EP 2173974 B1 20111026 - HEAT SHIELD SEGMENT FOR A STATOR OF A GAS TURBINE
Title (en)
HEAT SHIELD SEGMENT FOR A STATOR OF A GAS TURBINE
Title (de)
HITZESCHILDSEGMENT FÜR EINEN STATOR EINER GASTURBINE
Title (fr)
SEGMENT DE BOUCLIER THERMIQUE DESTINÉ AU STATOR D'UNE TURBINE À GAZ
Publication
Application
Priority
- EP 2008057946 W 20080623
- CH 10432007 A 20070628
Abstract (en)
[origin: WO2009000801A1] The invention relates to a heat shield segment (1) for a stator of a gas turbine which comprises a rotatably received turbine rotor having turbine blades (2), a hot combustion air flow flowing toward said turbine rotor. The heat shield segment (1) is arranged radially between the turbine rotor and a turbine housing (19) and is fastened to the turbine housing. The heat shield segment (1) has a profile which has a curved section (12) in at least one position of the profile in the longitudinal direction of the turbine, a radial exterior (15) of the heat shield segment (1) having an elevated section (14) that extends in the circumferential direction of the turbine in the area of the curved section (12) and in a first terminal section in the circumferential direction of the heat shield segment (1).
IPC 8 full level
F01D 11/08 (2006.01); F01D 25/24 (2006.01)
CPC (source: EP US)
F01D 9/06 (2013.01 - EP US); F05D 2240/11 (2013.01 - EP US); F05D 2260/231 (2013.01 - EP US)
Designated contracting state (EPC)
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR
DOCDB simple family (publication)
WO 2009000801 A1 20081231; AT E530736 T1 20111115; CA 2690705 A1 20081231; CA 2690705 C 20150804; EP 2173974 A1 20100414; EP 2173974 B1 20111026; SI 2173974 T1 20120330; TW 200925389 A 20090616; TW I475152 B 20150301; US 2010150712 A1 20100617; US 8182210 B2 20120522
DOCDB simple family (application)
EP 2008057946 W 20080623; AT 08761301 T 20080623; CA 2690705 A 20080623; EP 08761301 A 20080623; SI 200830526 T 20080623; TW 97124440 A 20080627; US 64588009 A 20091223