EP 1738061 B1 20120502 - METHOD FOR DESIGNING A TURBINE OF AN AIRCRAFT ENGINE
Title (en)
METHOD FOR DESIGNING A TURBINE OF AN AIRCRAFT ENGINE
Title (de)
VERFAHREN ZUR AUSLEGUNG EINER TURBINE EINES FLUGTRIEBWERKS
Title (fr)
PROCEDE DE CONCEPTION D'UNE TURBINE D'UN MOTEUR D'AERONEF
Publication
Application
Priority
- DE 2005000435 W 20050311
- DE 102004016246 A 20040402
Abstract (en)
[origin: WO2005100750A1] The invention relates to a low-pressure turbine of a gas turbine. The turbine comprises a number of stages arranged one behind the other in an axial manner in the flow-through direction of the turbine. Each stage is formed from a fixed vane ring having a number of vanes and from a rotating blade ring having a number of blades. Each stage is characterized by a characteristic value vane-to-blade ratio that indicates the ratio of the number of vanes to the number of blades within a stage. One of the stages of the turbine is designed in such a manner that, in the event of noise-critical conditions of the turbine, the characteristic value vane-to-blade ratio of this stage is between a lower cut-off limit for mode k=-1 of the blade passing frequency (BPF) of said stage and an upper cut-off limit for the mode k=-2 of the blade passing frequency (BPF) of this stage.
IPC 8 full level
CPC (source: EP US)
F01D 5/10 (2013.01 - EP US); F01D 5/26 (2013.01 - EP US); F05D 2260/96 (2013.01 - EP US)
Designated contracting state (EPC)
DE ES FR GB IT SE
DOCDB simple family (publication)
WO 2005100750 A1 20051027; DE 102004016246 A1 20051020; EP 1738061 A1 20070103; EP 1738061 B1 20120502; ES 2382382 T3 20120607; US 2008022691 A1 20080131; US 7806651 B2 20101005
DOCDB simple family (application)
DE 2005000435 W 20050311; DE 102004016246 A 20040402; EP 05732126 A 20050311; ES 05732126 T 20050311; US 54758105 A 20050311