Annular combustor for a turbine engine without film cooling
This patent describes a gas turbine engine. It comprises a rotary compressor; a turbine wheel coupled to the compressor to drive the same; an annular nozzle in proximity to the turbine wheel and having a plurality of vanes disposed to direct gases of combustion at the turbine wheel, the vanes having leading edges remote from the turbine wheel and trailing edges adjacent the turbine wheel; an annular combustor having a radially outer wall, a radially inner wall spaced therefrom and a radially extending wall interconnecting the inner and outer walls remote from the nozzle, the inner and outer walls, at a location remote from the radially extending wall defining an outlet throat opening to the leading edges of the vanes; means for injecting fuel into the combustor; a plurality of axially spaced rows of tangentially directed passages formed in the outer wall and in fluid communication with the compressor for introducing combustion air into the combustor, the passages being sized to provide substantially only combustion air to the substantial exclusion of dilution air into the combustor and in a quantity to substantially stoichiometrically combust fuel injected into the combustor by the fuel injecting means, and the combustor, between the throat and the radially extending wall, otherwise being free of any inlets in fluid communication with the compressor; and means at the throat and just upstream of the leading edges and in fluid communication with the compressor for introducing substantially all dilution air thereat toward the nozzle and away from the combustor whereby the combustion flame zone of the combustor is maximized.
- Assignee:
- Sundstrand Corp., Rockford, IL (United States)
- Patent Number(s):
- A; US 5101620
- Application Number:
- PPN: US 7-453687
- OSTI ID:
- 5052680
- Country of Publication:
- United States
- Language:
- English
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