Processing

Please wait...

PATENTSCOPE will be unavailable a few hours for maintenance reason on Saturday 31.10.2020 at 7:00 AM CET
Settings

Settings

Goto Application

1. WO2012065595 - ROTOR BLADE ARRANGEMENT FOR A TURBO MACHINE

Publication Number WO/2012/065595
Publication Date 24.05.2012
International Application No. PCT/DE2011/001964
International Filing Date 05.11.2011
IPC
F01D 5/16 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
12Blades
14Form or construction
16for counteracting blade vibration
CPC
F01D 5/12
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members
12Blades
F01D 5/16
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members
12Blades
14Form or construction
16for counteracting blade vibration
F05D 2250/241
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2250Geometry
20Three-dimensional
24ellipsoidal
241spherical
Y02T 50/60
YSECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
50Aeronautics or air transport
60Efficient propulsion technologies, e.g. for aircraft
Y10T 29/49336
YSECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
10TECHNICAL SUBJECTS COVERED BY FORMER USPC
TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
29Metal working
49Method of mechanical manufacture
49316Impeller making
49336Blade making
Applicants
  • MTU AERO ENGINES GMBH [DE]/[DE] (AllExceptUS)
  • HARTUNG, Andreas [DE]/[DE] (UsOnly)
Inventors
  • HARTUNG, Andreas
Priority Data
10 2010 051 529.916.11.2010DE
111 53 62108.02.2011EP
Publication Language German (DE)
Filing Language German (DE)
Designated States
Title
(DE) LAUFSCHAUFELANORDNUNG FÜR EINE TURBOMASCHINE
(EN) ROTOR BLADE ARRANGEMENT FOR A TURBO MACHINE
(FR) ENSEMBLE D'AUBE MOBILE POUR UNE TURBOMACHINE
Abstract
(DE)
Erfindungsgemäß sind bei einer Laufschaufelanordnung für eine Turbomaschine, insbesondere eine Gasturbine, mit wenigstens einer Laufschaufel (1), wobei die Laufschaufelanordnung wenigstens einen Hohlraum (3) aufweist, in dem wenigstens eine Stimmmasse (2) beweglich angeordnet ist, die Stimmmasse und/oder der Hohlraum derart abgestimmt, dass die Stimmmasse in einem vorgegebenen ersten Betriebszustand der Turbomaschine an einer Innenwandung (3.1) des Hohlraums anliegt und sich in einem zweiten vorgegebenen Betriebszustand der Turbomaschine, wenigstens zeitweise, von der Innenwandung löst.
(EN)
According to the invention, in a rotor blade arrangement for a turbo machine, in particular a gas turbine, having at least one rotor blade (1), wherein the rotor blade arrangement has at least one cavity (3) in which at least one tuning mass (2) is arranged in a movable manner, the tuning mass and/or the cavity are/is adapted such that the tuning mass bears against an inner wall (3.1) of the cavity in a predefined first operating state of the turbo machine, and moves away from the inner wall at least intermittently in a second predefined operating state of the turbo machine.
(FR)
L'invention concerne un ensemble d'aube mobile pour une turbomachine, en particulier une turbine à gaz, comprenant au moins une aube mobile (1). L'ensemble d'aube mobile comporte au moins un espace creux (3), dans lequel au moins une masse de syntonisation (2) est agencée de manière mobile. La masse de syntonisation et/ou l'espace creux sont adaptés de telle sorte que la masse de syntonisation repose sur une paroi intérieure (3.1) de l'espace creux lorsque la turbomachine se trouve dans un premier état de fonctionnement prédéfini et se sépare au moins temporairement de la paroi intérieure lorsque la turbomachine se trouve dans un deuxième état de fonctionnement prédéfini.
Also published as
Latest bibliographic data on file with the International Bureau