EP 3306196 B1 20220810 - COMBUSTION CHAMBER ASSEMBLY OF A GAS TURBINE AND AVIATION GAS TURBINE
Title (en)
COMBUSTION CHAMBER ASSEMBLY OF A GAS TURBINE AND AVIATION GAS TURBINE
Title (de)
BRENNKAMMERANORDNUNG EINER GASTURBINE SOWIE FLUGGASTURBINE
Title (fr)
ASSEMBLAGE DE CHAMBRE DE COMBUSTION D'UNE TURBINE À GAZ AINSI QUE TURBINE À GAZ D'AVION
Publication
Application
Priority
DE 102016219424 A 20161006
Abstract (en)
[origin: US2018100650A1] A gas turbine combustion chamber includes first admixing air holes having first inner and outer center points, and second admixing air holes having second inner and outer center points. The first and second inner center points respectively lie on a side of the first and second admixing air holes oriented towards the combustion chamber. The first and second outer center points lie on a side of the first and second admixing air holes facing away from the combustion chamber. An equation L=D2/D1*(D2−D1)/C2 is fulfilled, with L being a distance between the first and second inner center points and/or the first and second outer center points; D1 and D2 being flow diameters of the first and second admixing air holes respectively at an entry and/or exit side to the combustion chamber and C being an average flow rate coefficient of the first and second admixing holes.
IPC 8 full level
CPC (source: EP US)
F23R 3/002 (2013.01 - EP US); F23R 3/06 (2013.01 - EP US); F23R 3/10 (2013.01 - US); F23R 3/286 (2013.01 - US); F23R 2900/03044 (2013.01 - US)
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
DOCDB simple family (publication)
EP 3306196 A1 20180411; EP 3306196 B1 20220810; DE 102016219424 A1 20180412; US 10712006 B2 20200714; US 2018100650 A1 20180412
DOCDB simple family (application)
EP 17194774 A 20171004; DE 102016219424 A 20161006; US 201715726043 A 20171005