Parallel stage fuel combustion system

Claim 2

A combustor assembly for a gas turbine engine, comprising a head plate, a combustor liner joined to said plate including an outer wall and an inner wall, a plurality of pilot air holes in said liner located a first predetermined distance downstream of said head plate to supply a first combustion zone within said liner, a plurality of main air holes in said liner located downstream of said pilot air holes to supply a second combustion zone within said liner, a first fuel injection nozzle supported on said head plate for directing a first narrow fuel spray cone of a predetermined included angle to maintain a non-flammable air/fuel mixture within said first combustion zone at said narrow fuel spray cone, said narrow fuel spray cone being dispersed at said second combustion zone to define a flammable air/fuel mixture, a second fuel injection nozzle supported on said head plate in parallel to said first nozzle and including means therein to produce a wide angle fuel cone for supplying a fuel dispersion into said first combustion zone for combustion with air flow through said pilot air holes prior to passage into said second combustion zone to prevent combustor flame blow-out under lean fuel/air ratios.

Claim 3

An annular combustor assembly for a gas turbine engine, comprising an annular head plate, a combustor liner joined to said plate including an annular outer wall and an annular inner wall, a plurality of pilot air holes in said outer annular wall and said inner annular wall located a first predetermined distance downstream of said head plate to supply a first combustion zone within said liner, a plurality of main air holes in said outer and inner annular walls located downstream of said pilot air holes to supply a second combustion zone within said liner, a first narrow fuel injection nozzle supported on said plate for directing a first narrow fuel spray cone of a predetermined included angle to maintain a non-flammable air/fuel mixture within said first combustion zone at said narrow fuel spray cone, said narrow fuel spray cone being dispersed at said second combustion zone to define a flammable air/fuel mixture, a second fuel injection nozzle supported on said head plate in parallel to said first nozzle and including means therein to produce a wide angle fuel cone for supplying a fuel dispersion into said first combustion zone for combustion with air flow through said pilot air holes prior to passage into said second combustion zone to prevent combustor flame blow-out under lean fuel/air ratios.

Claim 4

An annular combustor assembly for a gas turbine engine, comprising an annular head plate, a combustor liner joined to said plate including an annular outer wall and an annular inner wall, a plurality of pilot air holes in said outer annular wall and said inner annular wall located a first predetermined distance downstream of said head plate to supply a first combustion zone within said liner, a plurality of main air holes in said outer and inner annular walls located downstream of said pilot air holes to supply a second combustion zone within said liner, a first narrow fuel injection nozzle supported on said plate for directing a first narrow fuel spray cone of a predetermined included angle to maintain a non-flammable air/fuel mixture within said first combustion zone at said narrow fuel spray cone, said narrow fuel spray cone being dispersed at said second combustion zone to define a flammable air/fuel mixture, a second fuel injection nozzle supported on said head plate in parallel to said first nozzle and including means therein to produce a wide angle fuel cone for supplying a fuel dispersion into said first combustion zone for combustion with air flow through said pilot air holes prior to passage into said second combustion zone to prevent combustor flame blow-out under lean fuel/air ratios.

Claim 5

An annular combustor assembly for use in a gas turbine engine comprising an outer annular wall having a plurality of axially spaced segments each including a radially inward formed deformation at one end thereof to form a spacer rib, each spacer rib on one of said axial segments being engageable with the outer surface of an adjacent segment to form a wall cooling passage, said combustor assembly including an inner annular wall, said inner annular wall having a plurality of axial segments each including an inward deformation therein engageable with an adjacent segment to form a wall cooling passage, means forming a first plurality of holes in said inner and outer walls in communication with a first combustion zone within said liner for directing pilot air therethrough, means forming a second plurality of holes in said inner and outer walls downstream of said first plurality of holes for directing air into a second downstream combustion zone within said combustor assembly, an annular head plate closing one end of said inner and outer annular walls, a first fuel injection nozzle on said head plate for directing a first narrow fuel spray cone into said first combustion zone, said first narrow fuel spray cone having a predetermined included angle to maintain a nonflammable air fuel mixture within said first combustion zone and said cone being dispersed in the region of said second combustion zone to define a flammable air fuel mixture to burn air and fuel within said second downstream combustion zone, a second fuel injection nozzle supported on said head plate in parallel to said first nozzle and including means therein to produce a wide angle fuel cone therefrom for supplying fuel dispersion into said first combustion zone for combustion with air flow through said first plurality of holes for burning of air fuel to prevent combustor flame blowout when the lean fuel air ratios are supplied to said first combustion zone.

Claim 6

An annular combustor assembly for use in a gas turbine engine comprising an outer annular wall having a plurality of axially spaced segments each including a radially inward formed deformation at one end thereof to form a spacer rib, each spacer rib on one of said axial segments being engageable with the outer surface of an adjacent segment to form a wall cooling passage, said combustor assembly including an inner annular wall, said inner annular wall having a plurality of axial segments each including an inward deformation therein engageable with an adjacent segment to form a wall cooling passage, means forming a first plurality of holes in said inner and outer walls in communication with a first combustion zone within said liner for directing pilot air therethrough, means forming a second plurality of holes in said inner and outer walls downstream of said first plurality of holes for directing air into a second downstream combustion zone within said combustor assembly, an annular head plate closing one end of said inner and outer annular walls, a first fuel injection nozzle on said head plate for directing a first narrow fuel spray cone into said first combustion zone, said first narrow fuel spray cone having a predetermined included angle to maintain a nonflammable air fuel mixture within said first combustion zone and said cone being dispersed in the region of said second combustion zone to define a flammable air fuel mixture to burn air and fuel within said second downstream combustion zone, a second fuel injection nozzle supported on said head plate in parallel to said first nozzle and including means therein to produce a wide angle fuel cone therefrom for supplying fuel dispersion into said first combustion zone for combustion with air flow through said first plurality of holes for burning of air fuel to prevent combustor flame blowout when the lean fuel air ratios are supplied to said first combustion zone.