Combustion apparatus

Claim 2

A combustion apparatus comprising: liner means defining a combustion chamber therein; a plurality of fuel carbureting air swirlers disposed in spaced apart relation about the combustion chamber wherein each carbureting air swirler includes fuel injection means for receiving and dispersing an inlet flow of fuel together with swirl means for imparting a circumferential velocity component to an inlet airflow so as to discharge into the combustion chamber a first vortical airflow which entrains, mixes and generally atomizes the fuel emanating from the fuel injector; and a plurality of stabilizing air swirlers alternately spaced apart between the fuel carbureting air swirlers wherein each stabilizing air swirler imparts a circumferential velocity component to an inlet airflow so as to discharge into the combustion chamber a second vortical airflow of greater strength than the first vortical airflow thereby entraining a portion of the hot products of combustion and causing a recirculation thereof so as to provide generally continuous reignition.

Claim 3

The combustion apparatus of claim 1 wherein: the liner means defines a hollow annular combustion chamber therein, and the upstream end of the combustion chamber is defined by a transverse closure member having a plurality of circumferentially spaced apart openings therein which alternately receive the fuel carbureting air swirlers and stabilizing air swirlers.

Claim 4

The combustion apparatus of claim 2 wherein: the fuel carbureting swirl means includes a swirl cup of the axial inflow type, the fuel injector is housed within a centerbody centrally disposed within the swirl cup, and the stabilizing air swirlers are of the radial flow type such that the core portions of the second vortical airflows are generally at a lower pressure than the core portions of the first vortical flows, providing improved flame holding stability within the combustion chamber.

Claim 5

The combustion apparatus of claim 3 wherein: the swirl cup includes an outer shroud member spaced apart from the centerbody so as to define a substantially annular air passage therebetween together with a plurality of circumferentially spaced apart axial swirl vanes disposed between the centerbody and the outer shroud member; and the stabilizing air swirler includes a first generally radially extending wall member spaced axially forward of a second radially extending annular wall member together with a plurality of circumferentially spaced apart radial swirl vanes disposed intermediate the first and second wall member so as to receive an inlet airflow through an axially extending annular inlet defined by the outer peripheral edges of the first and second wall members.

Claim 6

The combustion apparatus of claim 3 wherein: the swirl cup includes a primary shroud spaced apart from the centerbody so as to define a first substantially annular air passage therebetween together with a plurality of circumferentially spaced apart axial swirl vanes disposed between the centerbody and the primary shroud and further including a secondary shroud member spaced apart from the primary shroud so as to define a second annular air passage therebetween together with a plurality of circumferentially spaced apart radial flow swirl vanes disposed intermediate a first radially extending circumferential wall member integrally joined to the primary shroud and a second radially extending circumferential wall member integrally joined to the secondary shroud; and the stabilizing air swirler includes a thIrd generally radially extending wall member spaced axially forward of a fourth radially extending annular wall member together with a plurality of circumferentially spaced apart radial swirl vanes disposed intermediate the third and fourth wall members so as to receive an inlet airflow through an axially extending annular inlet defined by the outer peripheral edges of the first and second wall members.

Claim 7

A combustion apparatus comprising: means for delivering a compressed inlet airflow; a hollow liner defining an annular combustion chamber therein and open at one end to receive a portion of the compressed inlet airflow; an outer shell enclosing the hollow liner and spaced apart therefrom so as to define inner and outer air passages for directing a portion of the compressed inlet airflow into the combustion chamber through a plurality of openings in the liner; a plurality of fuel carbureting air swirlers disposed in spaced apart relation about the combustion chamber wherein each carburetor includes fuel injection means for receiving and dispersing an inlet flow of fuel together with swirl means for imparting a circumferential velocity component to the compressed inlet airflow so as to discharge into the combustion chamber a first vortical air-flow which entrains and generally atomizes the fuel emanating from the fuel injector; and a plurality of stabilizing air swirlers alternately spaced apart between the fuel carbureting air swirlers wherein each stabilizing air swirler imparts a circumferential velocity component to the compressed inlet airflow so as to discharge into the combustion chamber a second vortical airflow of greater strength than the first vortical airflow thereby entraining a portion of the hot products of combustion and causing a recirculation thereof so as to provide continuous reignition.

Claim 8

A combustion apparatus comprising: means for delivering a compressed inlet airflow; a hollow liner defining an annular combustion chamber therein and open at one end to receive a portion of the compressed inlet airflow; an outer shell enclosing the hollow liner and spaced apart therefrom so as to define inner and outer air passages for directing a portion of the compressed inlet airflow into the combustion chamber through a plurality of openings in the liner; a plurality of fuel carbureting air swirlers disposed in spaced apart relation about the combustion chamber wherein each carburetor includes fuel injection means for receiving and dispersing an inlet flow of fuel together with swirl means for imparting a circumferential velocity component to the compressed inlet airflow so as to discharge into the combustion chamber a first vortical air-flow which entrains and generally atomizes the fuel emanating from the fuel injector; and a plurality of stabilizing air swirlers alternately spaced apart between the fuel carbureting air swirlers wherein each stabilizing air swirler imparts a circumferential velocity component to the compressed inlet airflow so as to discharge into the combustion chamber a second vortical airflow of greater strength than the first vortical airflow thereby entraining a portion of the hot products of combustion and causing a recirculation thereof so as to provide continuous reignition.

Claim 9

The combustion apparatus of claim 6 wherein: the upstream end of the combustion chamber includes a domed upstream closure member having a plurality of circumferentially spaced apart openings therein which alternately receive the fuel carbureting air swirlers and stabilizing air swirlers.

Claim 10

The combustion apparatus of claim 7 wherein: the fuel carbureting air swirler means includes a swirl cup of the axial flow type, the fuel injector is housed within a centerbody centrally disposed within the swirl cup and the stabilizing air swirlers are of the radial flow type such that the core portions of the second vortical airflows are generally at a lower pressure than the core portions of the first vortical flows so as to provide improved flame holding stability within the combustion chamber.