DE102008057190A1 - Blade cluster with offset axial mounting foot - Google Patents
Blade cluster with offset axial mounting foot Download PDFInfo
- Publication number
- DE102008057190A1 DE102008057190A1 DE102008057190A DE102008057190A DE102008057190A1 DE 102008057190 A1 DE102008057190 A1 DE 102008057190A1 DE 102008057190 A DE102008057190 A DE 102008057190A DE 102008057190 A DE102008057190 A DE 102008057190A DE 102008057190 A1 DE102008057190 A1 DE 102008057190A1
- Authority
- DE
- Germany
- Prior art keywords
- blade
- blades
- rotor
- cluster
- stage according
- 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.)
- Withdrawn
Links
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Abstract
Die vorliegende Erfindung betrifft die Stufe einer Turbine oder eines Verdichters mit einer Mehrzahl von Schaufeln, die an einem Rotor und/oder einem erfindungsgemäß zu einer Anzahl von Schaufelclustern als integrale Bauteile zusammengefasst, die jeweils aus zumindest zwei Schaufeln bestehen und die jeweils mit einer einzigen gemeinsamen Schaufelbefestigung zur Montage des Clusters am Rotor oder Stator ausgestattet sind.The present invention relates to the stage of a turbine or a compressor with a plurality of blades, which are combined on a rotor and / or one according to the invention to a number of blade clusters as integral components, each consisting of at least two blades and each with a single common Blade attachment for mounting the cluster on the rotor or stator are equipped.
Description
Die vorliegende Erfindung betrifft ein Schaufelcluster gemäß dem Oberbegriff des Patentanspruchs 1.The The present invention relates to a blade cluster according to the Preamble of claim 1.
Turbinenstufen, die für Turbinen mit höheren Belastungen gebaut sind, aber auch Verdichterstufen werden im Allgemeinen mit Einzelschaufeln bestückt, die jeweils über einen profilierten Fuß in eine Scheibe mit Nuten eingehängt und darin fixiert sind.Turbine stages, built for turbines with higher loads are, but also compressor stages are generally with individual blades equipped, each with a profiled Foot hung in a disc with grooves and in it are fixed.
Aus
dem Stand der Technik beispielsweise gemäß der
Zwar wird durch eine derartige Verbindung eine extrem hohe Kraftübertragung ermöglicht, jedoch stellt das Gewicht einer derart aufgebauten Verdichter- oder Turbinenstufe ein entscheidendes Manko für deren Tauglichkeit beispielsweise im Bereich der Luftfahrt dar. Insbesondere schnell laufende NDT's (Niederdruckturbinen) weisen nach dem aktuellen Stand der Technik noch eine Überschreitung des vorgegebenen Gewichtszieles auf, was folglich eine konsequente optimale Gestaltung vor allem der Rotorbauteile erforderlich macht.Though By such a connection an extremely high power transmission allows, however, the weight of such a structure Compressor or turbine stage a major shortcoming for their suitability for example in the field of aviation. In particular, fast-running NDTs (low-pressure turbines) point According to the current state of the art still exceeding the predetermined weight target, which consequently a consistent optimal Design especially the rotor components required.
Eine teilweise Lösung des vorstehend genannten Problems stellen die Rotoren von Verdichter- und Turbinenstufen dar, die nach dem Konstruktionsprinzip einer BLISK aufgebaut sind. Grundlage einer BLISK ist vorzugsweise eine geschmiedete Scheibe, aus deren Außenkontur beispielsweise durch spanende Bearbeitung die Schaufelprofile ausgearbei tet sind. D. h. die Scheibe und die Schaufeln sind aus einem Teil gefertigt.A partially solve the above problem the rotors of compressor and turbine stages, which after the Design principle of a BLISK are constructed. Basis of a BLISK is preferably a forged disc, from its outer contour For example, by machining the blade profiles tet processing are. Ie. the disc and the blades are made of one piece.
Durch das Ersetzen von teilweise mehr als 120 einzelnen Schaufeln je Scheibe durch eine solche BLISK entfallen die Montagekosten für die Schaufeln, wodurch die Herstellung eines Neuteils insgesamt verringert wird. Des Weiteren wird durch dieses Verfahren eine erhebliche Gewichtsersparnis erreicht, was vor allem in der Luftfahrt von großem Interesse ist. Allerdings können derzeit im Wesentlichen nur weniger belastete Komponenten eines Triebwerks durch eine BLISK ersetzt werden, die nach dem vorstehend genannten Verfahren hergestellt ist. Auch ist das Erneuern einer BLISK im Gegensatz zum Ersetzen einzelner Schaufeln sehr aufwändig und teuer.By the replacement of partially more than 120 individual blades per disc such a BLISK eliminates the installation costs for the blades, thereby producing a new part in total is reduced. Furthermore, this process makes a considerable Weight savings achieved, especially in aviation of great Interest is. However, at present, essentially only less loaded components of an engine through a BLISK be replaced, prepared by the above method is. Also, renewing a BLISK is in contrast to replacing it individual blades very complex and expensive.
Angesichts dieser Situation ist es die Aufgabe der vorliegenden Erfindung eine Schaufelbefestigung bereitzustellen, die eine möglichst leichte Bauweise erlaubt und trotzdem hoch belastbar ist.in view of In this situation, it is the object of the present invention To provide blade attachment, the one possible lightweight design allows and yet is highly resilient.
Diese Aufgabe wird durch ein Schaufelcluster mit den Merkmalen der Patentanspruchs 1 gelöst.These The object is achieved by a blade cluster having the features of the patent claim 1 solved.
Schaufelcluster sind erfindungsgemäß integrale Bauteile bestehend aus zumindest zwei Schaufeln, die mit einer gemeinsamen (einzigen) Schaufelbefestigung zur Montage des Clusters am Rotor oder Stator ausgestattet sind.scoop cluster According to the invention are integral components from at least two blades with a common (single) Blade attachment for mounting the cluster on the rotor or stator are equipped.
Eine besonders hohe Kraftübertragung wird dadurch gewährleistet, indem die Schaufelbefestigung als axial verlaufende Schwalbenschwanzverbindung mit zumindest einer Hinterschneidung (auf jeder Flanke) ausgeführt ist. Diese Verbindungsart ist mit hoher Präzision herstellbar und kann kostengünstig montiert werden.A particularly high power transmission is ensured by by the blade attachment as an axially extending dovetail joint with at least one undercut (on each flank) executed is. This type of connection can be produced with high precision and can be mounted inexpensively.
Vorteilhafter Weise ist die Schwalbenschwanzverbindung dezentral zwischen den Schaufeln, vorzugsweise in Umfangsrichtung versetzt angeordnet. Hierdurch können die Schaufelblattlasten anstelle einer zentralen Zusammenführung aufgeteilt in jede Schwalbenschwanzanlagefläche eingeleitet werden, sodass sich die hierbei entstehenden hohen Kerblasten verringern. Dadurch wird es möglich, die Schwalbenschwanzverbindung weniger massiv auszugestalten, bzw. höhere Kräfte zu übertragen. Dabei hat es sich bzgl. Der Krafteinleitung als besonders günstig erwiesen, wenn der Versatz in Umfangsrichtung etwa eine halbe Schaufelteilung beträgt.Favorable Way the dovetail connection is decentralized between the Blades, preferably arranged offset in the circumferential direction. This allows the blade leaf loads instead of a central merge divided into each dovetail contact surface be initiated, so that the resulting high Kerblasten reduce. This makes it possible the dovetail connection less massive to design, or higher forces transferred to. It has respect. The introduction of force proved to be particularly favorable when the offset in the circumferential direction is about half a blade pitch.
Weiter vorzugsweise ist die Nut bzw. der Rücksprung der Schwalbenschwanzverbindung auf Seiten des Schaufelclusters und der Fuß bzw. der Vorsprung auf Seiten des Rotors bzw. Stators ausgebildet. Hierdurch verringert sich das Gewicht des Clusters und damit die Kraftbelastung der Verbindung.Further Preferably, the groove or the return of the dovetail connection on the side of the blade cluster and the foot or the projection formed on the side of the rotor or stator. This reduces the weight of the cluster and thus the force load of the connection.
Weitere vorteilhafte Ausgestaltungen der Erfindung sind Gegenstand der übrigen Unteransprüche.Further advantageous embodiments of the invention are the subject of the rest Dependent claims.
Die Erfindung wird nachstehen anhand eines bevorzugten Ausführungsbeispiels unter Bezugnahme auf die begleitenden Zeichnungen näher erläutert.The The invention will be apparent from a preferred embodiment with reference to the accompanying drawings closer explained.
Gemäß der
Wie
insbesondere der
Wie
ferner in der
In
der
Des
Weiteren weisen die Federn
Zur
Montage der Schaufelcluster
An
dieser Stelle soll darauf hingewiesen werden, dass ein Schaufelcluster
ZITATE ENTHALTEN IN DER BESCHREIBUNGQUOTES INCLUDE IN THE DESCRIPTION
Diese Liste der vom Anmelder aufgeführten Dokumente wurde automatisiert erzeugt und ist ausschließlich zur besseren Information des Lesers aufgenommen. Die Liste ist nicht Bestandteil der deutschen Patent- bzw. Gebrauchsmusteranmeldung. Das DPMA übernimmt keinerlei Haftung für etwaige Fehler oder Auslassungen.This list The documents listed by the applicant have been automated generated and is solely for better information recorded by the reader. The list is not part of the German Patent or utility model application. The DPMA takes over no liability for any errors or omissions.
Zitierte PatentliteraturCited patent literature
- - DE 19858702 A1 [0003] - DE 19858702 A1 [0003]
Claims (8)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102008057190A DE102008057190A1 (en) | 2008-11-13 | 2008-11-13 | Blade cluster with offset axial mounting foot |
EP09771688A EP2344722A2 (en) | 2008-11-13 | 2009-11-07 | Blade cluster having offset axial mounting base |
PCT/DE2009/001579 WO2010054632A2 (en) | 2008-11-13 | 2009-11-07 | Blade cluster having offset axial mounting base |
US12/998,388 US20110200440A1 (en) | 2008-11-13 | 2009-11-07 | Blade cluster having an offset axial mounting base |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102008057190A DE102008057190A1 (en) | 2008-11-13 | 2008-11-13 | Blade cluster with offset axial mounting foot |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102008057190A1 true DE102008057190A1 (en) | 2010-05-20 |
Family
ID=42105017
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102008057190A Withdrawn DE102008057190A1 (en) | 2008-11-13 | 2008-11-13 | Blade cluster with offset axial mounting foot |
Country Status (4)
Country | Link |
---|---|
US (1) | US20110200440A1 (en) |
EP (1) | EP2344722A2 (en) |
DE (1) | DE102008057190A1 (en) |
WO (1) | WO2010054632A2 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2695704A1 (en) * | 2012-08-09 | 2014-02-12 | MTU Aero Engines GmbH | Method for manufacturing a TIAL guide blade ring segment for a gas turbine and corresponding guide blade ring segment |
US9677405B2 (en) | 2013-03-05 | 2017-06-13 | Rolls-Royce Corporation | Composite gas turbine engine blade having multiple airfoils |
WO2020099184A1 (en) * | 2018-11-15 | 2020-05-22 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing a component for a turbomachine |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2640263T3 (en) | 2012-11-09 | 2017-11-02 | MTU Aero Engines AG | Set of blades for a turbine |
US20170002659A1 (en) * | 2015-07-01 | 2017-01-05 | United Technologies Corporation | Tip shrouded high aspect ratio compressor stage |
US10934859B2 (en) * | 2018-08-24 | 2021-03-02 | Rolls-Royce North American Technologies Inc. | Turbine blade comprising ceramic matrix composite materials |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE679926C (en) * | 1935-12-21 | 1939-08-17 | Gustav Koehler Dipl Ing | Attachment of radially loaded double blades |
CH305819A (en) * | 1951-02-26 | 1955-03-15 | Power Jets Res & Dev Ltd | Process for the production of a vane rotor of a turbomachine and vane rotor produced according to this process. |
DE1012927B (en) * | 1955-12-06 | 1957-08-01 | Bbc Brown Boveri & Cie | Fastening the rotor blades of axial turbo machines |
DE19858702A1 (en) | 1998-12-18 | 2000-06-29 | Mtu Muenchen Gmbh | Blade and rotor for a gas turbine and method for connecting blade parts |
WO2006060012A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2221685A (en) * | 1939-01-18 | 1940-11-12 | Gen Electric | Elastic fluid turbine bucket unit |
US2277484A (en) * | 1939-04-15 | 1942-03-24 | Westinghouse Electric & Mfg Co | Turbine blade construction |
GB1217275A (en) * | 1968-05-31 | 1970-12-31 | Rolls Royce | Gas turbine engine axial flow multi-stage compressor |
US3902820A (en) * | 1973-07-02 | 1975-09-02 | Westinghouse Electric Corp | Fluid cooled turbine rotor blade |
JPH0988506A (en) * | 1995-09-21 | 1997-03-31 | Ngk Insulators Ltd | Blade for hybrid type gas turbine moving blade and turbine disc and hybrid type gas turbine moving blade consisting of them |
DE19914227B4 (en) * | 1999-03-29 | 2007-05-10 | Alstom | Heat protection device in gas turbines |
FR2851285B1 (en) * | 2003-02-13 | 2007-03-16 | Snecma Moteurs | REALIZATION OF TURBINES FOR TURBOMACHINES HAVING DIFFERENT ADJUSTED RESONANCE FREQUENCIES AND METHOD FOR ADJUSTING THE RESONANCE FREQUENCY OF A TURBINE BLADE |
GB2401655A (en) * | 2003-05-15 | 2004-11-17 | Rolls Royce Plc | A rotor blade arrangement |
DE10337868A1 (en) * | 2003-08-18 | 2005-03-17 | Mtu Aero Engines Gmbh | Rotor for a gas turbine and gas turbine |
-
2008
- 2008-11-13 DE DE102008057190A patent/DE102008057190A1/en not_active Withdrawn
-
2009
- 2009-11-07 WO PCT/DE2009/001579 patent/WO2010054632A2/en active Application Filing
- 2009-11-07 EP EP09771688A patent/EP2344722A2/en not_active Withdrawn
- 2009-11-07 US US12/998,388 patent/US20110200440A1/en not_active Abandoned
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE679926C (en) * | 1935-12-21 | 1939-08-17 | Gustav Koehler Dipl Ing | Attachment of radially loaded double blades |
CH305819A (en) * | 1951-02-26 | 1955-03-15 | Power Jets Res & Dev Ltd | Process for the production of a vane rotor of a turbomachine and vane rotor produced according to this process. |
DE1012927B (en) * | 1955-12-06 | 1957-08-01 | Bbc Brown Boveri & Cie | Fastening the rotor blades of axial turbo machines |
DE19858702A1 (en) | 1998-12-18 | 2000-06-29 | Mtu Muenchen Gmbh | Blade and rotor for a gas turbine and method for connecting blade parts |
WO2006060012A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2695704A1 (en) * | 2012-08-09 | 2014-02-12 | MTU Aero Engines GmbH | Method for manufacturing a TIAL guide blade ring segment for a gas turbine and corresponding guide blade ring segment |
US9677405B2 (en) | 2013-03-05 | 2017-06-13 | Rolls-Royce Corporation | Composite gas turbine engine blade having multiple airfoils |
WO2020099184A1 (en) * | 2018-11-15 | 2020-05-22 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing a component for a turbomachine |
Also Published As
Publication number | Publication date |
---|---|
WO2010054632A3 (en) | 2010-12-29 |
EP2344722A2 (en) | 2011-07-20 |
US20110200440A1 (en) | 2011-08-18 |
WO2010054632A2 (en) | 2010-05-20 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
OM8 | Search report available as to paragraph 43 lit. 1 sentence 1 patent law | ||
R081 | Change of applicant/patentee |
Owner name: MTU AERO ENGINES AG, DE Free format text: FORMER OWNER: MTU AERO ENGINES GMBH, 80995 MUENCHEN, DE Effective date: 20131018 |
|
R119 | Application deemed withdrawn, or ip right lapsed, due to non-payment of renewal fee |