Very high altitude turbine combustor
In order to facilitate enhanced starting of gas turbines at very high altitudes where the cost must be low and the design must be simple, a turbine engine is disclosed. It includes a turbine wheel coupled to a compressor for driven movement, a nozzle for directing gases of combustion at the turbine wheel, and an annular combustor defining an annular combustion space upstream of the turbine wheel in fluid communication with both the compressor and the nozzle. The combustor receives fuel from a source and air from the compressor and combusts them in the combustion space to generate the gases of combustion. The combustor is defined by an annular outer wall, an annular inner wall, and a radial wall extending there between opposite the nozzle. The turbine engine also includes at least one air blast fuel injector disposed in the annular outer wall of the combustor for injecting atomized fuel generally tangentially of the outer wall outwardly of a flame zone within the combustion space. In order to achieve the objectives of the present invention, and to do so in a manner which does not require sophisticated fuel injector or combustor designs, the turbine engine utilizes air film strips and/or holes for cooling the combustor with an air film on an inwardly facing surface of one or more of the walls defining the combustor while at the same time avoiding the filming of air onto the outer wall radially outwardly of and generally axially coextensive with the flame zone. 4 figs.
- Assignee:
- Sundstrand Corp., Rockford, IL (United States)
- Patent Number(s):
- US 5277021; A
- Application Number:
- PPN: US 7-698994
- OSTI ID:
- 6990336
- Resource Relation:
- Patent File Date: 13 May 1991
- Country of Publication:
- United States
- Language:
- English
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