Thrust reversing and noise suppressing apparatus for a jet engine

Claim 2

In an aircraft having a jet engine enclosed within a tubular housing, sound-suppressing and thrust-reversing apparatus comprising: at least two tubular ejectors operatively associated with said aircraft and movable between a first position wherein they are disposed in concentric, nested relation adjacent the aft end of said housing and substantially coaxial therewith and a second position therein they are in end-to-end relation downstream from the thrust nozzle of said engine and substantially coaxial therewith so that the jet stream issuing therefrom flows therethrough, in said second position the ejectors having the largest diameters being progressively spaced farthest from said nozzle and the adjacent ends of the ejectors being disposed in spaced, substantially concentric relation so that slipstream air flowing past said housing enters each of said ejectors in a substantially annular stream surrounding the jet stream flowing therethrough; means for moving said ejectors between said first and second positions thereof, said means being adapted to permit independent translation of the largest ejector from said first position to a position downstream from said housing; blocker doors mounted on the largest ejector for movement between a first position wherein they are removed from the channel of said ejector and a second position wherein they are disposed across said channel and deflect said jet stream forwardly to thereby reverse the thrust thereof; and means for moving said blocker doors between said first and second positions thereof.

Claim 3

Apparatus as defined in claim 1 wherein: said thrust nozzle projects rearwardly from the aft end of said housing; and said ejectors are disposed around said thrust nozzle when in said first position thereof.

Claim 4

Apparatus as defined in claim 2 wherein: said thrust nozzle is formed with a plurality of lobes which extend longitudinally thereof and are spaced apart circumferentially thereon; and when said ejectors are in said first position thereof there is a gap between said nozzle and the ejector nEarest thereto, slipstream air flowing through said gap to thereby reduce aerodynamic drag upon said nozzle.

Claim 5

Apparatus as defined in claim 3 wherein said ejectors are shaped so that they conformably fit around the lobes of said nozzle when in said first position thereof.

Claim 6

In a jet propulsion assembly wherein an exhaust-conducting nozzle projects from the aft end of an engine nacelle, sound-suppressing and thrust-reversing apparatus comprising a pylon mounted on said nacelle and projecting from the aft end thereof, a first tubular ejector mounted on said pylon for movement longitudinally thereof while being maintained in substantially coaxial relation with said nozzle, said first ejector being disposable in spaced relation around said nozzle and having a pair of oppositely disposed apertures in the wall thereof, a pair of blocker doors mounted on said first ejector for movement between a first position wherein they respectively close said apertures and a second position wherein they are disposed transverse to said apertures and project into the interior of said first ejector, means operatively associated with said assembly for driving said first ejector toward and away from said nacelle, means operatively associated with said assembly for moving said blocker doors to said second position thereof when said first ejector is moved to a predetermined position thereof when said first ejector is moved to a said predetermined position aft of said nacelle and for returning said blocker doors to said first position thereof when said first ejector is moved away from said predetermined position, a second tubular ejector operatively associated with said assembly and movable longitudinally of said nozzle while being maintained in substantially coaxial relation therewith, said second ejector being disposable in spaced relation between said nozzle and said first ejector when the latter is disposed around said nozzle, a third tubular ejector operatively associated with said assembly and movable longitudinally of said nozzle while being maintained in substantially coaxial relation therewith, said third ejector being disposable in spaced relation between said first and second ejectors when the latter are disposed around said nozzle, and means operatively associated with said assembly for driving said second and third ejectors toward and away from said nacelle, whereby said ejectors can be selectively moved between a forward position wherein the aft ends thereof are adjacent the aft end of said nozzle and an aft position wherein the forward end of said second ejector encircles the aft end of said nozzle and is spaced therefrom, the forward end of said third ejector encircles the aft end of said second ejector and is spaced therefrom, and the forward end of said first ejector encircles the aft end of said third ejector and is spaced therefrom.

Claim 7

In a jet propulsion assembly wherein an exhaust-conducting nozzle projects from the aft end of an engine nacelle, sound-suppressing and thrust-reversing apparatus comprising a pylon mounted on said nacelle and projecting from the aft end thereof, a first tubular ejector mounted on said pylon for movement longitudinally thereof while being maintained in substantially coaxial relation with said nozzle, said first ejector being disposable in spaced relation around said nozzle and having a pair of oppositely disposed apertures in the wall thereof, a pair of blocker doors mounted on said first ejector for movement between a first position wherein they respectively close said apertures and a second position wherein they are disposed transverse to said apertures and project into the interior of said first ejector, means operatively associated with said assembly for driving said first ejector toward and away from said nacelle, means operatively associated with said assembly for moving said blocker doors to said second position thereof when said first ejector is moved to a predetermined position thereof when said first ejector is moved to a said predetermined position aft of said nacelle and for returning said blocker doors to said first position thereof when said first ejector is moved away from said predetermined position, a second tubular ejector operatively associated with said assembly and movable longitudinally of said nozzle while being maintained in substantially coaxial relation therewith, said second ejector being disposable in spaced relation between said nozzle and said first ejector when the latter is disposed around said nozzle, a third tubular ejector operatively associated with said assembly and movable longitudinally of said nozzle while being maintained in substantially coaxial relation therewith, said third ejector being disposable in spaced relation between said first and second ejectors when the latter are disposed around said nozzle, and means operatively associated with said assembly for driving said second and third ejectors toward and away from said nacelle, whereby said ejectors can be selectively moved between a forward position wherein the aft ends thereof are adjacent the aft end of said nozzle and an aft position wherein the forward end of said second ejector encircles the aft end of said nozzle and is spaced therefrom, the forward end of said third ejector encircles the aft end of said second ejector and is spaced therefrom, and the forward end of said first ejector encircles the aft end of said third ejector and is spaced therefrom.

Claim 8

Apparatus as defined in claim 5 including two sets of rails respectively attached to the outer surfaces of said nozzle and said second ejector and extending lengthwise thereof in circumferentially spaced relation, and a plurality of bearings respectively mounted on the inner surfaces of said second and third ejectors with their longitudinal axes extending laterally thereof, said bearings being arranged in rows extending lengthwise of a respective one of said surfaces and spaced apart circumferentially thereof, said rows being grouped in closely spaced pairs and respective ones of said rails on said nozzle being abuttingly disposed between bearings of said pairs of rows on said second ejector and respective ones of said rails on said second ejector being abuttingly disposed between bearings of said pairs of rows on said third ejector, whereby said second and third ejectors are movable longitudinally of said nozzle while being maintained substantially coaxial therewith as aforesaid.

Claim 9

Apparatus as defined in claim 5 wherein the wall of said nozzle is formed with a plurality of longitudinally extending lobes and the walls of said ejectors conforM with the contours of said lobes.

Claim 10

Apparatus as defined in claim 5 wherein said means for moving said blocker doors comprises a pair of arms respectively connected to the latter, spring means carried by said first ejector for biasing said blocker doors toward said first position thereof, and a pair of bars mounted on said pylon adjacent the aft end thereof and engageable by respective ones of said arms.

Claim 13

The method defined in claim 9 wherein said ejectors are positioned around the thrust nozzle of said engine when said aircraft is in cruise flight.