Combustor dome for gas turbine engine

A combustor for a gas turbine engine having a longitudinal axis extending therethrough, including an inner liner (34), an outer liner (32) spaced radially from the inner liner (34), an annular dome (36) connected to the inner and outer liners (34,32), a plurality of air/fuel mixers (38) connected to...

Full description

Saved in:
Bibliographic Details
Main Authors FARMER, GILBERT, GROESCHEN, JAMES ANTHONY
Format Patent
LanguageEnglish
French
German
Published 11.05.2005
Edition7
Subjects
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A combustor for a gas turbine engine having a longitudinal axis extending therethrough, including an inner liner (34), an outer liner (32) spaced radially from the inner liner (34), an annular dome (36) connected to the inner and outer liners (34,32), a plurality of air/fuel mixers (38) connected to the dome (36) and circumferentially spaced within the dome (36), an outer cowl (50) connected to the outer liner (32), and an inner cowl (54) connected to the inner liner (34), wherein a combustion chamber (30) is formed by the inner liner (34), the outer liner (32) and the dome (36). The dome (36) further includes a first end connected to a liner (32/34) of the combustor, a second end (48/52) spaced radially from the first end, a first portion (64/66) extending rearwardly from the first end adjacent the liner (32/34), a second portion (60/62) extending rearwardly from the second end (48/52) and flaring radially outward from the longitudinal axis, and a nonlinear third portion (68/70) connecting the first and second dome portions (64/66,60/62).
Bibliography:Application Number: EP20030255003