Gas turbine engine
Patent
·
OSTI ID:6832558
The gas turbine engine includes a centrifugal fan having radial blades for receiving inlet air through inner entrance openings to spaces between adjacent blades. The air passes through outer exit openings from the spaces between the blades. Stationary inner and outer circumferential segments define closure members which successively eclipse the inner entrance and outer exit openings of the centrifugal fan blades when the fan rotates to position adjacent blades between the closure members. The closure members and space between the blades thus define closed combustion chambers. Fuel is injected and ignited so that continuous combustion takes place at constant volume, the exhaust gases escaping through the outer exit openings when rotation of the fan positions these openings beyond the outer closure members. This continuous combustion at constant volume provides for increased efficiency in the gas turbine engine over the brayton cycle constant pressure type turbine engine.
- Assignee:
- IFI; EDB-81-050966
- Patent Number(s):
- US 4241576
- OSTI ID:
- 6832558
- Country of Publication:
- United States
- Language:
- English
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