Cumbustor carbon screen
This patent describes a gas turbine engine. It comprises a rotor including turbine blades and a nozzle adjacent the turbine blades, the nozzle being adapted to direct hot gases of combustion to the turbine blades to cause rotation of the rotor; an annular combustor about the rotor and having an outlet to the nozzle, the annular combustor having spaced inner and outer walls interconnected by a generally radially extending wall, the annular combustor also including a combustion annulus defined by the inner, outer and radially extending walls upstream of the outlet; a housing substantially surrounding the annular combustor in spaced relation to the inner, outer, and radially extending walls thereof, the housing defining a dilution air flow path including a compressed air inlet in communication with a source of compressed air supplying dilution air at one end thereof, the dilution air flow path extending at least part way about the annular combustor; at least one fuel injector having an air passageway positioned to inject air and fuel into the combustion annulus, the fuel injector extending through one of the walls of the combustor in fluid communication with the dilution air flow path; at least one dilution air hole in the outer wall of the combustor at a point in the dilution flow air path upstream of the fuel injector, the dilution air hole accommodating communication of the dilution air flow path with the combustion annulus; and means associated with the dilution air hole for preventing potentially obstructive matter from the combustion annulus from passing through the dilution air hole.
- Assignee:
- Sundstrand Corp., Rockford, IL (United States)
- Patent Number(s):
- US 5113648; A
- Application Number:
- PPN: US 7-486132
- OSTI ID:
- 5135154
- Resource Relation:
- Patent File Date: 28 Feb 1990
- Country of Publication:
- United States
- Language:
- English
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