초록 ▼

A thrust reversing system for controlling the fan gases from a thrust producing aircraft engine. The system comprises a first group of blocker doors surrounding the upper longitudinal portion of the engine fan duct; a second group of blocker doors positioned rearward of the first group surrounding t

A thrust reversing system for controlling the fan gases from a thrust producing aircraft engine. The system comprises a first group of blocker doors surrounding the upper longitudinal portion of the engine fan duct; a second group of blocker doors positioned rearward of the first group surrounding the entire engine fan duct; mechanism is provided for translating an upper movable fairing and a lower sleeve section which during translating provides an upwardly directed opening from the fan duct through gas-directing cascades and deploys the blocker doors from a stowed duct wall lining position to a deployed fan gas blocking deployed position.

대표청구항 ▼

1. In a thrust reversing system for controlling fan gases from a fan jet engine carried by an aircraft, said engine having upper and lower longitudinal sections comprising: a forward positioned fixed fairing having inner and outer walls; an inner duct wall carried exterior to said engine and an

1. In a thrust reversing system for controlling fan gases from a fan jet engine carried by an aircraft, said engine having upper and lower longitudinal sections comprising: a forward positioned fixed fairing having inner and outer walls; an inner duct wall carried exterior to said engine and an outer duct wall, spaced therefrom for forming a fan duct with said forward positioned fairing; a rearwardly translatable fairing positioned adjacent said engine upper longitudinal section that abuts said forward fixed fairing along its upper longitudinal section, forming a streamlined continuation thereof when in a stowed position and exposing an upwardly directed opening therebetween when in a deployed position; a fixed sleeve surrounding the lower longitudinal section of said engine in an abutting relationship with said fixed fairing; a translatable sleeve adjacent to the lower and upper longitudinal sections of the engine forming continuation of the fixed fairing inner wall portion whereby, in a stowed position, the translatable sleeve abuts said fixed fairing and when deployed, exposes said opening to said fan duct; first and second sets of blocker doors circumferentially carried by said translatable sleeve, said first set of blocker doors positioned forward of said second set of blocker doors and surrounding the upper longitudinal section of said fan duct and said set of second blocker doors substantially surrounding the entire engine whereby, in a stowed position, said sets of doors form a portion of the outer wall of said fan duct, in a partially deployed position of the thrust reverser system direct a portion of said fan gases through said opening and in a fully deployed position direct substantially all of the fan gases through said opening; and translating means for translating said rearwardly translatable outer fairing and said translatable sleeve. 2. The invention as defined in claim 1 wherein said opening has a fixed cascade assembly positioned therein. 3. The invention as defined in claim 1 wherein link means interconnect each of said blocker doors with said inner duct wall causing said doors to rotate toward said inner duct wall and away from said outer duct wall when said translatable sleeve is translated between its stowed and deployed positions. 4. The invention as defined in claim 1 wherein the cross-section of the upper longitudinal section is greater than a semi-circle. 5. The invention as defined in claim 2 wherein a cascade assembly is secured to and supported by said fixed sleeve to preclude fan gases exiting downwardly when the translatable sleeve is translated rearwardly. 6. The invention as defined in claim 1 wherein said translating means comprise gear boxes which translate said translatable fairing at a speed greater than the translation of said translatable sleeve. 7. The invention as defined in claim 6 wherein said translating means comprises a single drive means driving a common flex shaft through gearing means so as to cause said translatable fairing to travel approximately twice the distance of said translatable sleeve in the same time. 8. The invention as defined in claim 1 wherein said translatable means comprises linear actuators. 9. The invention as defined in claim 8 wherein said linear actuators are ball actuators.