초록 ▼

A gas turbine engine combustion chamber is disclosed having multiple sets of fuel injectors. A set of first fuel injectors are arranged in two radially inner and outer generally circular first arrays such that the fuel injectors of one array are located circumferentially between the fuel injectors o

A gas turbine engine combustion chamber is disclosed having multiple sets of fuel injectors. A set of first fuel injectors are arranged in two radially inner and outer generally circular first arrays such that the fuel injectors of one array are located circumferentially between the fuel injectors of the other array. The combustion chamber also includes a set of second fuel injectors which are also arranged in two generally circular, radially inner and outer arrays such that, in each array, the second fuel injectors are located circumferentially between the first fuel injectors. In a circumferential direction, the positions of the first and second fuel injectors vary between the radially outward array and the radially inward array. One set of fuel injectors may operate under idle and low power operating conditions, while the other set of fuel injectors inject fuel into the combustion chamber during full power take off or cruise operations. Since the radial positions of adjacent fuel injectors in each set vary in a radial direction around the circumference of the combustion chamber, the radial temperature variations are eliminated.

대표청구항 ▼

A combustion chamber for a gas turbine engine, the combustion chamber having a generally annular configuration about a central axis and having an outlet and being defined by inner and outer axial walls and an upstream end wall extending between the inner and outer walls, comprising: a) a plurality o

A combustion chamber for a gas turbine engine, the combustion chamber having a generally annular configuration about a central axis and having an outlet and being defined by inner and outer axial walls and an upstream end wall extending between the inner and outer walls, comprising: a) a plurality of first fuel injectors to inject first sprays of fuel directly into the combustion chamber during a first operational mode of a gas turbine engine, the plurality of first fuel injectors arranged in inner and outer first fuel injector arrays about the central axis, the first fuel injectors of each array being circumferentially spaced apart and located such that the first fuel injectors of one first fuel injector array are disposed circumferentially between first fuel injectors of the other first fuel injector array; b) a plurality of second fuel injectors to inject second sprays of fuel into the combustion chamber during a second operational mode of the gas turbine engine, the plurality of second fuel injectors arranged in inner and outer second fuel injector arrays about the central axis, the second fuel injector of each array being circumferentially spaced apart and located such that the second fuel injectors of one second fuel injector array are disposed circumferentially between second fuel injectors of the other second fuel injector array and c) first wall means extending axially into the combustion Chamber from the upstream end wall and having side edges attached to one of the inner and outer walls so as to define a plurality of chambers into which only the second fuel injectors inject fuel.