Counterflow single rotor turbojet and method
AssigneeAllied-Signal Inc.
InventorJeffrey M. Hayes
Life of this patent
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Abstract
A small gas turbine engine for generating thrust and shaft horsepower is provided. The engine is comprised in a flow series arrangement of an inlet, a diffuser, a single stage compressor, a fuel slinger combustor, a single stage turbine, and an exhaust nozzle. The compressor circumscribes the turbine and is mounted on the same rotating wheel so that the flow of air in the compressor is in the direction opposite to the direction of hot gas flow in the turbine. Accordingly, both the compressor and turbine are on the same side of the combustor and hence only a single bearing support structure is required.
Claims7
A gas turbine engine 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 said shaft and defining an inner flowpath therebetween, said inner casing mounted on said bearing support structure;
- a nonrotating outer, substantially cylindrical casing circumscribing said inner casing and defining an outer flow path therebetween, said outer casing mounted on said inner casing, said outer casing having a first portion that folds outward to define an inlet of said engine and having a second portion that folds inward defining an exhaust nozzle of said engine;
- and
- a plurality of blades circumferentially mounted to said wheel and extending radial therefrom so that a lower portion of each of said blades is disposed in said inner flowpath and a upper portion of each of said blades is disposed in said outer flow path, said inner and outer flowpaths being in fluid communication.
Dependencies are inferred from the claim text.