Gas turbine annular combustor
This patent describes an annular combustor for a gas turbine. It comprises a combustor housing including an axially extending sleeve having an axis; an annular liner disposed within the housing and about the sleeve and having concentric inner and outer axially elongated walls, the inner and outer walls of the liner being spaced from the sleeve and the housing, respectively, the liner also having a radially extending wall spaced from the housing and interconnecting the inner and outer walls at one end to define a combustion chamber; the liner being spaced from the housing and the sleeve to define a compressed air flow path, the compressed air flow path extending from a radially outer compressed air to a radially inner compressed air outlet in communication with the combustion chamber, the compressed air outlet being axially remote from the radially extending wall; means for injecting a liquid fuel to be burned into the liner in a generally tangential direction adjacent the radially extending wall to impact liquid fuel directly onto an inner surface of the outer wall adjacent thereto; means for centrifuging liquid fuel onto the inner surface of the outer wall to cause an at least partially stabilized stratification of an inner cold air layer, a hot flame layer, a gaseous fuel layer and an outer liquid fuel layer; and means for igniting a mixture of fuel and air within the combustion chamber.
- Assignee:
- Sundstrand Corp., Rockford, IL (United States)
- Patent Number(s):
- US 5113647; A
- Application Number:
- PPN: US 7-455588
- OSTI ID:
- 5052451
- Resource Relation:
- Patent File Date: 22 Dec 1989
- Country of Publication:
- United States
- Language:
- English
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