Counterflow single rotor turbojet and method
A gas turbine engine is described having a small frontal area comprising: a shaft, coupled to a wheel and a slinger type fuel nozzle, journaled for rotation to a single bearing support structure; a nonrotating inner, substantially cylindrical casing circumscribing the shaft and defining an inner flow path therebetween, the inner casing mounted on the bearing support structure; a nonrotating outer, substantially cylindrical casing circumscribing the inner casing and defining an outer flow path therebetween, the outer casing mounted on the inner casing, the outer casing having a first portion that folds outward to define an inlet of the engine and having a second portion that folds inward defining an exhaust nozzle of the engine; and a plurality of blades circumferentially mounted to the wheel and extending radial therefrom so that a lower portion of each of the blades is disposed in the inner flow path and a upper portion of each of the blades is disposed in the outer flow path, the inner and outer flow paths being in fluid communication.
- Assignee:
- Allied-Signal Inc., Morris Township, NJ (United States)
- Patent Number(s):
- US 5224339; A
- Application Number:
- PPN: US 7-629865
- OSTI ID:
- 6313256
- Resource Relation:
- Patent File Date: 19 Dec 1991
- Country of Publication:
- United States
- Language:
- English
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