Patent ID: 6270309
Filing Date: 2001-08-07
Classification: B64D,F01D,F02C,F05D,Y02T,Y10T

Abstract:
Ram air turbine apparatus comprising:a generally cylindrical external fairing having a leading end and an aft end, with an air inlet passage at said leading end, and with a plurality of external exhaust ports proximate said aft end;a support structure radially proximate the inner surface of said external fairing, said fairing supported by said support structure, said support structure including a plurality of axial spars,a central flow guide coaxially located within and supported by said support structure, said guide having an outer surface spaced from said support structure,a valve tube coaxially located intermediate said support structure and said central flow guide in radial proximity to said primary support structure, said valve tube being axially movable with respect to said external fairing and having an aerodynamically contoured nose end,a plurality of openings aft said nose end of said valve tube enabling flow of air from said air inlet passage through an annular passage formed between an inner surface of the valve tube and said outer surface of said center flow guide,a turbine wheel having vanes,a stator means having vanes for directing air flow to said turbine vanes,at least one nozzle in said annular passage between the outer surface of said central flow guide and said inner surface of said movable valve tube secured to said center flow guide and extending outward in close proximity to the inner surface of said movable valve tube, said at least one nozzle axially extending from a position proximate to said aft end of said air inlet in said external fairing to a position in close proximity to said stator vanes,said valve tube being movable between a first position wherein said contoured nose of said valve tube end is in line with the leading edge of said fairing front end such that a maximum flow area is presented to the air stream in said air inlet allowing maximum air flow through the air inlet, said at least one nozzle, said stator vanes, said turbine vanes, and through said fairing external exhaust ports to a surrounding region, and a second position wherein said valve tube is advanced forward so that the contoured nose end of said valve tube restricts said air inlet area so that reduced airflow occurs through said air inlet, said at least one nozzle, said stator vanes, said turbine vanes, and said fairing external exhaust ports to the surrounding region, and a third position wherein said valve tube is advanced to a maximum forward position so that the contoured nose of the valve tube contacts the inner surface of the fairing air inlet in a manner such that said air inlet is completely closed.