Combustion apparatus and method for a turbine engine
This patent describes a combustor structure for a turbine engine. It comprises: a pair of axially extending radially spaced annular walls which are radially congruent to cooperatively define at one end thereof an annular combustor exit; a radially extending annular dome wall interconnecting the pair of walls at the other end thereof to cooperatively bound thereabout an annular pressurized air space and to bound there within an annular combustion cavity; the walls cooperatively defining plural annular louvers opening therethrough for providing adjacent the combustion cavity respective annular film-like wall cooling interior air flows successively directed axially along the outer wall toward the dome wall, radially inwardly along the dome wall, and axially along the inner wall away from the dome wall; the inner wall defining a circumferential radially disposed ports opening therethrough and spaced from the dome wall to admit a respective radially outwardly directed air jets extending radially outwardly toward impingement upon the outer wall and forming a toroid of primary combustion air adjacent the dome wall, the toroid rotating in agreement with the wall cooling film-like air flows; means for energizing the rotating toroid of combustion air to swirl about the combustion cavity; and fuel delivery means for circumferentially distributing a flow of fuel into the rotating swirling toroid of primary combustion air for combustion therewith.
- Assignee:
- Allied-Signal Inc., Morris Township, Morris County, NJ (United States)
- Patent Number(s):
- US 5109671; A
- Application Number:
- PPN: US 7-446223
- OSTI ID:
- 5052501
- Resource Relation:
- Patent File Date: 5 Dec 1989
- Country of Publication:
- United States
- Language:
- English
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