Airflow modulation system and method
AssigneeNorthrop Grumman Systems Corporation
InventorsGeorge D. Rupp, Trajaen J. Troia
Life of this patent
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Abstract
The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.
Claims12
A system for regulating the air flow into a turbine engine, the turbine engine defining a generally cylindrical turbine face, a forward outer perimeter of the turbine face and a stationary center shaft extending forward of the turbine face, the center shaft defining an apex at a forward end thereof, the system comprising:
- an air flow deflector positioned upstream of the generally circular turbine face of the turbine engine, the air flow deflector being radially extendable to define a substantially cone shaped body disposed about the center shaft upstream of the turbine;
- the air flow deflector defining forward and aft ends, the air flow forward end being engaged to the apex, and the air deflector aft end being radially extendable about an aft portion of the center shaft to define a base of the cone shaped body adjacent the turbine face;
- said air flow deflector having a first retracted configuration wherein the airflow deflector defines a cylindrical body, extending substantially concentrically about and along the center shaft from the apex to the base of the cone shaped body;
- said air deflector having a second deployed configuration wherein the air flow deflector aft end is radially extended to substantially cover the turbine face of the turbine engine, the area from the apex to the base forming a cone shaped air deflecting surface;
- wherein said air flow deflector, in said first retracted configuration, allows full airflow to said, turbine engine, said full air flow defining a substantially undeflected concentric air flow along and about the air flow deflector;
- and
- wherein said air flow deflector, in said second deployed configuration, provides an air deflecting surface, substantially precluding airflow from entering the turbine face.
Dependencies are inferred from the claim text.