Abstract A combustion chamber of the type employing staged combustion principles is disclosed. Effective control of undesirable pollutants is sought over a wide range of operating power levels. A specific objective is to separate staged combustion zones without the penetration of structural apparatus into the chamber. Single site fuel injection is desired. Primary fuel premixing tubes (34) and secondary fuel premixing tubes (38) terminate at the front wall (32) of the combustion chamber (30). The primary fuel premixing tubes have highly angled discharge swirlers at the downstream ends thereof. The highly angled swirlers (66) cause the fuel/air mixture emanating therefrom to burn in close proximity to the front wall. The secondary fuel premixing tubes have lowly angled discharge swirlers, or no swirlers at all, so as to cause the effluent therefrom to penetrate the region at which primary combustion is taking place without significantly influencing the fuel/air ratio at the primary combustion site (P).
A combustion chamber of the type suited for use in a gas turbine engine and of the type employing primary and secondary combustion zones, wherein the improvement comprises aerodynamic means for separating the zone of primary combustion from the zone of secondary combustion and includes: one or more primary fuel premixing tubes terminating at the forward end of said combustion chamber and having a highly angled discharged swirler at the downstream end thereof for swirling effluent dischargeable therefrom in close proximity to the forward end of the chamber to establish the primary combustion zone in that region; and one or more secondary fuel premixing tubes terminating at the forward end of said combustion chamber, but which are adapted to discharge the effluent therefrom through said primary combustion zone to a secondary combustion zone at a location downstream of said primary combustion zone.
Claim 2
Dependent Claim
142 words
A combustion chamber of the type suited for use in a gas turbine engine and of the type employing primary and secondary combustion zones, wherein the improvement comprises aerodynamic means for separating the zone of primary combustion from the zone of secondary combustion and includes: one or more primary fuel premixing tubes terminating at the forward end of said combustion chamber and having a highly angled discharged swirler at the downstream end thereof for swirling effluent dischargeable therefrom in close proximity to the forward end of the chamber to establish the primary combustion zone in that region; and one or more secondary fuel premixing tubes terminating at the forward end of said combustion chamber, but which are adapted to discharge the effluent therefrom through said primary combustion zone to a secondary combustion zone at a location downstream of said primary combustion zone.
Claim 3
Dependent Claim
48 words
The invention according to claim 1 wherein each of said secondary fuel premixing tubes has a lowly angled discharge swirler at the downstream end thereof in comparison to the highly angled discharge swirlers of the primary premixing tubes to establish said separated zones of primary and secondary combustion.