Abstract A new thrust reverser is so shaped that sound suppressor chutes may be positioned between the thrust reverser doors and within the fore and aft limits of the thrust reverser doors to form a compact, efficient combination thrust reverser and sound suppressor. A modulating thrust reverser, the elements of which being supported at their centroids for effortless movement to all positions between retracted position for providing zero reverse thrust from a reaction engine exhaust to fully extended position for generating maximum reverse thrust for use as (1) a modulating thrust reverser as a braking device on the ground subsequent to landing or prior to an aborted takeoff, (2) a modulating thrust reverser for inflight reversing for rapid descent, and (3) a thrust-modulating device for rapid thrust adjustments as may be required during a landing approach. The balanced doors require only a small actuating force for movement thereof, and for holding thereof in the end positions or any position intermediate thereof, independent of the thrust setting of the engine. Likewise, noise attenuation of the jet exhaust results from the intermediately positioned thrust reverser doors, during thrust modulation during landing approach. Tertiary doors which are located on the outer surface of a secondary nozzle provide aerodynamically smooth air ducts for supplying ambient cooling air and for improving the efficiency of the secondary nozzle during takeoff and through subsonic flight. Further, tertiary doors comprising fore and aft portions covering the air ducts adjacent the engine air intake, are connected to the thrust reverser doors for opening only the aft portion of the tertiary door to accordingly eject away from the aircraft to prevent attachment of the hot exhaust gases to the nacelle skin and the accompanying scorching and sooting thereof and to prevent reingestion of the exhaust gases into the engine air intake. Some of the tertiary doors are further responsive to the thrust reverser doors for being held closed during reverse thrust to adjust the exit area for proper engine area matching. Some doors are closed to prevent impingement of the exhaust gases against adjacent aircraft surfaces. The shape of the new thrust reverser doors provides adequate room for the positioning of sound suppressor chutes between the thrust reverser doors to accordingly form a compact and efficient combination thrust reverser and sound suppressor unit.
In combination with an aircraft engine, a thrust reverser system comprising: a longitudinally extending annular housing surrounding and extending aft the primary exhaust nozzle of said engine, said housing having an interior wall forming a secondary exhaust nozzle passageway and an exterior wall forming an aerodynamic cowling surface exposed to ambient air; pivot means rigidly affixed to said annular housing for establishing pivot points which are prevented from movement longitudinally with respect to said primary exhaust nozzle; thrust reverser door members having inoperative positions wherein they are deployed along the walls of said housing and operative positions wherein they are extended into said passageway; link means pivotally mounted at one end to said pivot means and pivotally mounted at the opposite end to said door members at the location of the center of pressure of exhaust gases impinging on said door members when they are extended into said passageway; and actuating means pivotally connected to one end portion of each of said door members for selectively translating said end portion longitudinally toward and away from said primary exhaust nozzle to rotate said door members with respect to said opposite end of said link means and thereby displace said members within said passageway to change the flow of said gases for the purpose of modulating the thrust of said engine; wherein each of said door members is supported in balanced fashion about the center of pressure of exhaust gases impinging thereon such that only a minimal force is required by said actuating means to rapidly displace said door members into any desired position for thrust modulation and reversal during the flight regime including emergency descent, landing, and aborted takeoff conditions.
Claim 2
Dependent Claim
279 words
In combination with an aircraft engine, a thrust reverser system comprising: a longitudinally extending annular housing surrounding and extending aft the primary exhaust nozzle of said engine, said housing having an interior wall forming a secondary exhaust nozzle passageway and an exterior wall forming an aerodynamic cowling surface exposed to ambient air; pivot means rigidly affixed to said annular housing for establishing pivot points which are prevented from movement longitudinally with respect to said primary exhaust nozzle; thrust reverser door members having inoperative positions wherein they are deployed along the walls of said housing and operative positions wherein they are extended into said passageway; link means pivotally mounted at one end to said pivot means and pivotally mounted at the opposite end to said door members at the location of the center of pressure of exhaust gases impinging on said door members when they are extended into said passageway; and actuating means pivotally connected to one end portion of each of said door members for selectively translating said end portion longitudinally toward and away from said primary exhaust nozzle to rotate said door members with respect to said opposite end of said link means and thereby displace said members within said passageway to change the flow of said gases for the purpose of modulating the thrust of said engine; wherein each of said door members is supported in balanced fashion about the center of pressure of exhaust gases impinging thereon such that only a minimal force is required by said actuating means to rapidly displace said door members into any desired position for thrust modulation and reversal during the flight regime including emergency descent, landing, and aborted takeoff conditions.
Claim 3
Dependent Claim
53 words
The system of claim 1 wherein said annular housing includes structure forming a duct passing through said housing, and tertiary door means for preventing flow through said duct when disposed in an inoperative position and operably responsive to displacement of said door members to move to operative positions allowing flow through said duct.
Claim 4
Dependent Claim
43 words
The thrust reverser system of claim 1 wherein said actuating means comprises longitudinally extending track means located within said annular housing, and carriage means mounted on said track means for longitudinal travel toward and away from said pivot point of said pivot means.
Claim 5
Dependent Claim
50 words
The system of claim 1 which additionally includes sound suppression means comprising a pivotally mounted sound suppressor chute located between each of said thrust reverser door members and having an inoperative position along said interior wall, and an operative position wherein it is disposed into said secondary exhaust nozzle passageway.