (de) * | 2017-12-01 | 2019-06-06 | MTU Aero Engines AG | Schaufelkranz mit mischbeschaufelung |
US11299993B2 (en) | 2019-10-28 | 2022-04-12 | Honeywell International Inc. | Rotor assembly for in-machine grinding of shroud member and methods of using the same |
US20230235680A1 (en) * | 2022-01-26 | 2023-07-27 | General Electric Company | Non-uniform turbomachinery blade tips for frequency tuning |
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DE1426816A1 (de) * | 1963-07-02 | 1969-03-13 | Licentia Gmbh | Verfahren zur Herstellung eines Schaufelkranzes einer Axialstroemungsmaschine,insbesondere eines Axialverdichters |
US4671735A (en) * | 1984-01-19 | 1987-06-09 | Mtu-Motoren-Und Turbinen-Union Munchen Gmbh | Rotor of a compressor, more particularly of an axial-flow compressor |
US5299353A (en) * | 1991-05-13 | 1994-04-05 | Asea Brown Boveri Ltd. | Turbine blade and process for producing this turbine blade |
US5474421A (en) * | 1993-07-24 | 1995-12-12 | Mtu Motoren- Und Turbinen- Union Muenchen Gmbh | Turbomachine rotor |
DE4439726A1 (de) * | 1994-11-09 | 1996-05-15 | Siemens Ag | Laufrad für eine Strömungsmaschine |
US5910376A (en) * | 1996-12-31 | 1999-06-08 | General Electric Company | Hardfacing of gamma titanium aluminides |
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US6092989A (en) * | 1992-08-06 | 2000-07-25 | Hitachi, Ltd. | Compressor for turbine and gas turbine |
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GB9606963D0 (en) * | 1996-04-02 | 1996-06-05 | Rolls Royce Plc | A root attachment for a turbomachine blade |
DE19751129C1 (de) | 1997-11-19 | 1999-06-17 | Mtu Muenchen Gmbh | FAN-Rotorschaufel für ein Triebwerk |
DE19756354B4 (de) * | 1997-12-18 | 2007-03-01 | Alstom | Schaufel und Verfahren zur Herstellung der Schaufel |
DE10110102C2 (de) | 2000-12-18 | 2002-12-05 | Deutsch Zentr Luft & Raumfahrt | Rotorschaufel |
-
2003
- 2003-03-26 DE DE10313489A patent/DE10313489A1/de not_active Withdrawn
-
2004
- 2004-03-16 EP EP04101062A patent/EP1462617B1/de not_active Expired - Lifetime
- 2004-03-22 JP JP2004083410A patent/JP4638681B2/ja not_active Expired - Fee Related
- 2004-03-25 US US10/808,492 patent/US7048507B2/en not_active Expired - Lifetime
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1426816A1 (de) * | 1963-07-02 | 1969-03-13 | Licentia Gmbh | Verfahren zur Herstellung eines Schaufelkranzes einer Axialstroemungsmaschine,insbesondere eines Axialverdichters |
US4671735A (en) * | 1984-01-19 | 1987-06-09 | Mtu-Motoren-Und Turbinen-Union Munchen Gmbh | Rotor of a compressor, more particularly of an axial-flow compressor |
US5299353A (en) * | 1991-05-13 | 1994-04-05 | Asea Brown Boveri Ltd. | Turbine blade and process for producing this turbine blade |
US6092989A (en) * | 1992-08-06 | 2000-07-25 | Hitachi, Ltd. | Compressor for turbine and gas turbine |
US5474421A (en) * | 1993-07-24 | 1995-12-12 | Mtu Motoren- Und Turbinen- Union Muenchen Gmbh | Turbomachine rotor |
DE4439726A1 (de) * | 1994-11-09 | 1996-05-15 | Siemens Ag | Laufrad für eine Strömungsmaschine |
US5910376A (en) * | 1996-12-31 | 1999-06-08 | General Electric Company | Hardfacing of gamma titanium aluminides |
US5997248A (en) * | 1998-12-03 | 1999-12-07 | Sulzer Metco (Us) Inc. | Silicon carbide composition for turbine blade tips |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1746249A3 (de) * | 2005-07-22 | 2009-01-07 | United Technologies Corporation | Fanrotor |
EP2573326A1 (de) * | 2011-09-23 | 2013-03-27 | United Technologies Corporation | Schaufelspitzendichtungsanordnung |
Also Published As
Publication number | Publication date |
---|---|
JP4638681B2 (ja) | 2011-02-23 |
EP1462617B1 (de) | 2012-09-19 |
US7048507B2 (en) | 2006-05-23 |
DE10313489A1 (de) | 2004-10-14 |
JP2004293550A (ja) | 2004-10-21 |
US20060073019A1 (en) | 2006-04-06 |
EP1462617A3 (de) | 2006-11-15 |
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