Gas turbine combustors and method of operation
A gas turbine combustor is described that consists of: an outer casing; a flame tube disposed within the casing and spaced apart therefrom to form a first annular chamber between the flame tube and the casing; an air inlet means for introducing a first stream of air into the upstream end portion of the flame tube; a fuel inlet means for introducing fuel into the upstream end portion of the flame tube; an imperforate sleeve surrounding an upstream portion of the flame tube and spaced apart therefrom to longitudinally enclose an upstream portion of the first annular chamber and define a second annular chamber between the sleeve and the outer casing; means for supporting the sleeve in the spaced apart position from the flame tube; a wall member secured to the outer casing and substantially closing the downstream end of the second annular chamber; at least one opening provided in the wall of the flame tube at a first station located intermediate the upstream and downstream ends thereof; first conduit means extending from the second annular chamber into communication with the opening located at the first station for admitting a second stream of air from the second annular chamber into the interior of the flame tube; at least one other opening provided in the wall of the flame tube at a second station located downstream from the first station for admitting a third stream of air from the first annular chamber into the interior of said flame tube; and at least one opening provided in the wall member for providing communication between the second annular chamber and the portion of the first annular chamber downstream.
- Assignee:
- Phillips Petroleum Co.
- Patent Number(s):
- US 3939653
- OSTI ID:
- 7356016
- Country of Publication:
- United States
- Language:
- English
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