Thrust vector nozzle

A thrust vectoring exhaust nozzle is disclosed. The nozzle includes an inner nozzle for changing a first degree-of-freedom of exhaust gas, an outer nozzle for changing a second degree-of-freedom of exhaust gas, a mounting bracket, a first linear actuator, a second linear actuator, a first double universal joint, and a second double universal joint. The inner nozzle is coupled to the outer nozzle. The inner nozzle is coupled to the mounting bracket. The outer nozzle is coupled to the first and second joint. When the nozzle is mounted, the inner nozzle, the outer nozzle, and the exhaust are coaxially aligned in neutral position. Actuation of the first and second linear actuators drives the first and second double universal joints independently to each other. The independent motion of the first and second double universal joints rotates the inner and outer nozzles simultaneously about the exhaust in a horizontal direction and vertical direction enabling thrust vectoring.

FIELD OF THE DISCLOSED TECHNOLOGY

The disclosed technology relates to a thrust vectoring exhaust nozzle. More specifically, the disclosed technology relates to an exhaust nozzle including asynchronously actuating mechanisms that rotate the nozzle in a horizontal and vertical direction simultaneously about the exhaust enabling thrust vectoring.

BACKGROUND OF THE DISCLOSED TECHNOLOGY

Many thrust vectoring exhaust nozzle designs employ flaps or panes with a ring to deflect or diverge exhaust emanating from the aircraft. The flaps and panes enable the nozzle to create a variable outlet cross-sectional area, as well as a variable exit direction to provide different exhaust exit methods, enabling multidirectional control, or vectoring, of the aircraft when used on a jet-powered vehicle. The need for a variable outlet area to accommodate afterburners increases the complexity of the nozzle design. In applications where the variable area is not necessary, and the thrust vectoring is desireable, the above-mentioned nozzle design becomes excessive.

Accordingly, there is a need for an alternative nozzle design that can achieve two-degree-of-freedom thrust vectoring with minimal actuators and components.

SUMMARY OF THE DISCLOSED TECHNOLOGY

Disclosed herein is a thrust vectoring exhaust nozzle apparatus including an inner nozzle to change a first degree-of-freedom of exhaust gas emanating from an exhaust of a gas turbine and an outer nozzle to change a second degree-of-freedom of exhaust gas emanating from the exhaust of the gas turbine, wherein the inner nozzle is disposed within the outer nozzle, and the inner nozzle, the outer nozzle, and the exhaust nozzle of the gas turbine are coaxially aligned relative to one another in their neutral position.

In embodiments, the thrust vectoring exhaust nozzle includes a mounting bracket removably attachable to the gas turbine, a first linear actuator coupled to the mounting bracket, a second linear actuator coupled to the mounting bracket, a first double universal joint coupled to the first linear actuator, and a second double universal joint coupled to the second linear actuator. The outer nozzle is coupled to the first double universal joint and the second double universal joint. The inner nozzle is coupled to the mounting bracket. The mounting bracket positions the inner nozzle around the exhaust of the gas turbine when mounted. Actuation of the first linear actuator and the second linear actuator drives the first double universal joint and the second double universal joint linearly at their proximal end and asynchronously relative to each other. The linear asynchronous motion of the first double universal joint and the second double universal joint rotates the nozzle about the exhaust in a horizontal direction and vertical direction simultaneously.

In some embodiments, the thrust vectoring exhaust nozzle apparatus includes a nozzle bracket connecting the inner nozzle to the outer nozzle enabling movement of the outer nozzle relative to the inner nozzle.

In embodiments, the inner nozzle is swivelly coupled to the mounting bracket enabling movement of the inner nozzle relative to the mounting bracket and the outer nozzle includes a first arm removably affixed to the first double universal joint and a second arm removably affixed to the second double universal joint.

In certain embodiments, the distance between the first arm and the second arm of the outer nozzle corresponds to the distance between the first double universal joint and the second double universal joint.

In some embodiments, the inner nozzle includes a conically shaped body including a first end and a second end, wherein the body includes a bore extending longitudinally through the body that tapers in diameter from the first end to the second end.

In embodiments the outer nozzle includes a conically shaped body including a first end and a second end, wherein the body of the outer nozzle includes a bore extending longitudinally through the body that tapers in diameter from the first end to the second end.

In some embodiments, the mounting bracket includes an inner mount removably attachable to a first side of the gas turbine, an outer mount removably attachable to a second side of the gas turbine, a mounting strap removably attachable to the gas turbine, wherein the inner mount and the outer mount are removably attachable to each other about the gas turbine via the mounting strap.

In certain embodiments, the mounting bracket includes a reinforcement plate removably attachable to the first side of the gas turbine to support the inner mount when mounted on the gas turbine.

In embodiments, the first linear actuator and the second linear actuator each include a body having an actuating mechanism coupled to a shaft, wherein the actuating mechanism drives the shaft linearly back and forth in cyclic fashion.

In some embodiments, the first double universal joint includes a first end removably affixed to a distal end of the shaft of the first linear actuator and the second double universal joint includes a first end removably affixed to a distal end of the shaft of the second linear actuator.

In embodiments, the outer mount includes an elongated body including a first end, a second end, a first side, and a second side, a pair of arcuate arms including an arch corresponding to the curvature of the body of the gas turbine to fit flush around the gas turbine, a linear actuator mount including a first aperture for receiving the shaft of the first linear actuator therethrough and a second aperture for receiving the shaft of the second linear actuator therethrough, and a recess to receive and retain a ball bearing therein.

In some embodiments, the pair of arcuate arms extend outwardly from the first side of the elongated body and include an aperture for fastening the elongated body to the gas turbine. The linear actuator mount includes a plate including the first aperture and the second aperture, wherein the plate extends perpendicularly outwardly from the first end and second side of the linear actuator mount. The recess is disposed on the second side of the elongated body.

In embodiments, an inner mount includes an elongated body including a first end, a second end, a first side, and a second side, a pair of arcuate arms including an arch corresponding to the curvature of the body of the gas turbine to fit flush around the gas turbine, and a recess to receive and retain a ball bearing therein.

In some embodiments, the pair of arcuate arms are disposed on the first end of the inner mount and extend outwardly from the first side of the elongated body of the inner mount and include an aperture for fastening the elongated body of the inner mount to the gas turbine. The recess is disposed on the first side of the elongated body.

In embodiments, the inner nozzle includes a first shaft disposed adjacent a perimeter edge of the first end, the first shaft extending outwardly relative to the body of the inner nozzle, a second shaft disposed adjacent a perimeter edge of the first end of the nozzle, the second shaft extending outwardly relative to the body of the inner nozzle. The first shaft and the second shaft are disposed oppositely relative to each other on the first end of the inner nozzle. The recess of the outer mount removably receives the first shaft via a ball bearing. The recess of the inner mount removably receives the second shaft via a ball bearing. The ball bearings enable a one DOF (degree of freedom—defined as “ability to move in a particular plane” or as known in the art), and/or rotational movement of the inner nozzle relative to the exhaust of the gas turbine.

In embodiments, the outer nozzle includes a first shaft disposed on the first arm, the first shaft extending outwardly relative to the first arm of the outer nozzle, a second shaft disposed on the second arm, the second shaft extending outwardly relative to the second arm of the outer nozzle. The first double universal joint comprises an aperture disposed at a distal end thereof that removably receives the first shaft. The second double universal joint comprises an aperture disposed at a distal end thereof that removably receives the second shaft. The distance between a center of the first shaft and a center of the second shaft corresponds to a distance between the center of the aperture of the first double universal joint and the center of the aperture of the second double universal joint.

In some embodiments, the first end of the outer nozzle comprises a perimeter edge including a first recess corresponding to the first shaft of the inner nozzle and a second recess corresponding to the second shaft of the inner nozzle, wherein the first recess and second recess provide clearance for rotational movement of the inner nozzle relative to the outer nozzle.

In embodiments, the outer nozzle includes a third shaft disposed adjacent the perimeter edge of the first end, the third shaft extending outwardly relative to the body of the outer nozzle and a fourth shaft disposed adjacent a perimeter edge of the first end of the nozzle, the fourth shaft extending outwardly relative to the body of the outer nozzle. The third shaft and the fourth shaft are disposed oppositely relative to each other on the first end of the outer nozzle.

In some embodiments, the nozzle bracket includes a first recess that removably receives the third shaft of the outer nozzle via a ball bearing and a second recess that removably receives the fourth shaft of the outer nozzle via a ball bearing, wherein the ball bearings enable one DOF, rotational motion of outer nozzle relative to (e.g. perpendicular to) the inner nozzle.

For purposes of this disclosure, the following definitions are used. “Actuator” is defined as a “mechanical, electrical, or electromechanical device that causes an article, device, machine, apparatus, or system to operate.” “Actuate” is defined as “to cause a machine, device, apparatus, or process to operate.” “Thrust” is defined as “the propulsive force of an engine.” “Vector” is defined as “a course or direction, as of an aircraft or vehicle.” “Vectoring” is defined as the “act of controlling or manipulating a course or direction.” “Thrust vectoring” is defined as “the ability of an aircraft, rocket, or other vehicle or engine to manipulate the direction of the thrust from its engine(s) or motor(s) to control the linear and angular states (x, y, and z axis) of the vehicle.” “Exhaust” is defined as “the duct, pipe, area, or device through which fluids are expelled out of a system, aircraft, vehicle, or engine.” “Outlet” is defined as “the portion of an orifice where the flow exits, such as the outlet of a nozzle.” “Variable geometry” is defined as “a device, or system, which includes a geometry that varies in that the device, or system, have changing geometric variables.” “Variable direction outlet” is defined as “an outlet having a variable direction.” “Nozzle” is defined as “a cylindrical or round device or apparatus at the end of an exhaust, pipe, hose, or tube used to control a jet of a fluid, such as gas.” “Gas turbine” also known as “a combustion turbine,” is a type of continuous combustion, internal combustion engine.” “Degree-of-freedom” is defined as “any of a limited number of ways in which a body may move or in which a dynamic system may change.” “Universal joint” is defined as “a joint or coupling connecting rigid rods whose axes are inclined to each other and consists of a pair of hinges located close together, oriented at 90° to each other, connected by a cross shaft. “Double universal joint” is defined as “a joint consisting of two universal joints mounted back to back with a center yoke interconnecting the two universal joints.” “Asynchronous” is defined as “not occurring at the same time.” “Simultaneous” is defined as “occurring at the same time.” “Cyclic” is defined as occurring in regular repeated cycles.” “Swivelly” is defined as “a coupling between two parts enabling one to revolve without turning the other.” “Coaxial” is defined as “having a common axis.”

Any device or step to a method described in this disclosure can comprise or consist of that which it is a part of, or the parts which make up the device or step. The term “and/or” is inclusive of the items which it joins linguistically and each item by itself. “Substantially” is defined as at least 95% of the term being described and/or “within a tolerance level known in the art and/or within 5% thereof. Any device or aspect of a device or method described herein can be read as “comprising” or “consisting” thereof.

The present disclosed technology provides an exhaust nozzle apparatus including asynchronously actuating mechanism that rotate the nozzle in a horizontal and vertical direction simultaneously about an exhaust, thereby creating a variable direction outlet having a variable geometry for providing different exhaust exit directions enabling multidirectional control, or vectoring, when thrusting or propelling.

Referring now toFIGS. 1A and 1Bsimultaneously,FIG. 1Ashows a perspective view of the thrust vectoring exhaust nozzle mounted onto a gas turbine according to one embodiment of the present disclosed technology.FIG. 1Bshows an exploded view of the thrust vectoring exhaust nozzle ofFIG. 1A. The present disclosed technology comprises a thrust vectoring exhaust nozzle apparatus10comprising an inner nozzle15for changing a first degree-of-freedom of exhaust gas emanating from an exhaust20of a gas turbine25, an outer nozzle30for changing a second degree-of-freedom of exhaust gas emanating from the exhaust20of the gas turbine25, a mounting bracket35removably attachable to the gas turbine25, a first linear actuator40coupled to the mounting bracket35, a second linear actuator45coupled to the mounting bracket35, a first mechanism or (universal) joint50coupled to the first linear actuator40, and a second mechanism or joint55coupled to the second linear actuator45.

In embodiments, the inner nozzle15includes a conically shaped body including a first end52and a second end54, wherein the body includes a bore60extending longitudinally through the body that tapers in diameter from the first end52to the second end54. The outer nozzle30includes a conically shaped body including a first end65and a second end70, wherein the body of the outer nozzle30includes a bore76extending longitudinally through the body that tapers in diameter from the first end65to the second end70.

In embodiments, the mounting bracket35includes an inner mount75that is removably attachable to a first side80of the gas turbine25, an outer mount85that is removably attachable to a second side90of the gas turbine25, a mounting strap95that is removably attachable to a frame100of the gas turbine25. In some embodiments, the mounting bracket35includes a reinforcement plate105removably attachable to the first side80of the gas turbine25to support the inner mount75when mounted on the gas turbine25. The inner mount75and the outer mount85are removably attachable to each other about the gas turbine25via the mounting strap95, as shown inFIG. 1A.

In embodiments, the first linear actuator40and the second linear actuator45each define a body having an actuating mechanism110coupled to a shaft115. The actuating mechanism110drives the shaft115linearly back and forth in, some embodiments, a cyclic fashion.

In some embodiments, the first mechanism50comprises a first double universal joint including a first end120removably affixed to a distal end125of the shaft115of the first linear actuator40and the second mechanism55comprises a second double universal joint including a first end130removably affixed to a distal end135of the shaft115of the second linear actuator45.

In embodiments, the outer mount85includes a first elongated body140including a first end145, a second end150, a first side155, and a second side (not shown inFIGS. 1A and 1B), a pair of first arcuate arms165including an arch corresponding to the curvature of the body of the gas turbine25to fit flush around the gas turbine25, a linear actuator mount170including a first aperture175for receiving the shaft115of the first linear actuator40therethrough and a second aperture180for receiving the shaft115of the second linear actuator45therethrough, and a first recess185(not shown inFIGS. 1A and 1B) to receive and retain a first ball bearing190(seeFIG. 2B) therein. In some embodiments, the pair of arcuate arms165extend outwardly from the second side160of the elongated body140and include an aperture195for fastening the elongated body140to the gas turbine25. In one embodiment, the pair of arcuate arms165extend perpendicularly outwardly relative to the first side155of the elongated body140. In another embodiment, the pair of arcuate arms165each include a flange171extending perpendicularly outwardly relative to the corresponding arcuate arm that includes the aperture195. The linear actuator mount170includes a plate200including the first aperture175and the second aperture180. The plate200is disposed on the first end145of the elongated body140and extends outwardly from the second side160of the linear elongated body140. In one embodiment, the plate200extends perpendicularly outwardly relative to the second side160of the linear elongated body140. The recess185is disposed on the second side160of the elongated body140adjacent the second end150of the elongated body140.

In embodiments, the inner mount75includes a second elongated body205including a first end210, a second end215, a first side220, and a second side225(not shown inFIGS. 1A and 1B), a second arcuate arm230including an arch corresponding to the curvature of the body of the gas turbine25to fit flush around the gas turbine25, and a second recess240to receive and retain a second ball bearing245(not shown inFIGS. 1A and 1B) therein. In some embodiments, the arcuate arm230is disposed on the first end210of the elongated body and extends outwardly from the first side220of the elongated body205and includes an aperture247for fastening the elongated body205to the gas turbine25. In one embodiment, the arcuate arm230extends perpendicularly outwardly relative to the first side220of the elongated body205. In another embodiment, the arcuate arm includes a flange235at a either end that includes the aperture247. The flange235extends perpendicularly outwardly relative to the arcuate arm230. The flange235corresponds to the flange170of the pair of arcuate arms165of the outer mount85such that the outer mount85and the inner mount75may fasten to one another around the gas turbine25via the flanges170,235. The recess240is disposed on the first side220of the elongated body205adjacent the second end25of the elongated body205.

Referring now toFIGS. 2A-3B, simultaneously,FIG. 2Ashows a front view of the thrust vectoring exhaust nozzle mounted onto a gas turbine according to one embodiment of the present disclosed technology.FIG. 2Bshows a cross-sectional view ofFIG. 2Aalong line A-A.FIG. 3Ashows a left side view of the thrust vectoring exhaust nozzle mounted onto a gas turbine according to one embodiment of the present disclosed technology.FIG. 3Bshows a cross-sectional view ofFIG. 3Aalong line C-C. In embodiments of the present disclosed technology, when the thrust vectoring nozzle apparatus10is mounted onto the gas turbine25and is in its neutral position, the inner nozzle15is disposed within the outer nozzle30, and the inner nozzle15, the outer nozzle30, and the exhaust20of the gas turbine25are coaxially aligned relative to one another.

In embodiments, the inner nozzle15is coupled to mounting bracket35via the inner mount75and the outer mount85. The outer nozzle30is coupled to the first mechanism (joint)50and the second mechanism (joint)55. The mounting bracket35positions the inner nozzle15around the exhaust20of the gas turbine25when the thrust vectoring exhaust nozzle apparatus10is mounted, as shown inFIG. 2B. The inner nozzle15is coupled to the outer nozzle30via a nozzle bracket250. The nozzle bracket250connects the inner nozzle15to the outer nozzle30enabling movement of the outer nozzle30relative to the inner nozzle15, as shown inFIG. 3B. The inner nozzle15is swivelly coupled to the mounting bracket35enabling movement of the inner nozzle15relative to the mounting bracket35without the mounting bracket35moving. The outer nozzle30includes a first arm255removably affixed to the first joint50and a second arm260removably affixed to the second joint55. In some embodiments, the distance between the first arm225and the second arm260of the outer nozzle30corresponds to the distance between the first joint50and the second joint55.

In embodiments, the inner nozzle15includes a first shaft265disposed adjacent a perimeter edge of the first end52of the inner nozzle15and a second shaft270disposed adjacent a perimeter edge of the first end52of the inner nozzle15. The first shaft265extends outwardly relative to the body of the inner nozzle15. The second shaft270extends outwardly relative to the body of the inner nozzle15. The first shaft265and the second shaft270are disposed on opposite sides of the body of the inner nozzle15. In one embodiment, the first shaft265and the second shaft270extend perpendicularly outwardly relative to the body of the inner nozzle15. The recess185of the outer mount85removably receives the first shaft265of the inner nozzle15via the ball bearing190. The recess240of the inner mount75removably receives the second shaft270via the ball bearing245. The ball bearings190,245enable one DOF rotational motion of the inner nozzle15relative to the exhaust20of the gas turbine25.

In embodiments, the outer nozzle30includes a first shaft275disposed on the first arm255and a second shaft280disposed on the second arm260, as shown inFIG. 1B. The first shaft275extends upwardly relative to the first arm255of the outer nozzle30. The second shaft280extends upwardly relative to the second arm260of the outer nozzle30. In one embodiment, the first shaft275and the second shaft280extend perpendicularly upwardly relative to the first arm255and the second arm260.

The first joint50comprises an aperture (not shown) disposed at a distal end285thereof that removably receives the first shaft275of the outer nozzle30. The second joint55comprises an aperture (not shown) disposed at a distal end290thereof that removably receives the second shaft280. In some embodiments, the distance between a center of the first shaft275and a center of the second shaft280corresponds to a distance between the center of the aperture of the first joint50and the center of the aperture of the second joint55.

In some embodiments, the first end65of the outer nozzle30comprises a perimeter edge including a first recess295corresponding to the first shaft265of the inner nozzle15and a second recess300corresponding to the second shaft270of the inner nozzle15. The first recess295and the second recess300enable the inner nozzle15to rotate relative to the outer nozzle30, without interference by the outer nozzle30.

In embodiments, the outer nozzle30includes a third shaft305disposed adjacent the perimeter edge of the first end65of the outer nozzle30and a fourth shaft310disposed adjacent a perimeter edge of the first end65of the outer nozzle30, as shown inFIG. 3B. The third shaft305extends outwardly relative to the body of the outer nozzle30. The fourth shaft310extends outwardly relative to the body of the outer nozzle. In one embodiment, the third shaft305and the fourth shaft310extend perpendicularly outwardly relative to the body of the outer nozzle30. The third shaft305and the fourth shaft310are disposed on opposites sides of the first end65of the outer nozzle30.

In some embodiments, the nozzle bracket250includes a first recess315that removably receives the third shaft305of the outer nozzle30via a ball bearing320and a second recess325that removably receives the fourth shaft310of the outer nozzle30via a ball bearing330. The ball bearings320,330enable one DOF rotational motion of outer nozzle30relative to the inner nozzle15.

Referring now toFIGS. 4A-5B, simultaneously,FIG. 4Ashows a front view of the thrust vectoring exhaust nozzle mounted onto a gas turbine according to one embodiment of the present disclosed technology.FIG. 4Bshows a cross-sectional view ofFIG. 4Aalong line F-F.FIG. 5Ashows a front view of the thrust vectoring exhaust nozzle mounted onto a gas turbine according to one embodiment of the present disclosed technology.FIG. 5Bshows a cross-sectional view ofFIG. 5Aalong line L-L. In operation of the thrust vectoring exhaust nozzle apparatus10, actuation of the first linear actuator40and the second linear actuator45drives the first joint50and the second joint55, respectively, linearly and asynchronously relative to each other. In other words, the first linear actuator40and the second linear actuator45drive the first joint50and second joint55, respectively, in a reciprocating motion, such that when the first joint50is driven upward, the second joint55is being driven upward independently or as a result of movement of the other joint. Hence, the first joint50and the second joint55are being driven in opposite motions or opposite strokes, in some embodiments, or move independently of one another in other embodiments.

The linear asynchronous motion of the first end120of the first joint50and the first end130of the second joint55is converted to rotational motion which rotates the inner nozzle15and the outer nozzle30about the exhaust20in a horizontal direction and vertical direction simultaneously. The first joint50and the second joint55drive the first arm255and the second arm260, which in turn rotates the outer nozzle30, which in turn rotates the inner nozzle15. The simultaneous rotation of the inner nozzle15and the outer nozzle30in a horizontal and/or vertical direction (that is, perpendicular to each other) which enables thrust vectoring and multidirectional control of an aircraft having the thrust vectoring exhaust nozzle apparatus10mounted thereon. All such references to horizontal and vertical direction are relative to one another and are perpendicular or substantially perpendicular to one another.

Rotation of the inner nozzle15about the exhaust20enables changing of a first degree-of-freedom of exhaust gas emanating from the exhaust20. Rotation of the outer nozzle30about the inner nozzle15enables changing of a second degree-of-freedom of exhaust gas emanating from the exhaust20. When the first joint50and the second joint55comprise double universal joints, the double universal joints allow rotational motion of the outer nozzle30and the inner nozzle15relative to the exhaust20, thereby enabling first degree-of-freedom and second degree-of-freedom of exhaust gas and significant thrust vectoring.