Thrust augmenting and south suppressing apparatus and method

Claim 2

Apparatus for augmenting the thrust and suppressing the exhaust noise of a jet engine having a rearwardly discharging exhaust nozzle, comprising: an ejector ring comprising an inner and outer wall and having an entrance end and an exit end; the ejector ring being located in operative position aft of the exhaust nozzle with its entrance end adjacent to the nozzle exit and spaced at least in part from the nozzle to define inlet path means for the flow of free stream air; the ring defining a mixing zone for the free stream air and the gas stream issuing from the nozzle; a plenum chamber within the ejector ring; conduit means to conduct gas under pressure from the engine to the plenum chamber, the plenum chamber being in the forward portion of the ejector ring and being formed by the forward portions of the inner and outer walls of the ejector ring and by peripheral partition means extending between the inner and outer walls of the ejector ring; and auxiliary jet nozzle means peripherally arranged around the inner wall of the ejector ring intermediate its ends to discharge energized gas from the plenum chamber into the ejector ring around the periphery of the gaseous mixture flowing through the ejector ring.

Claim 3

Apparatus as claimed in claim 1; the jet nozzle means comprising a substantially continuous peripheral slot through the inner wall of the ejector ring in flow communication with the interior of the ring.

Claim 4

Apparatus as claimed in claim 1; the exhaust nozzle being a simple conical nozzle.

Claim 5

Apparatus as claimed in claim 1; the exhaust nozzle comprising a plurality of discrete longitudinally directed tubes separating the exhaust into a plurality of separate streams for mixing with the free stream air in the mixing zone.

Claim 6

Apparatus as claimed in claim 1; the exhaust nozzle being in the form of a plurality of peripherally spaced radially and longitudinally extending lobes opening rearwardly and defining inlet paths between them for flow of free stream air.

Claim 7

Apparatus as claimed in claim 1; including passages in the aft portion of the ejector ring downstream of the jet nozzle means and extending through the inner and outer walls of the ejector ring; and a vane pivotally mounted in each passage on a transverse axis; the Vanes being swingable in unison about their axes through limited angles to modify the nozzle profile and exit area of the ejector ring, and through substantially greater angles into proximity with each other and with the ejector ring axis to serve as thrust reverser doors to block rearward flow of the gases from the mixing zone and divert them laterally out through the passages to produce reverse thrust.

Claim 8

Apparatus as claimed in claim 1; the engine being of the fan type with a central nozzle to direct the turbine discharge into the radially central portion of the ejector ring; a fan air passage adjacent to the central nozzle; the forward portion of the ejector ring comprising a plenum chamber flowconnected to the jet nozzle means; the entrance end of the ejector ring being in flow communication with the fan air passage to receive at least a portion of the fan air for discharge through the jet nozzle means.

Claim 9

Apparatus as claimed in claim 1; the engine being provided with an afterburner located within the exhaust nozzle; a plurality of peripherally spaced longitudinally extending conduits connecting the ejector ring to the nozzle and providing between them a plurality of inlet passages between the nozzle and the ejector ring for flow of free stream air; and a door hinged at its forward end for each inlet passage adapted to be stowed for normal flight operation clear of the inlet passage and to be deployed to block the passage for afterburner operation.

Claim 10

Apparatus as claimed in claim 1; the engine including a central nozzle for the discharge of turbine gas and a fan air passage adjacent to the central nozzle; the forward portion of the ejector ring being hollow to define an annular plenum chamber; a radial partition extending across the chamber at each side to divide it into compartments; the jet nozzle means consisting of a substantially complete peripheral slot extending through the inner wall of the ejector ring and in flow communication with the compartments; a conduit connecting the fan air passage with one of the compartments, and a conduit connecting the central nozzle with another of the compartments.

Claim 11

Apparatus for augmenting the thrust and suppressing the exhaust noise of a jet engine located on an airplane wing provided with trailing edge lift increasing flaps; the engine having a rearwardly discharging exhaust nozzle with an exit plane adjacent to the trailing edge of the wing, comprising: an integrated ejector nozzle in the form of an ejector ring having an entrance end and an exit end; the ejector ring being located aft of the exhaust nozzle with its entrance end adjacent to the nozzle exit and below and adjacent to the trailing edge of the wing and spaced at least in part from the nozzle to define inlet path means for the flow of free stream air including air passing over the adjacent wing surfaces; the ring defining a mixing zone for the free stream air and the gas stream issuing from the nozzle; auxiliary jet nozzle means peripherally arranged around the inner wall of the ejector ring intermediate its ends to discharge energized gas thereinto around the periphery of the gas mixture flowing through the ring and increase the flow of free stream air over the adjacent wing flaps; and means to supply gas under pressure to said jet nozzle means.

Claim 12

Apparatus for augmenting the thrust and suppressing the exhaust noise of a jet engine located on an airplane wing provided with trailing edge lift increasing flaps; the engine having a rearwardly discharging exhaust nozzle with an exit plane adjacent to the trailing edge of the wing, comprising: an integrated ejector nozzle in the form of an ejector ring having an entrance end and an exit end; the ejector ring being located aft of the exhaust nozzle with its entrance end adjacent to the nozzle exit and below and adjacent to the trailing edge of the wing and spaced at least in part from the nozzle to define inlet path means for the flow of free stream air including air passing over the adjacent wing surfaces; the ring defining a mixing zone for the free stream air and the gas stream issuing from the nozzle; auxiliary jet nozzle means peripherally arranged around the inner wall of the ejector ring intermediate its ends to discharge energized gas thereinto around the periphery of the gas mixture flowing through the ring and increase the flow of free stream air over the adjacent wing flaps; and means to supply gas under pressure to said jet nozzle means.

Claim 13

Apparatus as claimed in claim 10; the aft portion of the ejector ring being provided with pivoted vanes swingable upward and downward to produce vertical components in the issuing jet stream.

Claim 14

Apparatus for augmenting the thrust and suppressing the exhaust noise of a jet engine located on an airplane wing provided with trailing edge lift increasing flaps deployable to chordwise spaced positions; the engine having a rearwardly discharging exhaust nozzle with an exit plane substantially forward of the flaps, comprising: an integrated ejector nozzle in the form of an ejector ring having an entrance end and an exit end; the ejector ring being located aft of the exhaust nozzle with its entrance enD adjacent to the nozzle exit and its exit end forward of the flaps; the entrance end being spaced at least in part from the nozzle to define inlet path means for the flow of free stream air; the ring defining a mixing zone for the free stream air and the gas stream issuing from the nozzle; auxiliary jet nozzle means peripherally arranged around the inner wall of the ejector ring intermediate its ends to discharge energized gas thereinto around the periphery of the gas mixture flowing through the ring; and means to supply gas under pressure to said jet nozzle means; the aft portion of the ejector ring being provided with pivoted vanes swingable upward to direct the issuing gas stream toward and over the surfaces of the deployed flaps to enhance their lift producing effect.

Claim 15

Apparatus for augmenting the thrust and suppressing the exhaust noise of a jet engine located on an airplane wing provided with trailing edge lift increasing flaps deployable to chordwise spaced positions; the engine having a rearwardly discharging exhaust nozzle with an exit plane substantially forward of the flaps, comprising: an integrated ejector nozzle in the form of an ejector ring having an entrance end and an exit end; the ejector ring being located aft of the exhaust nozzle with its entrance enD adjacent to the nozzle exit and its exit end forward of the flaps; the entrance end being spaced at least in part from the nozzle to define inlet path means for the flow of free stream air; the ring defining a mixing zone for the free stream air and the gas stream issuing from the nozzle; auxiliary jet nozzle means peripherally arranged around the inner wall of the ejector ring intermediate its ends to discharge energized gas thereinto around the periphery of the gas mixture flowing through the ring; and means to supply gas under pressure to said jet nozzle means; the aft portion of the ejector ring being provided with pivoted vanes swingable upward to direct the issuing gas stream toward and over the surfaces of the deployed flaps to enhance their lift producing effect.