Power plants – Reaction motor – Condition responsive thrust varying means
Patent
1993-08-20
1995-08-01
Casaregola, Louis J.
Power plants
Reaction motor
Condition responsive thrust varying means
60 3929, 137 152, F02C 7042, F02C 7057
Patent
active
054371511
ABSTRACT:
The position of the normal airflow shock pattern in the airflow inlet of a supersonic aircraft jet engine assembly is detected by a light beam position sensor assembly. A narrow band coherent source light beam is angularly transmitted across the engine assembly airflow inlet and is angularly refracted by the normal shock pattern. A bank of light beam sensor assemblies is mounted on the airflow inlet so as to detect the position of the refracted light beam relative to the leading surface of the power section of the engine. Selectively adjustable airflow control tabs are mounted on the engine assembly and are operably connected to an airflow inlet controller. The airflow inlet controller monitors ambient flight conditions and the location of the refracted light beam, and will selectively adjust the position of the airflow control tabs so as to maintain the position of the normal shock pattern at a calculated desired distance from the leading surface of the engine power section.
REFERENCES:
patent: 3533238 (1970-10-01), Marvin
patent: 3911260 (1975-10-01), Dustin
patent: 5072612 (1991-12-01), Iverson et al.
Casaregola Louis J.
United Technologies Corporation
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