EP1232331B1 - Verfahren zur herstellung eines leichtbauteils in verbundbauweise - Google Patents
Verfahren zur herstellung eines leichtbauteils in verbundbauweise Download PDFInfo
- Publication number
- EP1232331B1 EP1232331B1 EP00988632A EP00988632A EP1232331B1 EP 1232331 B1 EP1232331 B1 EP 1232331B1 EP 00988632 A EP00988632 A EP 00988632A EP 00988632 A EP00988632 A EP 00988632A EP 1232331 B1 EP1232331 B1 EP 1232331B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- core structure
- wall layers
- structural component
- producing
- blade
- 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.)
- Expired - Lifetime
Links
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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F01D5/16—Form or construction for counteracting blade vibration
-
- 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
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/50—Vibration damping features
Definitions
- the invention relates to a method for producing a lightweight component in composite construction for turbomachinery, with thin, metallic wall layers as well as with a metallic core structure with a high void volume fraction, according to the Preamble of claim 1.
- Lightweight components in composite construction with a thin outer wall layer and with A lightweight core structure is known in a variety of designs, be it in Metal and / or plastic construction.
- the bulk of the mechanical loads will be absorbed by the wall layer, the core structure has primarily a supporting function in relation to the wall layer and protects the latter from dents, kinks etc ..
- core structures Rigid foams and honeycomb geometries are preferably used and mechanically bonded to the wall layer, often by gluing.
- the type and direction of the component load are also rib, spar and stringerieri Core structures for use, in particular in pure metal construction.
- a lightweight bucket for turbomachines comprising a vane shell and a vane core, the latter consisting of a bunch of tubes, which are stuck together and with the outer shell are connected.
- US 5,634,189 discloses a lightweight composite structural member with thin, metallic ones Wall layers and a metallic core structure surrounded by these, wherein the core structure of juxtaposed sintered hollow bodies with a high void volume fraction is built and the core structure in relation provided to their volume in the finished lightweight component with a larger volume is and during the molding process by compressing in the compacted desired shape and sintered in itself and with the wall layers becomes.
- the invention is therefore based on the object, a method for producing a To propose lightweight composite components for turbomachinery, with both a low structural weight and a high structural rigidity, as well as a high internal damping of the component is achieved and thus for high dynamic Loads is suitable.
- the desired, optimal combination of strength and self-damping in combination with lightweight construction is by the structure of the core structure and by the Type of internal consolidation and connection to the wall layer achieved.
- the Core structure is a spatial felt and / or braid-like structure of wires (also endless wire), ribbons, chips etc. made of the same metal or a base same Have metal like the core structure surrounding metallic wall layers, wherein the desired damping i. w. by internal friction, i. through friction the metal elements together, is achieved.
- the required dimensional stability and rigidity of the core structure and the overall structure is by sintering the forming metal elements (wires, etc.) with each other and with the wall layers achieved, the opposite capture the majority of the component surface.
- the term "sintering" or “sintering” in the present case has nothing to do with powder metallurgy but indicates superficial welding, i. one cohesive joining of touching metal elements, under heat and certain Pressure down.
- the core structure is in a state in relation to its Volume in the finished corpus of larger volume and thus lower density provided and before and during the molding process, wherein a molding from the wall layers of the lightweight component and the enclosed core structure is compressed by compression in the desired profile shape, volumetrically compressed and sintered in the compacted state in itself and with the wall layers.
- Figures 1 and 2 show two stages of manufacture of a lightweight blade 1 for a turbomachine, for example a compressor blade for a gas turbine engine. It can be seen a thin wall layer 3, which consists of metal and the component wrapped, and a felt or braid-like core structure 9, also made of metal.
- the metal used here can be a metal based on aluminum, titanium, iron, nickel or cobalt.
- the wall layer 3 of two curved cover plates 5, 6 is composed.
- a comparably shaped, one-piece and thin-walled hollow profile could be used (not shown).
- the core structure 9 is according to Figure 1 only preformed but not yet stabilized in itself and not yet integrally connected to the wall layer 3. The transition from the manufacturing state according to FIG.
- the cover plates 5, 6 are integrally connected in the region of the inlet and outlet edge of the blade profile, preferably by welding or soldering.
- the shaped body of wall layer 3 and enclosed core structure 9 is brought by means of a suitable tool and a press by compressing before and during the molding process, in which a shaped body of the wall layers 3 and the core structure 9, in the desired blade profile shape and sintered, ie under pressure heated until the compacted core structure elements (wires, chips, tapes, etc.) superficially cohesively connect with each other and with the wall layer 3 (sintering).
- the blade 1 is consolidated and it retains its shape even after removal from the pressing tool.
- a certain, elastic springback / decompression of the blade profile can be compensated by compressing the profile in the die to undersize (profile thickness below nominal thickness), so that it has the desired contour after springback.
- undersize profile thickness below nominal thickness
- the entry and exit edge of the blade profile must be reworked, either to remove protruding ends of the cover plates 5, 6 and to achieve the predetermined edge radii.
- the finished profile of the blade 1 can be seen in Figure 2, which is an axial section through the component corresponds.
- light construction buckets in composite construction have in all typically massive areas, e.g. the blade root or a shroud.
- inventive Lightweight construction it is the cheapest, the massive component zones as to manufacture separate parts and then in the actual lightweight composite to integrate, whether by welding, soldering, gluing, etc ..
- FIG. 3 shows, on the basis of a housing part 2, inter alia. the integration of a solid part, here a flange 11, for attachment to adjacent components, not shown. It should be a rotationally symmetrical housing part 2 for a gas turbine act, the figure corresponds to an axial section in the flange portion.
- the Wall layer 4 comprises an outer and an inner cover plate 7 and 8, soft are arranged concentrically at a constant, radial distance A to each other.
- the Core structure 10 is in a compressed, sintered-fixed manner Condition and is also sintered with the cover plates 7, 8.
- the massive, metallic Flange 11 extends into the lightweight structure, so that sufficient connection surfaces to the cover plates 7, 8 result in terms of joining by Welding, soldering, gluing etc.
- such housing parts also executed in several parts in the circumferential direction, that is segmented.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Powder Metallurgy (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Description
- Figur 1
- ein Leichtbauteil in Form einer Schaufel in vorgefertigtem Zustand,
- Figur 2
- die Schaufel aus Figur 1 in fertigem Zustand,
- Figur 3
- ein Leichtbauteil in Form eines Gehäuseteils.
In aller Regel müssen auch die Ein- und Austrittskante des Schaufelprofils nachgearbeitet werden, sei es, um überstehende Enden der Deckbleche 5, 6 zu entfernen bzw. um die vorgegebenen Kantenradien zu erzielen.
Claims (4)
- Verfahren zur Herstellung eines Leichtbauteils (1,2) in Verbundbauweise für Turbomaschinen, insbesondere einer Laufschaufel (1) für eine Gasturbine, mit dünnen, metallischen Wandschichten (3,4) sowie mit einer metallischen Kemstruktur (9,10) mit einem hohen Leervolumenanteil, wobei die Wandschichten (3,4) das Leichtbauteil (1,2) zumindest auf zwei sich gegenüberliegenden, den Großteil der Bauteiloberfläche erfassenden Seiten begrenzen, die Wandschichten (3,4) und die Kernstruktur (9,10) aus dem selben Metall oder aus zwei basisgleichen Metallen bestehen, sowie stoffschlüssig miteinander verbunden sind, und wobei die Kernstruktur (9,10) einen räumlichen, filz- und/oder geflechtartigen Aufbau aufweist sowie aus einem oder mehreren Drähten, Bändern, Spänen und/oder vergleichbaren Elementen besteht, wobei die Kernstruktur (9,10) in einem Zustand mit in Relation zu ihrem Volumen im fertigen Leichbauteil (1,2) größerem Volumen und somit geringerer Dichte bereitgestellt wird, dadurch gekennzeichnet, dass die Kernstruktur (9, 10) vor und während des Formgebungsvorganges, bei dem ein Formkörper aus den Wandschichten (3,4) des Leichbauteils (1,2) und der eingeschlossenen Kernstruktur (9,10) durch Komprimieren in die gewünschte Profilform gebracht wird, volumetrisch verdichtet und im verdichteten Zustand in sich sowie mit den Wandschichten (3,4) versintert, das heisst durch oberflächliches Verschweissen stoffschlüssig stabilisiert und integral angebunden wird.
- Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass für die Wandschichten (3,4) und die Kernstruktur (9,10) ein Metall auf Basis von Aluminium, Titan, Eisen, Nickel oder Kobalt verwendet wird.
- Verfahren nach Anspruch 1 oder 2, zur Herstellung einer Schaufel (1) für eine Turbomaschine, dadurch gekennzeichnet, dass für die Wandschichten (3) zwei, im Bereich der Ein- und Austrittskante des Schaufelprofils verbundene Deckbleche (5,6) oder ein dünnwandiges Hohlprofil verwendet werden.
- Verfahren nach Anspruch 1 oder 2, zur Herstellung eines Gehäuseteils (2) für eine Turbomaschine, dadurch gekennzeichnet, dass für die Wandschichten (4) zwei sich gegenüberliegende, ebene und/oder gekrümmte Deckbleche (7, 8) in zumindest bereichsweise konstantem Abstand (A) angeordnet werden.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19956444 | 1999-11-24 | ||
DE19956444A DE19956444B4 (de) | 1999-11-24 | 1999-11-24 | Verfahren zur Herstellung eines Leichtbauteils in Verbundbauweise |
PCT/DE2000/004091 WO2001038698A1 (de) | 1999-11-24 | 2000-11-20 | Leichtbauteil in verbundbauweise |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1232331A1 EP1232331A1 (de) | 2002-08-21 |
EP1232331B1 true EP1232331B1 (de) | 2005-05-11 |
Family
ID=7930121
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00988632A Expired - Lifetime EP1232331B1 (de) | 1999-11-24 | 2000-11-20 | Verfahren zur herstellung eines leichtbauteils in verbundbauweise |
Country Status (4)
Country | Link |
---|---|
US (1) | US6893211B1 (de) |
EP (1) | EP1232331B1 (de) |
DE (2) | DE19956444B4 (de) |
WO (1) | WO2001038698A1 (de) |
Families Citing this family (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10138250B4 (de) * | 2001-02-23 | 2008-11-20 | Oliver Dr. Romberg | Tragendes Bauteil in Sandwichbauweise |
DE102005002671B3 (de) * | 2005-01-14 | 2006-06-22 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Turbinenschaufel für Strömungsmaschinen und Verfahren zu ihrer Herstellung |
DE102005033591B4 (de) * | 2005-07-19 | 2010-11-18 | Mtu Aero Engines Gmbh | Hohlschaufel |
GB2450935B (en) * | 2007-07-13 | 2009-06-03 | Rolls Royce Plc | Component with internal damping |
GB2450934B (en) | 2007-07-13 | 2009-10-07 | Rolls Royce Plc | A Component with a damping filler |
GB0808840D0 (en) * | 2008-05-15 | 2008-06-18 | Rolls Royce Plc | A compound structure |
GB2462102B (en) * | 2008-07-24 | 2010-06-16 | Rolls Royce Plc | An aerofoil sub-assembly, an aerofoil and a method of making an aerofoil |
US8956105B2 (en) * | 2008-12-31 | 2015-02-17 | Rolls-Royce North American Technologies, Inc. | Turbine vane for gas turbine engine |
GB0901235D0 (en) * | 2009-01-27 | 2009-03-11 | Rolls Royce Plc | An article with a filler |
GB0901318D0 (en) * | 2009-01-28 | 2009-03-11 | Rolls Royce Plc | A method of joining plates of material to form a structure |
US20110182741A1 (en) * | 2010-01-26 | 2011-07-28 | United Technologies Corporation | Composite fan blade leading edge recamber |
GB201009216D0 (en) | 2010-06-02 | 2010-07-21 | Rolls Royce Plc | Rotationally balancing a rotating part |
GB2485831B (en) | 2010-11-26 | 2012-11-21 | Rolls Royce Plc | A method of manufacturing a component |
US9004873B2 (en) | 2010-12-27 | 2015-04-14 | Rolls-Royce Corporation | Airfoil, turbomachine and gas turbine engine |
US9151170B2 (en) | 2011-06-28 | 2015-10-06 | United Technologies Corporation | Damper for an integrally bladed rotor |
DE102012018871B4 (de) * | 2012-09-25 | 2014-12-24 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Strömungskörper und Verfahren zur Herstellung eines solchen |
DE102013214389A1 (de) | 2013-07-23 | 2015-01-29 | MTU Aero Engines AG | Gehäusecontainment |
GB201414495D0 (en) * | 2014-08-15 | 2014-10-01 | Rolls Royce Plc | Blade |
US11719103B1 (en) | 2022-04-07 | 2023-08-08 | General Electric Company | Components having composite laminate with co-cured chopped fibers |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2750147A (en) * | 1947-10-28 | 1956-06-12 | Power Jets Res & Dev Ltd | Blading for turbines and like machines |
US2642263A (en) * | 1951-01-05 | 1953-06-16 | Westinghouse Electric Corp | Blade apparatus |
GB716612A (en) | 1951-04-23 | 1954-10-13 | Bristol Aeroplane Co Ltd | Improvements in or relating to hollow blades for turbines or compressors |
US2921769A (en) * | 1953-06-08 | 1960-01-19 | Peerless Turbine Corp | Turbine rotor |
GB757502A (en) | 1953-07-15 | 1956-09-19 | Rolls Royce | Improvements in or relating to hollow blades and the manufacture thereof |
DE1112350B (de) | 1959-07-03 | 1961-08-03 | United Aircraft Corp | Bedaempfter, als Hohlkoerper ausgebildeter Koerper und Verfahren zu seiner Herstellung |
US3519282A (en) * | 1966-03-11 | 1970-07-07 | Gen Electric | Abradable material seal |
GB1130285A (en) * | 1967-05-05 | 1968-10-16 | Rolls Royce | Method of making an aerofoil shaped blade for a fluid flow machine |
US3667108A (en) * | 1970-04-17 | 1972-06-06 | Us Navy | Method of making a beryllium titanium composite |
US4395196A (en) * | 1980-05-05 | 1983-07-26 | Plautz John R | Turbine shroud honeycomb matrix mechanical locking structure and method |
FR2483513A1 (fr) * | 1980-05-28 | 1981-12-04 | Snecma | Procede pour la fabrication d'aubes de turbine refroidies au moyen d'un corps poreux et produit obtenu suivant ce procede |
DE3327659C2 (de) * | 1983-07-30 | 1987-01-02 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Verfahren zur Herstellung eines Verbundkörpers |
US4547122A (en) * | 1983-10-14 | 1985-10-15 | Aeronautical Research Associates Of Princeton, Inc. | Method of containing fractured turbine blade fragments |
US4772450A (en) * | 1984-07-25 | 1988-09-20 | Trw Inc. | Methods of forming powdered metal articles |
DE4041104C1 (de) | 1990-12-21 | 1992-06-04 | Mtu Muenchen Gmbh | |
GB9202982D0 (en) | 1992-02-13 | 1992-03-25 | Preci Spark Ltd | Reinforced vane |
DE4338457C2 (de) * | 1993-11-11 | 1998-09-03 | Mtu Muenchen Gmbh | Bauteil aus Metall oder Keramik mit dichter Außenschale und porösem Kern und Herstellungsverfahren |
US5509781A (en) * | 1994-02-09 | 1996-04-23 | United Technologies Corporation | Compressor blade containment with composite stator vanes |
US5498137A (en) * | 1995-02-17 | 1996-03-12 | United Technologies Corporation | Turbine engine rotor blade vibration damping device |
-
1999
- 1999-11-24 DE DE19956444A patent/DE19956444B4/de not_active Expired - Fee Related
-
2000
- 2000-11-20 DE DE50010312T patent/DE50010312D1/de not_active Expired - Lifetime
- 2000-11-20 EP EP00988632A patent/EP1232331B1/de not_active Expired - Lifetime
- 2000-11-20 WO PCT/DE2000/004091 patent/WO2001038698A1/de active IP Right Grant
- 2000-11-20 US US10/148,036 patent/US6893211B1/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
DE19956444A1 (de) | 2001-06-07 |
DE19956444B4 (de) | 2004-08-26 |
WO2001038698A1 (de) | 2001-05-31 |
EP1232331A1 (de) | 2002-08-21 |
DE50010312D1 (de) | 2005-06-16 |
US6893211B1 (en) | 2005-05-17 |
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