Counterflow single rotor turbojet and method
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Jul 6, 1993
Grant Date -
N/A
app pub date -
Dec 19, 1990
filing date -
Dec 19, 1990
priority date (Note) -
Expired
status (Latency Note)
Importance
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.
First Claim
Family
International Classification(s)
Cited Art Landscape
Patent Citation Ranking
Recipient Email Address
Recipient Email Address
Comment
Recipient Email Address
Add to Portfolio(s)
To add this patent to one, or more, of your portfolios, simply click the add button.
This Patent is in these Portfolios:
Add to additional portfolios:
Last Refreshed On:
Changes done successfully