Micro-combustor for gas turbine engine
View Patent ↗An improved gas turbine combustor ( 20 ) including a basket ( 26 ) and a multiplicity of micro openings ( 29 ) arrayed across an inlet wall ( 27 ) for passage of a fuel/air mixture for ignition within the combustor. The openings preferably have a diameter on the order of the quenching diameter; i.e. the port diameter for which the flame is self-extinguishing, which is a function of the fuel mixture, temperature and pressure. The basket may have a curved rectangular shape that approximates the shape of the curved rectangular shape of the intake manifolds of the turbine.
1. A gas turbine engine combustor comprising:
a basket comprising a peripheral wall and an inlet surface, defining a combustion region therein; and
a multiplicity of inlet openings arrayed through the inlet surface for passage of a fuel/air mixture for ignition within the combustion region;
wherein each of the inlet openings comprises an inlet opening dimension of 1 mm to 15 mm, and an inlet length of 5 mm to 20 mm.
2. The combustor as in claim 1 further comprising a multiplicity of peripheral openings each comprising a peripheral opening dimension of 1 mm to 15 mm arranged through the peripheral wall for axial staging of a portion of the fuel/air mixture.
3. The combustor as in claim 1 wherein said inlet openings comprise holes of 3 mm±2.0 mm diameter.
4. The combustor as in claim 1 wherein the inlet surface comprises wire mesh having inlet openings between parallel wires.
5. The combustor as in claim 1 , wherein the inlet surface comprises a shape corresponding to a shape of a turbine inlet in fluid communication with the combustor.
6. The combustor as in claim 1 , wherein the inlet openings are unevenly arrayed across the inlet surface such that there is greater flow volume near a center of the inlet surface than near a radial edge.
7. The combustor as in claim 1 , wherein at least one of the openings comprises a varying diameter along an axial length of the respective opening.
8. The combustor as in claim 1 , wherein each of the openings comprises a dimension no greater than 10 mm.
9. The combustor as in claim 1 , wherein each of the openings comprises a dimension no greater than 5 mm.
10. A gas turbine engine comprising the combustor of claim 1 .
11. The combustor as in claim 1 wherein the inlet openings comprise rifling scores effective to impart a swirling effect on the fuel/air mixture flowing therethrough.