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An emergency conveyance seat includes a frame for supporting a seat cushion and a back cushioning arrangement. The frame includes a pair of spaced apart channels connected by an enclosure adapted to receive a self-contained breathing apparatus. The channels provide attachment structure for mounting

An emergency conveyance seat includes a frame for supporting a seat cushion and a back cushioning arrangement. The frame includes a pair of spaced apart channels connected by an enclosure adapted to receive a self-contained breathing apparatus. The channels provide attachment structure for mounting the back cushioning arrangement thereon. One of the channels provides a protective housing for an elongated seat belt webbing having one end attached to a retractor positioned within the channel and a second end attached to a lower portion of the frame.

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An emergency conveyance seat includes a frame for supporting a seat cushion and a back cushioning arrangement. The frame includes a pair of spaced apart channels connected by an enclosure adapted to receive a self-contained breathing apparatus. The channels provide attachment structure for mounting

An emergency conveyance seat includes a frame for supporting a seat cushion and a back cushioning arrangement. The frame includes a pair of spaced apart channels connected by an enclosure adapted to receive a self-contained breathing apparatus. The channels provide attachment structure for mounting the back cushioning arrangement thereon. One of the channels provides a protective housing for an elongated seat belt webbing having one end attached to a retractor positioned within the channel and a second end attached to a lower portion of the frame. inlet region upstream of said upstream wall-flow perturber. 5. The active effective flow-through area control system of claim 4, wherein said suction system comprises an aspirated section in an inner wall of the inlet region, and wherein said blowing system is configured to blow the stream of air at a variable angle α relative to an inner wall of the inlet region. 6. The active effective flow-through area control system of claim 2, wherein each of said upstream and downstream wall-flow perturbers is configured to extend into the inlet region about two to about ten percent of the radius of the inlet region when deployed. 7. The active effective flow-through area control system of claim 2, wherein each of said upstream and downstream wall flow perturbers comprises at least one baffle. 8. The active effective flow-through area control system of claim 7, further comprising a suction system positioned in the inlet region of the aircraft engine downstream from said downstream wall-flow perturber, said suction system being configured to apply suction to the airflow in the inlet region downstream from said downstream wall flow perturber. 9. The active effective flow-through area control system of claim 7, wherein each of said upstream and downstream wall-flow perturbers comprises an annular obstruction extending from an inner wall of the inlet region, each of said annular obstructions comprising an annular arrangement of at least two baffles. 10. The active effective flow-through area control system of claim 9, wherein each of said annular obstructions comprises an annular arrangement of at least four baffles. 11. The active effective flow-through area control system of claim 2, wherein each of said upstream and downstream wall-flow perturbers comprises an iris diaphragm. 12. The active effective flow-through area control system of claim 11, further comprising a suction system positioned in the inlet region of the aircraft engine downstream from said downstream wall-flow perturber, said suction system being configured to apply suction to the airflow in the inlet region downstream from said downstream wall-flow perturber. 13. A fluidic effective flow-through area control system for an inlet region of an aircraft engine, said fluidic control system comprising: a blowing system positioned in the inlet region and being configured to blow a stream of air into the inlet region at an angle relative to an inner wall of the inlet region, to generate a fluidic obstruction to the airflow through the inlet region and generate at least one region of separated vortical flow in the airflow through the inlet region; and a suction system positioned in the inlet region and downstream from said blowing system, wherein said suction system is configured to apply suction to the airflow in the inlet region to reattach, trap and control the region of separated vortical flow. 14. The fluidic control system of claim 13, wherein said suction system comprises an aspirated section in an inner wall of the inlet region, and wherein said blowing system is configured to vary the angle at which said blowing system blows the stream of air. 15. The fluidic control system of claim 14, wherein said blowing system comprises a portion of the inner wall of the inlet region, said portion of the inner wall defining a flow-through portion. 16. A variable effective flow-through area inlet of an aircraft engine, said variable effective flow-through area inlet comprising: an inner wall defining an airflow passage; and an upstream wall-flow perturber and a downstream wall-flow perturber connected to said inner wall, said downstream wall-flow perturber being positioned downstream from said upstream wall-flow perturber, and said upstream and downstream wall-flow perturbers being configured to generate and trap at least one region of separated vortical flow in the airflow within the airflow passage. 17. The variable effective flow-through area inlet of claim 16, wherein