US20090203270A1 - Reverse mechanism for a jet system - Google Patents
Reverse mechanism for a jet system Download PDFInfo
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- US20090203270A1 US20090203270A1 US12/367,923 US36792309A US2009203270A1 US 20090203270 A1 US20090203270 A1 US 20090203270A1 US 36792309 A US36792309 A US 36792309A US 2009203270 A1 US2009203270 A1 US 2009203270A1
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- Prior art keywords
- propulsion system
- jet propulsion
- discharge nozzle
- fluid
- set forth
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H11/00—Marine propulsion by water jets
- B63H11/02—Marine propulsion by water jets the propulsive medium being ambient water
- B63H11/10—Marine propulsion by water jets the propulsive medium being ambient water having means for deflecting jet or influencing cross-section thereof
- B63H11/107—Direction control of propulsive fluid
- B63H11/11—Direction control of propulsive fluid with bucket or clamshell-type reversing means
Definitions
- the invention relates to the operation of jet propulsion systems. More particularly, this invention incorporates a reverse mechanism into the jet propulsion system utilizing a deflecting surface to redirect the flow from the primary jet exhaust nozzle to produce a reverse thrust.
- Jet propulsion is a well-known means of propelling a watercraft through the water. It is also well-known to provide a reverse gate or “bucket” for converting forward thrust into rearward thrust to the propel watercraft in a reverse direction.
- U.S. Pat. No. 5,344,344 which issued to Forsstrom on Sep. 6, 1994, describes a steering and reversing system for a marine jet propulsion unit.
- the system has a stationary nozzle for discharging a waterjet in the rearward direction from the unit and incorporates a pair of steering and reversing members mounted side by side at the rear end of the nozzle and individually pivot in opposite directions about upright axes from a non-deflecting position to first and second deflecting positions.
- the steering and reversing members In the non-deflecting position, the steering and reversing members form an extension of the nozzle in the rearward direction, while in the first deflecting position each member diverts a portion of the waterjet laterally outward by means of its front section.
- In the second deflecting position each member deflects a portion of the waterjet downward and forward by means of scoop-like members at its rear section.
- U.S. Pat. No. 3,937,172 which issued to Castoldi on Feb. 10, 1976, discloses a waterjet propelling apparatus for boats.
- the apparatus forces water by a pump through a nozzle directed a stern of a boat.
- a curved jet-deflecting surface deflects the water downward and forward and reverses the thrust, and a pair of steerable parallel rudder blades pivot in unison for laterally deflecting the jet.
- the jet-deflecting surface has symmetrical channel-like side panels which direct water escaping laterally from the clearance between the trailing edges of the rudder blades and the jet-deflecting surface forward towards the bow to enhance the reverse thrust, and a central portion which is shaped with blades for maintaining the clearance with the later constant for various pivotal deviations of the blades.
- a number of embodiments of the steering nozzle and reverse thrust bucket arrangements for jet propelled watercraft are described.
- the steering nozzle in addition to being mounted for steering movement about a vertically extending steering axis, is also mounted for trim adjustment about a horizontally extending axis.
- a cooperating reverse thrust bucket provides reverse thrust operation.
- the reverse thrust bucket is either mounted on the hull of the watercraft independent of the jet propulsion unit, on the outer housing of the jet propulsion unit independent of the steering nozzle, or on the steering nozzle.
- jet propulsion system with an improved reverse mechanism that provides robust performance when switching between forward, neutral and reverse directions. It also remains desirable to provide an improved reverse mechanism that enhances or at least does not degrade the performance of the jet propulsion system in the forward direction. It is also desirable to provide an improved reverse mechanism that may be manipulated to control damping of the attitude and motion of a vessel in any of the pitch, roll or yaw axes of the vessel.
- a jet propulsion system includes a housing having a discharge nozzle through which fluid exits and provides propulsion of a vehicle along a first direction.
- the jet propulsion system also includes a reverse mechanism having a deflecting movable surface coupled to the housing for movement between a non-deployed position allowing fluid to exit the discharge nozzle and provide propulsion of the vehicle in a first direction and a deployed position forming a substantially hemispherical inner surface for redirecting flow from the discharge nozzle and providing propulsion of the vehicle in a second direction substantially opposite the first direction.
- a jet propulsion system includes an inlet receiving a fluid, and a housing defining a discharge nozzle through which fluid is discharged to provide propulsion of a vehicle in a first direction.
- the jet propulsion system also includes a reverse mechanism movable between a deployed position redirecting fluid from the discharge nozzle toward the first direction and providing propulsion of the vehicle in a second direction substantially opposite the first direction and a non-deployed position allowing fluid to exit the discharge nozzle and provide propulsion of the vehicle in the first direction.
- the reverse mechanism produces a flow entrainment that enhances forward thrust while the reverse mechanism is in the non-deployed position which results in a net thrust gain over the thrust attributed to the discharge nozzle alone.
- a jet propulsion includes a housing defining a discharge nozzle through which fluid exits and provides propulsion of a vehicle along a first direction.
- a reverse mechanism is pivotally coupled to the housing.
- the housing is moveable relative to the discharge nozzle in a pitch and steer axis wherein a thrust vector of fluid exiting the discharge nozzle may be manipulated to control damping of an attitude and motion of the vehicle in any of the pitch, roll and yaw axes.
- FIG. 1 is perspective view of a portion of a jet propulsion system according to one embodiment of the invention
- FIG. 2 is an exploded perspective view of the jet propulsion system of FIG. 1 ;
- FIG. 3 is an enlarged perspective view of a reverse mechanism for the jet propulsion system shown in a deployed position
- FIG. 4 is an enlarged perspective view of the reverse mechanism for the jet propulsion system shown in a partially deployed position
- FIG. 5 is a cross sectional view of the reversing mechanism for the jet propulsion system shown in a deployed position
- FIG. 6 is a cross sectional view of the reversing mechanism for the jet propulsion system shown in a non-deployed position
- FIG. 7 is a cross sectional view of the reversing mechanism for the jet propulsion system shown in a neutral position between the deployed and non-deployed positions;
- FIG. 8 is a cross sectional view of an alternative embodiment of the reversing mechanism for the jet propulsion system shown in the deployed position;
- FIG. 9 is a partial cross section view of another alternative of the reversing mechanism for the jet propulsion system shown in the deployed position;
- FIG. 10 is a partial perspective view of another alternative embodiment of the reversing mechanism in the deployed position
- FIG. 11 is a partial perspective view of the alternative embodiment of FIG. 10 in the non-deployed position
- FIG. 12 is a partial perspective view of another alternative embodiment of the reversing mechanism in the deployed position
- FIG. 13 is a partial perspective view of the alternative embodiment of FIG. 12 in the non-deployed position
- FIG. 14 is a partial perspective view of another alternative embodiment of the reversing mechanism in the deployed position
- FIG. 15 is a partial perspective view of the alternative embodiment of FIG. 14 in the non-deployed position
- FIG. 16 is a partial perspective view of the alternative embodiment of FIG. 14 in the non-deployed position including the transom and fixed portion of the vessel;
- FIG. 17 is a partial perspective view of the alternative embodiment of FIG. 14 in the non-deployed position including the transom and fixed portion of the vessel;
- FIG. 18 is a partial perspective view of the alternative embodiment of FIG. 14 in the deployed position including the transom and fixed portion of the vessel;
- FIG. 19 is an exploded perspective view of the alternative embodiment of FIG. 14 ;
- FIG. 20 is a perspective view of an alternative embodiment of a nozzle and ring.
- a jet propulsion system according to one embodiment of the invention is generally indicated at 10 .
- the jet propulsion system 10 includes an inlet that receives fluid into the system and an outlet or discharge nozzle 14 through which fluid exits to provide thrust for moving a vehicle 12 in a first direction.
- the jet propulsion system 10 includes a reverse mechanism 20 , shown in FIGS. 3 and 4 , that reverses the thrust or a portion of the thrust from the discharge nozzle 14 to move the vehicle 12 in a second direction opposite the first direction or to neutralize or hold the vehicle 12 in a generally fixed position relative to the body of fluid in which the vehicle 12 travels.
- the reverse mechanism 20 is shown illustratively as part of a jet propulsion system 10 for a recreational water vehicle. It should, however, be appreciated that the reverse mechanism 20 may also be used in other jet propulsion systems, where in general an accelerated jet of fluid is expelled to generate thrust, such as turbojets, turbofans, rockets, ramjets, pulse jets, gas turbine engines, and the like.
- the reverse mechanism 20 is movable between non-deployed and deployed positions. In the non-deployed position, the reverse mechanism 20 allows fluid to exit the discharge nozzle 14 to provide propulsion of the vehicle 12 in the first direction or “forward” thrust. In the non-deployed position the reverse mechanism 20 may be supported by a ring 26 outside of the discharge nozzle 14 .
- the ring 26 forms an annulus 31 with a nozzle housing 24 . Water passes through the annulus 31 in which the cross sectional area is decreased in the axial direction to accelerate the flow as it passes through the exit plane in the same direction as the flow from the discharge or exhaust nozzle 14 . The additional mass flow of the water through the annulus 31 mixes with the flow from the jet discharge or exhaust nozzle 14 resulting in thrust augmentation.
- the extent of the thrust augmentation achieved is determined by the cross section area and axial length of the annulus 31 and the velocity of the flow from the discharge or exhaust nozzle 14 .
- the flow through the annulus 31 is a flow entrainment effect due to the lower pressure in the higher speed flow from the discharge nozzle 14 .
- the reverse mechanism 20 redirects the fluid from the discharge nozzle 14 from the first direction and provides propulsion of the vehicle 12 in the second direction producing “rearward” thrust.
- the reverse mechanism 20 is also movable between the deployed and non-deployed position to provide varying degrees of forward thrust, rearward thrust or neutral.
- the reverse mechanism 20 utilizes a substantially hemispherical shaped diverting assembly 22 for diverting or “reversing” the thrust from the discharge nozzle 14 .
- a ring 26 in FIGS. 3 and 4 is attached to a housing 24 of the jet propulsion system 10 .
- the ring 26 includes an inner surface 28 spaced apart from an outer surface 30 of the housing 24 to define the annulus 31 through which fluid diverted by the diverting assembly 22 can flow.
- the diverting assembly 22 is coupled to the ring 26 and is movable relative to the ring 26 between the deployed and non-deployed positions.
- the diverting assembly 22 may include two movable parts 32 , 34 movable between the deployed and non-deployed positions.
- An opening 36 is formed between the two parts 32 , 34 and changes in size due to the movement of the parts 32 , 34 between the deployed and non-deployed positions.
- the opening 36 In the deployed position, shown in FIGS. 2 and 5 , the opening 36 is closed to prevent fluid from passing through the diverting assembly 22 .
- the non-deployed position shown in FIGS. 1 and 6 , the opening 36 is open to allow fluid to pass therethrough.
- the two parts 32 , 34 of the diverting assembly 22 are also movable to a neutral position between the deployed position and the non-deployed position, in which the amount of thrust in the first direction is substantially the same as the amount of thrust in the second direction.
- the diverting assembly 22 may include a fabric material 23 .
- the diverting assembly 22 may be formed of Vectran or other suitable high tensile strength fabric.
- the diverting assembly 22 may include a pair of movable support frames 40 , 42 that supports the two parts 32 , 34 of the diverting assembly 22 along the opening 36 .
- Each support frame 40 , 42 may be pivotally coupled to the ring 26 and provides movement of the two parts 32 , 34 of the diverting assembly 22 between the deployed and non-deployed positions.
- Each support frame 40 , 42 may have opposite ends 44 , 46 pivotally coupled to opposite sides of the housing 24 for rotation about a common pivot axis 47 .
- Each support frame 40 , 42 may extend generally arcuately between the opposite ends 44 , 46 .
- each support frame 40 , 42 has a generally L-shaped cross section defined by generally orthogonal back 50 and side 52 walls.
- the back walls 50 of the support frames 40 , 42 extend outwardly from each other in a generally symmetrically opposite manner from respective side walls 52 when the diverting assembly 22 is in the deployed position. Further, the side walls 52 of the support frames 40 , 42 are substantially parallel to each other when the diverting assembly 22 is in the deployed position.
- Each part 32 , 34 of the diverting assembly 22 includes a longitudinal pocket 54 , shown in FIGS. 5 , 6 , and 7 , that extends along the opening 36 and receives one of the support frames 40 , 42 therethrough.
- the support frames 40 , 42 are actuated between the deployed and non-deployed positions by an actuating mechanism 60 .
- the actuating mechanism 60 may include a set of arms 62 , 64 extending outward from the pivot axis 47 of the support frames 40 , 42 .
- Each arm 62 , 64 is connected to one of the respective support frames 40 , 42 such that rotation of the arms 62 , 64 about the pivot axis 47 causes corresponding rotation of the support frames 40 , 42 about the pivot axis 47 .
- the arms 62 , 64 are connected to support frames 42 , 40 on opposite sides of the pivot axis 47 so that pulling the arms 62 , 64 toward the vehicle (as indicated by the arrow A shown in FIGS.
- the arms 62 , 64 may be actuated by any suitable rod, cable mechanism and/or by a powered actuating device, such as an electric motor, hydraulic actuator or pneumatic actuator.
- the housing 24 may also be movably coupled to the vehicle 12 for steering and/or vertical pitch control.
- the housing may be moveable to allow for simultaneous steering and pitch control.
- the housing 24 may be pivotally coupled to a frame 70 , best seen in FIG. 2 , for movement about a first pivot 72 relative to the frame 70 .
- the frame 70 is, in turn, pivotally coupled to a fixed portion 74 of the vessel 12 for movement of the housing 24 and frame 70 together about a second pivot 76 relative to the fixed portion 74 of the vessel 12 .
- Cables 80 , 82 may be used for controlling the movement of the housing 24 about the first 72 and second pivots 76 .
- the housing 24 may be manipulated to control damping of the attitude and motion of the vehicle 12 in any of the pitch, roll or yaw axes in both the forward and reverse directions.
- the frame 70 includes a tab extending off of the frame 70 and isolates movement in the steering and pitch axis to prevent control loop problems when controlling movement.
- the reverse mechanism 20 also provides enhanced thrust while the reverse mechanism 20 is in the non-deployed position resulting in a net thrust gain over an amount of thrust attributable to the discharge nozzle 14 alone.
- the annulus 31 defined between the inner surface 28 of the ring 26 and the outer surface 30 of the housing 24 narrows so as to accelerate the flow of fluid passing therethrough as the vehicle 12 is propelled in the first or forward direction.
- the accelerated fluid due to the reduction in cross section area of the annulus 31 in the flow direction mixes with the fluid exiting the discharge or exhaust nozzle 14 as a result of the lower pressure in the higher speed flow from the discharge nozzle 14 . This increases the mass flow rate and hence the momentum at the exit of the discharge nozzle 14 and thereby contributes to thrust enhancement.
- FIG. 8 an alternative embodiment of the jet propulsion system 110 is shown, wherein like components or features from the previous embodiment are indicated by numerals offset by 100.
- the moving parts of the diverting assembly 122 are dimensionally stable or substantially rigid shells 33 , 35 instead of the flexible fabric 23 of the previous embodiment.
- the shells 33 , 35 rotate generally telescopically relative to each other between the deployed and non-deployed positions about the pivot axis 147 . It should be appreciated that the movement of the shells 33 , 35 is not limited to pivotal movement about the axis 147 .
- the shells 33 , 35 may, for example, be slidable or movable along a generally compound curve or path between the deployed and non-deployed positions.
- the diverting member 222 includes support frames 240 , 242 that are moveable between the deployed and non-deployed positions.
- the support frames 240 , 242 are similar to those of the previous embodiments but they are sized and shaped to define a diverting surface. 241 .
- the diverting surface 241 corresponds to an inner surface 243 of the support frames 240 , 242 when in the deployed position.
- the support members 240 , 242 may have a greater width than the previously described support members to deflect the flow of fluid from the discharge nozzle 14 .
- the diverting surface 241 intersects with the fluid flow to substantially reverse a portion of the fluid flow and direct the vehicle 12 in the second or reverse direction.
- the width of the support members 240 , 242 may be selected such that a balance of the drag cased by the support members 240 , 242 in the forward direction or non-deployed position and the amount of area available to contact the fluid in the deployed position is achieved. For example, one may optimize the contact area in the reverse direction or limit the drag dependent upon the design and performance objectives of the vehicle 12 .
- a leading edge portion 245 of the support members 240 , 242 acts as the ring 26 of the previously described embodiment.
- the leading edge portion 245 is angled to reduce its size radially in the flow direction of the fluid. More specifically, the annulus 231 is defined between the inner surface of the leading edge portion 245 of the support members 240 , 242 and the outer surface 30 of the housing 24 in the non-deployed position and narrows so as to accelerate the flow of fluid passing there through as the vehicle 12 is propelled in the first or forward direction.
- the accelerated fluid due to the reduction in cross section area of the annulus 231 in the flow direction mixes with the fluid exiting the discharge or exhaust nozzle 14 as a result of the lower pressure in the higher speed flow from the exhaust nozzle. This increases the mass flow rate and hence the momentum at the exit of the discharge nozzle 14 and thereby contributes to thrust enhancement.
- FIGS. 9 , 12 and 13 there is shown another alternative embodiment of the jet propulsion system 210 .
- This embodiment is similar to that described above with reference to FIGS. 10 and 11 except that the diverting members 222 or the support members 240 , 242 are positioned so they are not concentric or offset relative to a centerline of the discharge nozzle 14 .
- the discharge nozzle's position is upwards relative to the support members of the previously described embodiment.
- the diverting surface 231 of the support members 240 , 242 acts as a scoop to channel the flow of fluid around the curved shape of the diverting surface 231 .
- the offset is extreme such that the reverse thrust is fully diverted below the housing 24 . It should be appreciated that any degree of offset of the diverting member 222 relative to the exhaust nozzle 14 may be utilized.
- FIGS. 14-19 there is shown another alternative embodiment of the jet propulsion system 310 attached to a transom 311 .
- This embodiment is similar to that described above in FIGS. 10 and 11 with the addition of a ring 326 attached to the housing 24 and a change in the shape of the support members 340 , 342 .
- the annulus 331 is defined between the inner surface 328 of the ring 326 and the outer surface 30 of the housing 24 .
- the shape of the ring 326 narrows so as to accelerate the flow of fluid passing through the annulus 331 as the vehicle 12 is propelled in the first or forward direction.
- the ring 326 may also include a shaped leading edge 332 that reduces drag in the forward direction.
- the support members 340 , 342 no longer include a leading edge portion 245 as the ring 326 defines the annulus 331 with the housing 24 .
- This embodiment may also be offset relative to the discharge nozzle 14 , as described above. In other words, the discharge nozzle 14 may be moved upwards relative to the support members 340 , 342 in the deployed position, as described above.
- FIG. 20 there is shown an alternative embodiment of a jet propulsion system 410 .
- a discharge nozzle 14 having a nozzle housing 24 and ring 26 .
- the ring 26 forms an annulus 31 with a nozzle housing 24 .
- Water passes through the annulus 31 in which the cross sectional area is decreased in the axial direction to accelerate the flow as it passes through the exit plane in the same direction as the flow from the discharge or exhaust nozzle 14 .
- the additional mass flow of the water through the annulus 31 mixes with the flow from the jet discharge or exhaust nozzle 14 resulting in thrust augmentation.
- the extent of the thrust augmentation achieved is determined by the cross section area and axial length of the annulus 31 and the velocity of the flow from the discharge or exhaust nozzle 14 .
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Abstract
A jet propulsion system includes an inlet receiving a fluid, and a housing defining a discharge nozzle through which fluid is discharged to provide propulsion of a vehicle in a first direction. The jet propulsion system also includes a reverse mechanism movable between a deployed position redirecting fluid from the discharge nozzle toward the first direction and providing propulsion of the vehicle in a second direction substantially opposite the first direction and a non-deployed position allowing fluid to exit the discharge nozzle and provide propulsion of the vehicle in the first direction. The reverse mechanism produces a flow entrainment that enhances forward thrust while the reverse mechanism is in the non-deployed position which results in a net thrust gain over the thrust attributed to the discharge nozzle alone.
Description
- This application claims priority of U.S. Provisional Patent Application No. 61/027,240 filed Feb. 8, 2008, the content of which is incorporated herein by reference.
- The invention relates to the operation of jet propulsion systems. More particularly, this invention incorporates a reverse mechanism into the jet propulsion system utilizing a deflecting surface to redirect the flow from the primary jet exhaust nozzle to produce a reverse thrust.
- Jet propulsion is a well-known means of propelling a watercraft through the water. It is also well-known to provide a reverse gate or “bucket” for converting forward thrust into rearward thrust to the propel watercraft in a reverse direction.
- U.S. Pat. No. 5,344,344, which issued to Forsstrom on Sep. 6, 1994, describes a steering and reversing system for a marine jet propulsion unit. The system has a stationary nozzle for discharging a waterjet in the rearward direction from the unit and incorporates a pair of steering and reversing members mounted side by side at the rear end of the nozzle and individually pivot in opposite directions about upright axes from a non-deflecting position to first and second deflecting positions. In the non-deflecting position, the steering and reversing members form an extension of the nozzle in the rearward direction, while in the first deflecting position each member diverts a portion of the waterjet laterally outward by means of its front section. In the second deflecting position each member deflects a portion of the waterjet downward and forward by means of scoop-like members at its rear section.
- U.S. Pat. No. 3,937,172, which issued to Castoldi on Feb. 10, 1976, discloses a waterjet propelling apparatus for boats. The apparatus forces water by a pump through a nozzle directed a stern of a boat. A curved jet-deflecting surface deflects the water downward and forward and reverses the thrust, and a pair of steerable parallel rudder blades pivot in unison for laterally deflecting the jet. The jet-deflecting surface has symmetrical channel-like side panels which direct water escaping laterally from the clearance between the trailing edges of the rudder blades and the jet-deflecting surface forward towards the bow to enhance the reverse thrust, and a central portion which is shaped with blades for maintaining the clearance with the later constant for various pivotal deviations of the blades.
- U.S. Pat. No. 5,551,898, which issued to Matsumoto on Sep. 3, 1996, describes an exhaust nozzle arrangement for a waterjet propulsion unit. A number of embodiments of the steering nozzle and reverse thrust bucket arrangements for jet propelled watercraft are described. The steering nozzle, in addition to being mounted for steering movement about a vertically extending steering axis, is also mounted for trim adjustment about a horizontally extending axis. A cooperating reverse thrust bucket provides reverse thrust operation. The reverse thrust bucket is either mounted on the hull of the watercraft independent of the jet propulsion unit, on the outer housing of the jet propulsion unit independent of the steering nozzle, or on the steering nozzle.
- It remains desirable to provide a jet propulsion system with an improved reverse mechanism that provides robust performance when switching between forward, neutral and reverse directions. It also remains desirable to provide an improved reverse mechanism that enhances or at least does not degrade the performance of the jet propulsion system in the forward direction. It is also desirable to provide an improved reverse mechanism that may be manipulated to control damping of the attitude and motion of a vessel in any of the pitch, roll or yaw axes of the vessel.
- According to one aspect, a jet propulsion system includes a housing having a discharge nozzle through which fluid exits and provides propulsion of a vehicle along a first direction. The jet propulsion system also includes a reverse mechanism having a deflecting movable surface coupled to the housing for movement between a non-deployed position allowing fluid to exit the discharge nozzle and provide propulsion of the vehicle in a first direction and a deployed position forming a substantially hemispherical inner surface for redirecting flow from the discharge nozzle and providing propulsion of the vehicle in a second direction substantially opposite the first direction.
- According to another aspect, a jet propulsion system includes an inlet receiving a fluid, and a housing defining a discharge nozzle through which fluid is discharged to provide propulsion of a vehicle in a first direction. The jet propulsion system also includes a reverse mechanism movable between a deployed position redirecting fluid from the discharge nozzle toward the first direction and providing propulsion of the vehicle in a second direction substantially opposite the first direction and a non-deployed position allowing fluid to exit the discharge nozzle and provide propulsion of the vehicle in the first direction. The reverse mechanism produces a flow entrainment that enhances forward thrust while the reverse mechanism is in the non-deployed position which results in a net thrust gain over the thrust attributed to the discharge nozzle alone.
- According to another aspect, a jet propulsion includes a housing defining a discharge nozzle through which fluid exits and provides propulsion of a vehicle along a first direction. A reverse mechanism is pivotally coupled to the housing. The housing is moveable relative to the discharge nozzle in a pitch and steer axis wherein a thrust vector of fluid exiting the discharge nozzle may be manipulated to control damping of an attitude and motion of the vehicle in any of the pitch, roll and yaw axes.
- Advantages of the present invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings, wherein:
-
FIG. 1 is perspective view of a portion of a jet propulsion system according to one embodiment of the invention; -
FIG. 2 is an exploded perspective view of the jet propulsion system ofFIG. 1 ; -
FIG. 3 is an enlarged perspective view of a reverse mechanism for the jet propulsion system shown in a deployed position; -
FIG. 4 is an enlarged perspective view of the reverse mechanism for the jet propulsion system shown in a partially deployed position; -
FIG. 5 is a cross sectional view of the reversing mechanism for the jet propulsion system shown in a deployed position; -
FIG. 6 is a cross sectional view of the reversing mechanism for the jet propulsion system shown in a non-deployed position; -
FIG. 7 is a cross sectional view of the reversing mechanism for the jet propulsion system shown in a neutral position between the deployed and non-deployed positions; -
FIG. 8 is a cross sectional view of an alternative embodiment of the reversing mechanism for the jet propulsion system shown in the deployed position; -
FIG. 9 is a partial cross section view of another alternative of the reversing mechanism for the jet propulsion system shown in the deployed position; -
FIG. 10 is a partial perspective view of another alternative embodiment of the reversing mechanism in the deployed position; -
FIG. 11 is a partial perspective view of the alternative embodiment ofFIG. 10 in the non-deployed position; -
FIG. 12 is a partial perspective view of another alternative embodiment of the reversing mechanism in the deployed position; -
FIG. 13 is a partial perspective view of the alternative embodiment ofFIG. 12 in the non-deployed position; -
FIG. 14 is a partial perspective view of another alternative embodiment of the reversing mechanism in the deployed position; -
FIG. 15 is a partial perspective view of the alternative embodiment ofFIG. 14 in the non-deployed position; -
FIG. 16 is a partial perspective view of the alternative embodiment ofFIG. 14 in the non-deployed position including the transom and fixed portion of the vessel; -
FIG. 17 is a partial perspective view of the alternative embodiment ofFIG. 14 in the non-deployed position including the transom and fixed portion of the vessel; -
FIG. 18 is a partial perspective view of the alternative embodiment ofFIG. 14 in the deployed position including the transom and fixed portion of the vessel; -
FIG. 19 is an exploded perspective view of the alternative embodiment ofFIG. 14 ; -
FIG. 20 is a perspective view of an alternative embodiment of a nozzle and ring. - Referring to
FIGS. 1-7 , a jet propulsion system according to one embodiment of the invention is generally indicated at 10. Thejet propulsion system 10 includes an inlet that receives fluid into the system and an outlet ordischarge nozzle 14 through which fluid exits to provide thrust for moving avehicle 12 in a first direction. Discussed in greater detail below, thejet propulsion system 10 includes areverse mechanism 20, shown inFIGS. 3 and 4 , that reverses the thrust or a portion of the thrust from thedischarge nozzle 14 to move thevehicle 12 in a second direction opposite the first direction or to neutralize or hold thevehicle 12 in a generally fixed position relative to the body of fluid in which thevehicle 12 travels. Thereverse mechanism 20 is shown illustratively as part of ajet propulsion system 10 for a recreational water vehicle. It should, however, be appreciated that thereverse mechanism 20 may also be used in other jet propulsion systems, where in general an accelerated jet of fluid is expelled to generate thrust, such as turbojets, turbofans, rockets, ramjets, pulse jets, gas turbine engines, and the like. - The
reverse mechanism 20 is movable between non-deployed and deployed positions. In the non-deployed position, thereverse mechanism 20 allows fluid to exit thedischarge nozzle 14 to provide propulsion of thevehicle 12 in the first direction or “forward” thrust. In the non-deployed position thereverse mechanism 20 may be supported by aring 26 outside of thedischarge nozzle 14. Thering 26 forms anannulus 31 with anozzle housing 24. Water passes through theannulus 31 in which the cross sectional area is decreased in the axial direction to accelerate the flow as it passes through the exit plane in the same direction as the flow from the discharge orexhaust nozzle 14. The additional mass flow of the water through theannulus 31 mixes with the flow from the jet discharge orexhaust nozzle 14 resulting in thrust augmentation. The extent of the thrust augmentation achieved is determined by the cross section area and axial length of theannulus 31 and the velocity of the flow from the discharge orexhaust nozzle 14. The flow through theannulus 31 is a flow entrainment effect due to the lower pressure in the higher speed flow from thedischarge nozzle 14. In the deployed position, thereverse mechanism 20 redirects the fluid from thedischarge nozzle 14 from the first direction and provides propulsion of thevehicle 12 in the second direction producing “rearward” thrust. Thereverse mechanism 20 is also movable between the deployed and non-deployed position to provide varying degrees of forward thrust, rearward thrust or neutral. - In one embodiment of the invention, the
reverse mechanism 20 utilizes a substantially hemispherical shaped divertingassembly 22 for diverting or “reversing” the thrust from thedischarge nozzle 14. More specifically, aring 26 inFIGS. 3 and 4 is attached to ahousing 24 of thejet propulsion system 10. Thering 26 includes aninner surface 28 spaced apart from anouter surface 30 of thehousing 24 to define theannulus 31 through which fluid diverted by the divertingassembly 22 can flow. The divertingassembly 22 is coupled to thering 26 and is movable relative to thering 26 between the deployed and non-deployed positions. - The diverting
assembly 22 may include twomovable parts opening 36 is formed between the twoparts parts FIGS. 2 and 5 , theopening 36 is closed to prevent fluid from passing through the divertingassembly 22. In the non-deployed position, shown inFIGS. 1 and 6 , theopening 36 is open to allow fluid to pass therethrough. The twoparts assembly 22 are also movable to a neutral position between the deployed position and the non-deployed position, in which the amount of thrust in the first direction is substantially the same as the amount of thrust in the second direction. - In one embodiment, the diverting
assembly 22 may include afabric material 23. In particular, the divertingassembly 22 may be formed of Vectran or other suitable high tensile strength fabric. In this embodiment, the divertingassembly 22 may include a pair of movable support frames 40, 42 that supports the twoparts assembly 22 along theopening 36. Eachsupport frame ring 26 and provides movement of the twoparts assembly 22 between the deployed and non-deployed positions. Eachsupport frame housing 24 for rotation about acommon pivot axis 47. Eachsupport frame - As best shown in
FIGS. 4-7 , eachsupport frame orthogonal back 50 andside 52 walls. Theback walls 50 of the support frames 40, 42 extend outwardly from each other in a generally symmetrically opposite manner fromrespective side walls 52 when the divertingassembly 22 is in the deployed position. Further, theside walls 52 of the support frames 40, 42 are substantially parallel to each other when the divertingassembly 22 is in the deployed position. Eachpart assembly 22 includes alongitudinal pocket 54, shown inFIGS. 5 , 6, and 7, that extends along theopening 36 and receives one of the support frames 40, 42 therethrough. - The support frames 40, 42 are actuated between the deployed and non-deployed positions by an
actuating mechanism 60. Theactuating mechanism 60 may include a set ofarms pivot axis 47 of the support frames 40, 42. Eacharm arms pivot axis 47 causes corresponding rotation of the support frames 40, 42 about thepivot axis 47. In one embodiment, thearms frames pivot axis 47 so that pulling thearms FIGS. 1 , 3 and 4) results in movement of the support frames 40, 42 toward the deployed position. Thearms - The
housing 24 may also be movably coupled to thevehicle 12 for steering and/or vertical pitch control. In one aspect, the housing may be moveable to allow for simultaneous steering and pitch control. In the illustrated embodiment, thehousing 24 may be pivotally coupled to aframe 70, best seen inFIG. 2 , for movement about afirst pivot 72 relative to theframe 70. Theframe 70 is, in turn, pivotally coupled to a fixedportion 74 of thevessel 12 for movement of thehousing 24 andframe 70 together about asecond pivot 76 relative to the fixedportion 74 of thevessel 12.Cables FIG. 1 , may be used for controlling the movement of thehousing 24 about the first 72 and second pivots 76. In one aspect, thehousing 24 may be manipulated to control damping of the attitude and motion of thevehicle 12 in any of the pitch, roll or yaw axes in both the forward and reverse directions. Theframe 70 includes a tab extending off of theframe 70 and isolates movement in the steering and pitch axis to prevent control loop problems when controlling movement. - As stated above, the
reverse mechanism 20 also provides enhanced thrust while thereverse mechanism 20 is in the non-deployed position resulting in a net thrust gain over an amount of thrust attributable to thedischarge nozzle 14 alone. More specifically, theannulus 31 defined between theinner surface 28 of thering 26 and theouter surface 30 of thehousing 24 narrows so as to accelerate the flow of fluid passing therethrough as thevehicle 12 is propelled in the first or forward direction. The accelerated fluid, due to the reduction in cross section area of theannulus 31 in the flow direction mixes with the fluid exiting the discharge orexhaust nozzle 14 as a result of the lower pressure in the higher speed flow from thedischarge nozzle 14. This increases the mass flow rate and hence the momentum at the exit of thedischarge nozzle 14 and thereby contributes to thrust enhancement. - Referring to
FIG. 8 , an alternative embodiment of thejet propulsion system 110 is shown, wherein like components or features from the previous embodiment are indicated by numerals offset by 100. In this embodiment, the moving parts of the divertingassembly 122 are dimensionally stable or substantiallyrigid shells 33, 35 instead of theflexible fabric 23 of the previous embodiment. Theshells 33, 35 rotate generally telescopically relative to each other between the deployed and non-deployed positions about thepivot axis 147. It should be appreciated that the movement of theshells 33, 35 is not limited to pivotal movement about theaxis 147. Theshells 33, 35 may, for example, be slidable or movable along a generally compound curve or path between the deployed and non-deployed positions. - Referring to
FIGS. 10 and 11 , another alternative embodiment of thejet propulsion system 210 is shown, wherein the divertingmember 222 includes support frames 240, 242 that are moveable between the deployed and non-deployed positions. The support frames 240, 242 are similar to those of the previous embodiments but they are sized and shaped to define a diverting surface. 241. The divertingsurface 241 corresponds to aninner surface 243 of the support frames 240, 242 when in the deployed position. Thesupport members discharge nozzle 14. In the deployed position, the divertingsurface 241 intersects with the fluid flow to substantially reverse a portion of the fluid flow and direct thevehicle 12 in the second or reverse direction. The width of thesupport members support members vehicle 12. - In the embodiment depicted in
FIGS. 10 and 11 , aleading edge portion 245 of thesupport members ring 26 of the previously described embodiment. Theleading edge portion 245 is angled to reduce its size radially in the flow direction of the fluid. More specifically, theannulus 231 is defined between the inner surface of theleading edge portion 245 of thesupport members outer surface 30 of thehousing 24 in the non-deployed position and narrows so as to accelerate the flow of fluid passing there through as thevehicle 12 is propelled in the first or forward direction. The accelerated fluid, due to the reduction in cross section area of theannulus 231 in the flow direction mixes with the fluid exiting the discharge orexhaust nozzle 14 as a result of the lower pressure in the higher speed flow from the exhaust nozzle. This increases the mass flow rate and hence the momentum at the exit of thedischarge nozzle 14 and thereby contributes to thrust enhancement. - Referring to
FIGS. 9 , 12 and 13 there is shown another alternative embodiment of thejet propulsion system 210. This embodiment is similar to that described above with reference toFIGS. 10 and 11 except that the divertingmembers 222 or thesupport members discharge nozzle 14. In the depicted embodiment, the discharge nozzle's position is upwards relative to the support members of the previously described embodiment. In this manner the divertingsurface 231 of thesupport members surface 231. In the illustrated embodiment ofFIG. 9 , the offset is extreme such that the reverse thrust is fully diverted below thehousing 24. It should be appreciated that any degree of offset of the divertingmember 222 relative to theexhaust nozzle 14 may be utilized. - Referring to
FIGS. 14-19 there is shown another alternative embodiment of thejet propulsion system 310 attached to atransom 311. This embodiment is similar to that described above inFIGS. 10 and 11 with the addition of aring 326 attached to thehousing 24 and a change in the shape of thesupport members ring 326 and theouter surface 30 of thehousing 24. The shape of thering 326 narrows so as to accelerate the flow of fluid passing through the annulus 331 as thevehicle 12 is propelled in the first or forward direction. Thering 326 may also include a shaped leadingedge 332 that reduces drag in the forward direction. Thesupport members leading edge portion 245 as thering 326 defines the annulus 331 with thehousing 24. This embodiment may also be offset relative to thedischarge nozzle 14, as described above. In other words, thedischarge nozzle 14 may be moved upwards relative to thesupport members - Referring to
FIG. 20 , there is shown an alternative embodiment of a jet propulsion system 410. In the depicted embodiment there is shown adischarge nozzle 14 having anozzle housing 24 andring 26. Thering 26 forms anannulus 31 with anozzle housing 24. Water passes through theannulus 31 in which the cross sectional area is decreased in the axial direction to accelerate the flow as it passes through the exit plane in the same direction as the flow from the discharge orexhaust nozzle 14. The additional mass flow of the water through theannulus 31 mixes with the flow from the jet discharge orexhaust nozzle 14 resulting in thrust augmentation. The extent of the thrust augmentation achieved is determined by the cross section area and axial length of theannulus 31 and the velocity of the flow from the discharge orexhaust nozzle 14. - The invention has been described in an illustrative manner. It is, therefore, to be understood that the terminology used is intended to be in the nature of words of description rather than of limitation. Many modifications and variations of the invention are possible in light of the above description. Thus, within the scope of the appended claims, the invention may be practiced or applied other than as specifically described.
Claims (25)
1. A jet propulsion system comprised of:
a housing having a discharge nozzle through which fluid exits and provides propulsion of a vehicle along a first direction; and
a reverse mechanism having a diverting assembly pivotally coupled to the housing for movement between a non-deployed position allowing fluid to exit the discharge nozzle and provide propulsion of the vehicle in a first direction and a deployed position forming a substantially hemispherical inner surface for redirecting fluid from the discharge nozzle and providing propulsion of the vehicle in a second direction substantially opposite the first direction.
2. The jet propulsion system as set forth in claim 1 , wherein the reverse mechanism includes a ring attached to the housing, the ring having an inner surface spaced apart from an outer surface of the housing forming an annulus through which flow will pass.
3. The jet propulsion system as set forth in claim 2 , wherein the reverse mechanism includes a substantially hemispherically shaped diverting assembly coupled to the ring for movement between the deployed and non-deployed positions.
4. The jet propulsion system as set forth in claim 3 , wherein the diverting assembly is formed of a fabric material.
5. The jet propulsion system as set forth in claim 4 , wherein the fabric material includes a opening formed between two parts of the diverting assembly, the two parts being movable between the deployed position, in which the opening is closed to prevent fluid from passing therethrough, and non-deployed position, in which the opening is open to allow fluid to pass therethrough.
6. The jet propulsion system as set forth in claim 5 , wherein the diverting assembly includes a pair of movable support frames supporting the two parts of the diverting assembly along the opening,
7. The jet propulsion system as set forth in claim 6 , wherein each support frame is pivotally coupled to the ring and provides movement of the two parts of the diverting assembly between the deployed and non-deployed positions.
8. The jet propulsion system as set forth in claim 6 , wherein each support frame has opposite ends pivotally coupled to opposite sides of the housing, each support frame extending generally arcuately between the opposite ends.
9. The jet propulsion system as set forth in claim 5 , wherein the two parts of the diverting assembly are movable to a neutral position between the deployed position and the non-deployed position, in which the amount of thrust in the first direction is substantially the same as the amount of thrust in the second direction.
10. The jet propulsion system as set forth in claim 2 , wherein the housing includes a fixed portion interconnected to the vehicle and a movable portion movably coupled to the fixed portion, the discharge nozzle being disposed on the movable portion of the housing.
11. The jet propulsion system as set forth in claim 10 , wherein movable portion is pivotally coupled to the fixed portion for movement along at least one pivot axis.
12. The jet propulsion system as set forth in claim 10 including a support frame pivotally coupled to the housing for movement along a generally horizontal first axis.
13. The jet propulsion system as set forth in claim 12 , wherein the movable portion is coupled to the support frame for movement therewith about the first axis.
14. The jet propulsion system as set forth in claim 13 , wherein the movable portion is pivotally coupled to the support frame for movement about a second axis.
15. The jet propulsion system as set forth in claim 14 , wherein the first axis and second axis are substantially orthogonal relative to each other.
16. The jet propulsion system as set forth in claim 3 , wherein the diverting assembly includes a plurality of dimensionally stable shells movable between the deployed and non-deployed positions.
17. The jet propulsion system as set forth in claim 16 , wherein the shells are movable about a common pivot axis relative to each other.
18. A jet propulsion system comprising:
a housing defining a discharge nozzle through which fluid exits and provides propulsion of a vehicle along a first direction; and
a reverse mechanism movable between a deployed position redirecting fluid from the discharge nozzle toward the first direction and providing propulsion of the vehicle in a second direction substantially opposite the first direction and a non-deployed position allowing fluid to exit the discharge nozzle and provide propulsion of the vehicle in the first direction, the reverse mechanism enhancing forward thrust while the reverse mechanism is in the non-deployed position by increasing the mass flux and momentum of the flow at the exit of the discharge nozzle through flow entrainment.
19. The jet propulsion system as set forth in claim 18 , wherein the reverse mechanism includes a ring securely fixed to the housing, the ring having an inner surface spaced apart from an outer surface of the housing to define an annular channel through which fluid diverted by the reverse mechanism can flow, the annular channel narrowing to accelerate fluid passing therethrough.
20. The jet propulsion system as set forth in claim 18 , wherein the reverse mechanism includes a pair of movable support frames pivotally coupled to the housing moveable between the deployed and non-deployed positions an inner surface of the support members spaced apart from an outer surface of the housing in the non-deployed position to define an annular channel through which fluid diverted by the reverse mechanism can flow, the annular channel narrowing to accelerate fluid passing therethrough.
21. The jet propulsion system as set forth in claim 18 , wherein the reverse mechanism includes a diverting assembly with a curved inner surface for reversing fluid exiting the discharge nozzle producing reverse thrust.
22. The jet propulsion system as set forth in claim 18 , wherein the reverse mechanism is offset relative to a center line of the discharge nozzle.
23. A jet propulsion system comprising:
a housing defining a discharge nozzle through which fluid exits and provides propulsion of a vehicle along a first direction; and
a reverse mechanism pivotally coupled to the housing, the housing moveable relative to the discharge nozzle in a pitch and steer axis wherein a thrust vector of fluid exiting the discharge nozzle may be manipulated to control damping of an attitude and motion of the vehicle in any of the pitch, roll and yaw axes.
24. The jet propulsion system as set forth in claim 23 wherein the reverse mechanism is movable between a deployed position redirecting fluid from the discharge nozzle toward the first direction and providing propulsion of the vehicle in a second direction substantially opposite the first direction and a non-deployed position allowing fluid to exit the discharge nozzle and provide propulsion of the vehicle in the first direction, the reverse mechanism enhancing forward thrust while the reverse mechanism is in the non-deployed position by increasing the mass flux and momentum of the flow at the exit of the discharge nozzle through flow entrainment.
25. A jet propulsion system attached to a watercraft comprising:
a housing defining a discharge nozzle through which fluid exits and provides propulsion of a vehicle along a first direction; and
a ring securely fixed to the housing, the ring having an inner surface spaced apart from an outer surface of the housing to define an annular channel through which fluid diverted by the reverse mechanism can flow, the annular channel narrowing to accelerate fluid passing therethrough.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/367,923 US20090203270A1 (en) | 2008-02-08 | 2009-02-09 | Reverse mechanism for a jet system |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US2724008P | 2008-02-08 | 2008-02-08 | |
US12/367,923 US20090203270A1 (en) | 2008-02-08 | 2009-02-09 | Reverse mechanism for a jet system |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090203270A1 true US20090203270A1 (en) | 2009-08-13 |
Family
ID=40939275
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/367,923 Abandoned US20090203270A1 (en) | 2008-02-08 | 2009-02-09 | Reverse mechanism for a jet system |
Country Status (3)
Country | Link |
---|---|
US (1) | US20090203270A1 (en) |
EP (1) | EP2250080A4 (en) |
WO (1) | WO2009100418A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2467916C1 (en) * | 2011-05-18 | 2012-11-27 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Ship propulsor |
CN104908918A (en) * | 2015-05-22 | 2015-09-16 | 黄塬森 | Backward steering device for propelling and direction control in water |
EP3141472A4 (en) * | 2014-04-07 | 2018-01-17 | Shenzhen Yunzhou Innovation Technology Company Ltd | Podded all-direction pump-jet vector propeller |
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US3266733A (en) * | 1963-07-15 | 1966-08-16 | Elmer E Goehler | Hydraulic boat propelling, guiding and reversing means |
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AU5887299A (en) * | 1998-09-24 | 2000-04-10 | Cwf Hamilton & Co Limited | Improvements relating to steering devices for water jet propulsion |
RU2205774C1 (en) * | 2002-05-06 | 2003-06-10 | Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт им. акад. А.Н.Крылова" | Water-jet propulsion and steering complex |
JP4272135B2 (en) * | 2004-09-10 | 2009-06-03 | 本田技研工業株式会社 | Water jet propulsion machine |
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2009
- 2009-02-09 EP EP09707662A patent/EP2250080A4/en not_active Withdrawn
- 2009-02-09 US US12/367,923 patent/US20090203270A1/en not_active Abandoned
- 2009-02-09 WO PCT/US2009/033534 patent/WO2009100418A1/en active Application Filing
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US3266733A (en) * | 1963-07-15 | 1966-08-16 | Elmer E Goehler | Hydraulic boat propelling, guiding and reversing means |
US3957207A (en) * | 1974-08-05 | 1976-05-18 | Chronic Bill M | Gimball nozzle-trim |
US4538997A (en) * | 1982-01-27 | 1985-09-03 | Kjell Haglund | Reversing means in water-jet propulsion units |
US5154650A (en) * | 1989-08-03 | 1992-10-13 | Sanshin Kogyo Kabushiki Kaisha | Water jet propulsion unit |
US5312275A (en) * | 1993-01-11 | 1994-05-17 | Frank Place | Jet boat diverter nozzle with built-in ride plate |
US5803775A (en) * | 1995-06-26 | 1998-09-08 | Yamaha Hatsudoki Kabushiki Kaisha | Steering arrangement for jet propulsion unit |
US6102756A (en) * | 1997-12-03 | 2000-08-15 | Bombardier Inc. | Turning-aid nozzle |
US7387552B2 (en) * | 2005-03-31 | 2008-06-17 | Honda Motor Co., Ltd. | Trim adjusting device for small surface boat |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
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RU2467916C1 (en) * | 2011-05-18 | 2012-11-27 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Ship propulsor |
EP3141472A4 (en) * | 2014-04-07 | 2018-01-17 | Shenzhen Yunzhou Innovation Technology Company Ltd | Podded all-direction pump-jet vector propeller |
CN104908918A (en) * | 2015-05-22 | 2015-09-16 | 黄塬森 | Backward steering device for propelling and direction control in water |
Also Published As
Publication number | Publication date |
---|---|
EP2250080A4 (en) | 2012-05-23 |
EP2250080A1 (en) | 2010-11-17 |
WO2009100418A1 (en) | 2009-08-13 |
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