US20090137165A1 - Newtonian thrust cowl array - Google Patents
Newtonian thrust cowl array Download PDFInfo
- Publication number
- US20090137165A1 US20090137165A1 US12/365,152 US36515209A US2009137165A1 US 20090137165 A1 US20090137165 A1 US 20090137165A1 US 36515209 A US36515209 A US 36515209A US 2009137165 A1 US2009137165 A1 US 2009137165A1
- Authority
- US
- United States
- Prior art keywords
- outlet
- flow
- port
- starboard
- bypass
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 239000012530 fluid Substances 0.000 claims abstract description 69
- 238000004891 communication Methods 0.000 claims description 15
- 238000007789 sealing Methods 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 238000005259 measurement Methods 0.000 description 2
- 241000284156 Clerodendrum quadriloculare Species 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000037361 pathway Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
-
- 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
- B63H11/117—Pivoted vane
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H25/00—Steering; Slowing-down otherwise than by use of propulsive elements; Dynamic anchoring, i.e. positioning vessels by means of main or auxiliary propulsive elements
- B63H25/46—Steering or dynamic anchoring by jets or by rudders carrying jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/20—Adaptations of gas-turbine plants for driving vehicles
- F02C6/203—Adaptations of gas-turbine plants for driving vehicles the vehicles being waterborne vessels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/90—Application in vehicles adapted for vertical or short take off and landing (v/stol vehicles)
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/3367—Larner-Johnson type valves; i.e., telescoping internal valve in expanded flow line section
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/8593—Systems
- Y10T137/86493—Multi-way valve unit
- Y10T137/86718—Dividing into parallel flow paths with recombining
- Y10T137/86759—Reciprocating
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/8593—Systems
- Y10T137/86493—Multi-way valve unit
- Y10T137/86879—Reciprocating valve unit
- Y10T137/86887—Combined disk or plug and gate or piston
Definitions
- the Newtonian Thrust Cowl Array is a three-way valve with a flow diffuser to reduce downstream turbulence. This invention creates a relatively flat downstream velocity flow profile which results in more accurate flow measurements by downstream ultrasonic flow meters.
- This three-way valve may be used in a variety of other situations, e.g., vertical take-off and landing (“VTOL”) jet airplanes to direct the thrust from the jet engines or ships.
- VTOL vertical take-off and landing
- Flow diffusers of various types have been previously used to reduce turbulence in valves and piping systems in general.
- Robert H. Welker the inventor of the present patent application has also developed prior art flow diffusers shown in U.S. Pat. Nos. 5,769,388; 6,250,330; 6,289,934 and 6,439,267.
- the flow diffuser shown in U.S. Pat. No. 5,769,388 was used in conjunction with a control valve to reduce downstream turbulence.
- U.S. Pat. No. 6,250,330 discloses a diaphragm regulator with removable diffuser.
- the removable flow diffuser in U.S. Pat. No. 6,289,934 was used in an elbow to reduce downstream turbulence.
- the adjustable flow diffuser in U.S. Pat. No. 6,439,267 was also used in elbows and piping systems.
- a three-way valve with a flow diffuser reduces downstream turbulence and produces a flat velocity profile in the flowing fluid, which is an advantage to ultrasonic measurement.
- it can be used to direct the thrust from a jet engine in a VTOL airplane.
- Larger versions of the three-way valve can also be used in ships with side thrusters.
- FIG. 1 is a section view of the three-way valve with flow diffuser in the open position to the run valve outlet.
- FIG. 2 is an exploded section view of the movable valve element of FIG. 1 .
- FIG. 3 is a front view of the movable valve element of FIG. 2 along the line 3 - 3 .
- FIG. 4 is a section view of a web of FIG. 3 along the line 4 - 4 .
- FIG. 5 is a section view of the three-way valve with flow diffuser of FIG. 1 in the open position to the bypass outlet.
- FIG. 6 is a section view of the three-way valve with flow diffuser of FIG. 1 open to both the run outlet and the bypass outlet.
- FIG. 7 is a section view of a VTOL jet airplane with the three-way valve with flow diffuser therein.
- FIG. 8 is a top plan view of the VTOL jet airplane of FIG. 7 .
- FIG. 9 is a plan view of a ship with two three-way valves with flow diffusers therein.
- FIG. 10 is a section view of the ship of FIG. 9 .
- FIG. 11 is a plan view of the ship of FIG. 9 reversing thrust towards the bow.
- FIG. 12 is a plan view of the ship of FIG. 9 using the mid-ships thrusters to maneuver.
- FIG. 13 is a plan view of the flow diffuser.
- FIG. 14 is an enlarged section view of the primary valve seat and the bypass valve seat in the flow diffuser along the line 14 - 14 of FIG. 13 .
- FIG. 15 is a plan view of the flow diffuser in the receptacle formed by the body of the three-way valve.
- a plurality of flow arrows indicates a generally flat velocity profile of fluid passing through the flow diffuser.
- the three-way valve with flow diffuser is generally identified by the numeral 14 .
- the body 22 includes a primary frame 24 and a removable cap 26 which is connected to the primary frame by a plurality of bolts, only one of which 28 is shown in the drawings.
- the primary frame and the cap form a receptacle 30 sized and arranged to receive the removable flow diffuser 32 .
- the cap disengages from the primary frame allowing maintenance or removal of the flow diffuser 32 .
- a channel and seal 33 are positioned in the cap 26 to engage the primary frame 24 and seal the receptacle 30 .
- An alignment pin 34 is seated in an aperture 36 of the primary frame and an aperture 38 in the flow diffuser.
- the three-way valve with flow diffuser 20 defines a run inlet 40 , a run outlet 42 , a bypass inlet 44 and a bypass outlet 46 .
- the flow diffuser 32 has a flow diffuser inlet 48 , better seen in FIG. 12 and a flow diffuser outlet 50 .
- the bypass inlet 44 may also be referred to as a vertical takeoff inlet and the bypass outlet 46 may also be referred to as a vertical takeoff outlet.
- FIGS. 1 , 5 and 6 the three-way valve with flow diffuser 14 has three operational positions show in FIGS. 1 , 5 and 6 .
- FIG. 2 fluid flows from the run inlet 40 to the run outlet 42 as shown by the flow arrows.
- FIG. 1 may sometimes be referred to as the full open or full run position with the bypass valve 18 in the full closed position.
- FIG. 5 fluid flows from the run inlet 40 , through the bypass inlet 44 to the flow diffuser inlet 48 , the flow diffuser outlet 50 to the bypass outlet 46 , as shown by the flow arrows.
- FIG. 2 may sometimes be referred to as the bypass valve in the full open position and the run valve 16 in the full closed position.
- FIG. 6 all of the fluid enters the run inlet, and a portion exits the run outlet 42 and the other portion flow through the flow diffuser 32 and exits the bypass outlet 46 .
- FIG. 3 may sometimes be described as the split flow position.
- a movable valve element 52 includes a primary valve element 54 and a bypass valve element 56 .
- a primary valve seat 58 is formed opposite to a bypass valve seat 60 on a protruding portion of the flow diffuser, better seen in FIG. 13 .
- the bypass valve element 56 is in sealing engagement with the bypass valve seat 60 sealing against fluid flow into the flow diffuser 32 and the bypass outlet 46 .
- the primary valve element 54 is in sealing engagement with the primary valve seat 58 sealing against fluid flow to the run outlet 42 .
- there is no seal on either the primary valve seat 58 or the bypass valve seat 60 thus allowing fluid to flow to both the run valve outlet 42 and the bypass outlet 46 .
- a channel and seal 62 are formed in the removable cap 26 to seal against the bypass valve element 56 .
- the seals 62 and 33 are shown as o-rings, but may be metal seals depending on the type of service required.
- a support 64 is connected to the tail cone 66 .
- the support extends from the primary frame 24 to the tail cone and may be a plurality of vanes or a single column to hold the tail cone in place.
- the support 64 holds the tail cone 66 in position in the three-way valve.
- the tail cone 66 supports the primary valve element 54 and a channel 68 supports the bypass valve element 56 .
- the movable valve element 52 is supported by the channel 68 on the end proximate the run inlet 40 and by the support 64 on the end proximate the run outlet 42 .
- the movable valve element slides back and forth in the channel 68 and over the tail cone 66 which act as supports. These supports allow the movable valve element 54 to move back and forth to the different positions shown in FIGS. 1 , 5 and 6 .
- the movable valve element 54 may be actuated by any suitable means 78 , such as a mechanical screw, not shown or by hydraulic means shown in FIGS. 1 , 5 and 6 .
- the hydraulic actuation means includes a pressurized source of hydraulic fluid, not shown, and a control means, not shown, to apply and drain pressurized hydraulic fluid through the conduit 80 .
- the primary valve element 54 forms a cylinder 82 that slides over the tail cone 66 forming a chamber 84 to receive hydraulic fluid from the pressurized source, not shown. Pressurized fluid flows through the conduit 80 to the chamber 84 .
- the tail cone 66 is held in a stationary position by the support 64 .
- the run valve 16 includes the body 22 , the movable valve element 52 , and the means for actuating 78 .
- the bypass valve includes the flow diffuser 32 , the movable valve element 52 , the body 22 and the means for actuating 78 .
- the three-way valve 14 includes the run valve 16 and the bypass valve 18 .
- the movable valve element 52 includes the primary valve element 54 and the bypass valve element 56 , which are dissembled and shown in section view in FIG. 2 .
- a pointed bolt 70 is a means for connecting the bypass valve element to the primary valve element.
- the bypass valve element forms a cylindrical closure 72 , as best seen in FIG. 3 , with a plurality of webs 74 extending from the cylindrical closure to a center 76 which is sized and arranged to receive the bolt 70 .
- a threaded receptacle 71 is formed in the primary valve element to receive the bolt 70 .
- the webs 74 are aerodynamic in cross section as shown in FIG. 4 .
- the movable valve element 52 is shown in these figures being formed from several different parts; however, the actual construction is a matter of manufacturing convenience. For example, movable valve element formed from one part may also be suitable for this invention.
- a thrust controller 98 is positioned in a jet aircraft 100 .
- the jet aircraft is designed for vertical takeoff and landing (“VTOL”).
- the jet aircraft has a jet engine 102 , schematically portrayed in these drawings, with an air intake 104 and an exhaust 106 connected to the thrust controller 98 which is connected to both the tail pipe 108 and vertical takeoff outlet 110 .
- An adjustable door 112 covers the vertical takeoff outlet 110 and normally is in the closed position as shown in FIG. 7 during flight. However, the door is opened to various angles during vertical takeoff and landing maneuvers. If the door 112 is only partially opened, it helps the aircraft 100 to slow down in preparation for landing. The door 112 will be fully opened during the vertical phase of takeoff and landing.
- the thrust controller 98 is the same as the three-way valve 14 , except that the seals 33 and 62 must be suitable for service with very hot gases, such as those generated by jet engines and the other components of the valve must likewise be suitable for such extreme service.
- the parts and components of the thrust controller 98 have the same names and identification numerals of the three-way valve 14 .
- the bypass outlet 46 is in fluid communication with the vertical takeoff outlet 110 to allow VTOL.
- the thrust controller 98 is actuated into the position of FIG. 5 and the adjustable door 112 will be fully opened, prior to starting the jet engine 102 .
- the hot exhaust from the jet engine will pass through the bypass outlet 46 and into the vertical takeoff outlet 110 of the aircraft 100 .
- This thrust will be directed towards the ground, allowing the aircraft to lift off.
- the thrust controller will be shifted to the position of FIG. 6 , allowing some of the hot gases to exit the tailpipe 108 of the aircraft.
- the thrust controller 98 will be adjusted to the position of FIG. 1 with all the hot gases from the jet engine exiting the tailpipe 108 .
- the adjustable door 112 is fully closed.
- a ship 130 is shown in plan view and in section view.
- the ship may sometimes be generically referred to as a watercraft.
- the watercraft 130 has a bow 132 , a stem 134 , a port side 136 and a starboard side 138 .
- the watercraft has a port power plant 140 to drive a port propulsion unit 142 which is in fluid communication with a port thrust controller 144 .
- the watercraft has a starboard power plant 146 to drive a starboard propulsion unit 148 which is in fluid communication with a starboard thrust controller 150 .
- the port water intake 152 is located at the bottom 154 of the watercraft.
- the starboard water intake is likewise located at the bottom of the watercraft.
- the port turbine outlet 156 is in fluid communication with the run inlet 40 of the port thrust controller 144 and the run outlet 42 is in fluid communication with the port thrust conduit 158 .
- the port thrust conduit outlet 160 is located at the stem of the watercraft.
- the starboard turbine outlet 162 is in fluid communication with the run inlet 40 A of the starboard thrust controller 150 and the run outlet 42 A is in fluid communication with the starboard thrust conduit 164 .
- the starboard thrust conduit outlet 166 is located at the stern of the watercraft.
- a port rudder 168 is supported by an upper port rudder stanchion and a lower port rudder stanchion.
- a starboard rudder 174 is supported by an upper starboard rudder stanchion, not shown, and a lower starboard rudder stanchion, not shown.
- a rudder control means independently controls the direction of each rudder. Fluid flows from the port water intake, through the port propulsion unit 143 , the port thrust controller 144 , the port thrust conduit 158 and exits the port thrust conduit outlet 160 at the port rudder 168 . Likewise fluid flows through the starboard water intake, not shown, through the starboard propulsion unit 148 , the starboard thrust controller 150 , the starboard thrust conduit 164 and exits the starboard thrust conduit outlet 166 at starboard rudder 174 .
- An adjustable port turning plane 182 is positioned proximate the port amidships outlet 184 and an adjustable starboard turning plane 186 is positioned proximate the starboard amidships outlet.
- the bypass outlet 46 of the port thrust controller 144 is in fluid communication with the port amidships outlet 184 ; the bypass outlet 46 A of the starboard thrust controller 150 is in fluid communication with the starboard amidships outlet 188 .
- These amidships outlets may be used to reverse direction or slow down forward progress of the watercraft as shown in FIG. 11 or they may be used to help maneuver the watercraft as shown in FIG. 12 .
- FIG. 11 is a plan view of the watercraft 130 of FIG. 9 , except the port thrust controller 144 and the starboard thrust controller 150 have been actuated so fluid passes through the bypass outlet 46 and 46 A respectively as indicated by the flow arrows and not the port thrust conduit outlet 160 or the starboard thrust conduit outlet 166 at the stem 134 .
- the adjustable port turning plane 182 and the adjustable starboard turning plane 186 have been opened to redirect the fluid flow towards the bow 132 of the watercraft 130 . Fluid flow as shown in FIG. 11 will slow forward progress of the watercraft, if it has been making way, and will ultimately bring the watercraft to a stop. If the watercraft is not making way, the fluid flow in FIG. 11 will cause the watercraft to move in a reverse direction.
- FIG. 13 is a plan view of the watercraft 130 of FIG. 9 , except the port thrust controller has been actuated so fluid exits through the bypass outlet 46 as shown by the flow arrow. Further, the starboard rudder has been turned to direct fluid flow from the starboard thrust conduit outlet 166 in the starboard direction. The net effect of the fluid flow pattern shown in FIG. 12 is to turn the watercraft in the starboard direction as indicated by the arrow at the bow 132 .
- FIG. 13 is a plan view of the removable flow diffuser 32 along the line 13 - 13 of FIG. 1 .
- the cylindrical closure 72 and the pointed bolt 70 have been omitted from FIG. 13 to better show the flow diffuser 32 .
- the alignment pin 34 is shown in phantom and is responsible for properly aligning the vanes in the three-way valve 14 .
- Similar flow diffusers are shown in U.S. Pat. Nos. 5,469,388; 6,250,330; 6,289,934 and 6,439,267 which are incorporated herein by reference.
- FIG. 14 is an enlargement of the primary valve seat 58 and the bypass valve seat 60 which are a part of the removable flow diffuser 32 .
- the opposing valve seats 58 and 60 are not shown in the aforementioned four patents concerning flow diffusers.
- a front central vane 200 points towards the bypass outlet 46 as better seen in FIG. 1 .
- a rear central vane 202 receives the alignment pin 34 shown in phantom.
- Disposed between the front central vane 200 and the rear central vane 202 is a first right vane 204 , a second right vane 206 , a third right vane 208 , a fourth right vane 210 , a fifth right vane 212 , a sixth right vane 214 and a seventh right vane 216 .
- Between the front central vane 200 and the first right vane 204 is a first right flow passageway 220 .
- Between the first right vane 204 and the second right vane 206 is a second right flow passageway 222 .
- first left flow passageway 260 Between the front central vane 200 and the first left vane 240 is a first left flow passageway 260 . Between the first left vane 240 and the second left vane 242 is a second left flow passageway 262 . Between the second left vane 242 and the third left vane 244 is a third left flow passageway 264 . Between the third left vane 244 and the fourth left vane 246 is a fourth left flow passageway 266 . Between the fourth left vane 246 and the fifth left vane 248 is a fifth left flow passageway 268 . Between the fifth left vane 249 and the sixth left vane 250 is a sixth left flow passageway 270 . Between the sixth left vane 250 and the seventh left vane 252 is a seventh left flow passageway 272 . Between the seventh left vane 252 and the rear central vane 202 is the eighth left flow passageway 274 .
- fluid enters the three-way valve 14 as shown by the flow arrow A, through the run inlet 40 .
- the fluid then passes through the bypass valve element 56 as indicated by the flow arrows E and F.
- the fluid then flows into the bypass inlet 44 , the circular flow diffuser inlet 48 and into the right flow passageways 220 , 222 , 224 , 226 , 228 , 230 , 232 and 234 and the left flow passageways, 260 , 262 , 264 , 266 , 268 , 270 , 272 and 274 .
- the flow path of the fluid into the flow diffuser is best seen in FIG. 15 and is represented by the starburst of flow arrows at the center of the figure.
- the shortest pathway from the flow diffuser inlet 48 to the flow diffuser outlet 50 is through the first right flow passageway 220 and the first left flow passageway 260 .
- the flow arrow F shows fluid passing from the flow diffuser inlet 48 into the first right flow passageway 220 .
- the flow arrow G shows fluid leaving the first right flow passageway and passing through the flow diffuser outlet 50 .
- the longest distance that fluid must travel from the flow diffuser inlet 48 to the flow diffuser outlet 50 is through the eighth right flow passageway 234 and the eighth left flow passageway 274 .
- the flow arrow E shows fluid leaving the flow diffuser inlet 48 and passing into the eighth right flow passageway 234 .
- the flow arrow I shows fluid leaving the eighth right flow passageway 234 and the flow diffuser outlet 50 .
- the prior art flow diffuser of U.S. Pat. No. 6,439,267 created a non-uniform velocity flow profile as shown pictorially in FIG. 15 of that patent.
- One purpose of the flow diffuser 32 of the present invention is to produce a generally flat velocity profile indicated by the dashed line 294 , as better seen in FIG. 15 of the present patent application.
- a generally flat velocity profile 294 is helpful to ultrasonic flow meters.
- the non-uniform velocity profile in the prior art sometimes distorts the accuracy of ultrasonic flow meters.
- the generally flat velocity profile 294 of the present application is created by strategically positioning choke points and flow restrictions in the left and right flow passageways to slow down some fluid molecules and to accelerate others.
- the choke point indicated by the dashed circle 280 encloses a protrusion 282 on first right vane 204 .
- the protrusion 282 creates a choke point at the dashed circle 280 in the second right flow passageway 222 which slows the speed of fluid as it passes through the choke point 280 .
- a similar protrusion 284 is formed on first left vane 240 which slows the speed of fluid as it passes through the second left flow passageway 262 .
- a right protrusion 286 is formed on the right side of front central vane 200 and a left protrusion 288 is formed on the left side of the front central vane 200 creating choke points in the first right passageway 220 and the first left flow passageway 260 .
- the right flow constriction 290 in the eighth right flow passageway 234 and the left flow constriction 292 in the eighth left flow passageway 274 are as far away from the circular flow diffuser inlet 48 as possible to speed up the fluid flow in the two longest passageways.
- the fluid molecules traveling through the flow passageways, 220 and 260 have the shortest distance to travel from the circular flow diffuser inlet 48 , better seen in FIG. 5 , to the flow diffuser outlet 50 , as better seen in FIGS. 5 and 15 ; thus the velocity of these molecules needs to be slowed down by the choke points 286 and 288 to give the molecules traveling a greater distance time to catch up, such as those traveling in the eighth right flow passageway 234 and the eighth left flow passageway 274 .
- Choke points 282 and 284 are placed in the flow passageways 222 and 262 in which the fluid molecules have a shorter distance of travel compared with flow passageways 232 and 272 which have a longer distance to travel from the circular flow diffuser inlet 48 to the flow diffuser outlet 250 .
- a protrusion 296 is formed on vane 206 , creating a choke point in right flow passageway 226 to slow the velocity of the fluid molecules; a protrusion 298 is formed on vane 242 creating a choke point in left flow passageway 264 to slow the velocity of the fluid molecules.
- An additional protrusion 298 is formed on vane 242 and protrusion 300 is formed on vane 242 , again creating choke points to slow the velocity of the fluid molecules passing through the aforementioned passageways.
- a flow restriction 304 is placed in the right flow passageway 234 and a flow restriction 306 is placed in the left flow passageway 272 .
- a flow restriction 308 is placed in right flow passageway 230 and a flow restriction 310 is placed in left flow passageway 270 .
- a flow restriction 312 is placed in right flow passageway 228 and a flow restriction 314 is placed in left flow passageway 268 to speed up the fluid molecules so the overall velocity profile 294 is substantially flat.
- the cross sectional profile of the bypass outlet 46 is similar to the cross sectional profile shown in FIGS. 6-9 of U.S. Pat. No. 6,289,934, which is incorporated herein by reference.
- the cross sectional area of the run inlet 40 shall be approximately equal to the cross sectional area of the run outlet 42 .
- the cross sectional area of the run inlet 40 shall be approximately equal to the cross sectional area of the bypass outlet 46 .
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ocean & Marine Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Lift Valve (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The three-way valve allows fluid flow to be selectively directed to a run outlet, a bypass outlet or both at the same time. The three-way valve includes a flow diffuser with a primary valve seat positioned opposite a bypass valve seat. Choke points and flow restrictions, strategically positioned in the flow diffuser create a substantially flat velocity profile downstream of the bypass outlet. Larger versions of this three-way valve may be used in Vertical Takeoff and Landing (“VTOL”) aircraft. Other versions may be used in ships and other watercraft.
Description
- This Application is a Divisional Application of application Ser. No. 11/161,033, filed Jul. 20, 2005, now allowed, of the same title, the disclosure of which is incorporated herein by reference.
- The Newtonian Thrust Cowl Array is a three-way valve with a flow diffuser to reduce downstream turbulence. This invention creates a relatively flat downstream velocity flow profile which results in more accurate flow measurements by downstream ultrasonic flow meters.
- This three-way valve may be used in a variety of other situations, e.g., vertical take-off and landing (“VTOL”) jet airplanes to direct the thrust from the jet engines or ships.
- Flow diffusers of various types have been previously used to reduce turbulence in valves and piping systems in general. For example, Robert H. Welker, the inventor of the present patent application has also developed prior art flow diffusers shown in U.S. Pat. Nos. 5,769,388; 6,250,330; 6,289,934 and 6,439,267. The flow diffuser shown in U.S. Pat. No. 5,769,388 was used in conjunction with a control valve to reduce downstream turbulence. U.S. Pat. No. 6,250,330 discloses a diaphragm regulator with removable diffuser. The removable flow diffuser in U.S. Pat. No. 6,289,934 was used in an elbow to reduce downstream turbulence. The adjustable flow diffuser in U.S. Pat. No. 6,439,267 was also used in elbows and piping systems.
- Robert H. Welker has developed other solutions to turbulent flow including U.S. Pat. Nos. 5,307,830; 5,454,640 and 5,730,416. These three patents disclose a set of tubes instead of the flow diffuser discussed above.
- A three-way valve with a flow diffuser reduces downstream turbulence and produces a flat velocity profile in the flowing fluid, which is an advantage to ultrasonic measurement. In larger versions of the three-way valve, it can be used to direct the thrust from a jet engine in a VTOL airplane. Larger versions of the three-way valve can also be used in ships with side thrusters.
-
FIG. 1 is a section view of the three-way valve with flow diffuser in the open position to the run valve outlet. -
FIG. 2 is an exploded section view of the movable valve element ofFIG. 1 . -
FIG. 3 is a front view of the movable valve element ofFIG. 2 along the line 3-3. -
FIG. 4 is a section view of a web ofFIG. 3 along the line 4-4. -
FIG. 5 is a section view of the three-way valve with flow diffuser ofFIG. 1 in the open position to the bypass outlet. -
FIG. 6 is a section view of the three-way valve with flow diffuser ofFIG. 1 open to both the run outlet and the bypass outlet. -
FIG. 7 is a section view of a VTOL jet airplane with the three-way valve with flow diffuser therein. -
FIG. 8 is a top plan view of the VTOL jet airplane ofFIG. 7 . -
FIG. 9 is a plan view of a ship with two three-way valves with flow diffusers therein. -
FIG. 10 is a section view of the ship ofFIG. 9 . -
FIG. 11 is a plan view of the ship ofFIG. 9 reversing thrust towards the bow. -
FIG. 12 is a plan view of the ship ofFIG. 9 using the mid-ships thrusters to maneuver. -
FIG. 13 is a plan view of the flow diffuser. -
FIG. 14 is an enlarged section view of the primary valve seat and the bypass valve seat in the flow diffuser along the line 14-14 ofFIG. 13 . -
FIG. 15 is a plan view of the flow diffuser in the receptacle formed by the body of the three-way valve. A plurality of flow arrows indicates a generally flat velocity profile of fluid passing through the flow diffuser. - Referring now to
FIGS. 1 , 5 and 6, the three-way valve with flow diffuser is generally identified by thenumeral 14. Like all three-way valves, the fluid flow may be directed to three different settings as shown byFIGS. 1 , 5 and 6. Thebody 22 includes a primary frame 24 and aremovable cap 26 which is connected to the primary frame by a plurality of bolts, only one of which 28 is shown in the drawings. The primary frame and the cap form areceptacle 30 sized and arranged to receive theremovable flow diffuser 32. When the bolts are removed, the cap disengages from the primary frame allowing maintenance or removal of theflow diffuser 32. A channel andseal 33 are positioned in thecap 26 to engage the primary frame 24 and seal thereceptacle 30. Analignment pin 34 is seated in anaperture 36 of the primary frame and anaperture 38 in the flow diffuser. The three-way valve with flow diffuser 20 defines arun inlet 40, arun outlet 42, abypass inlet 44 and abypass outlet 46. Theflow diffuser 32 has aflow diffuser inlet 48, better seen inFIG. 12 and aflow diffuser outlet 50. In the case of VTOL aircraft, thebypass inlet 44 may also be referred to as a vertical takeoff inlet and thebypass outlet 46 may also be referred to as a vertical takeoff outlet. - As previously mentioned, the three-way valve with
flow diffuser 14 has three operational positions show inFIGS. 1 , 5 and 6. InFIG. 2 , fluid flows from therun inlet 40 to therun outlet 42 as shown by the flow arrows.FIG. 1 may sometimes be referred to as the full open or full run position with thebypass valve 18 in the full closed position. InFIG. 5 , fluid flows from therun inlet 40, through thebypass inlet 44 to theflow diffuser inlet 48, theflow diffuser outlet 50 to thebypass outlet 46, as shown by the flow arrows.FIG. 2 may sometimes be referred to as the bypass valve in the full open position and therun valve 16 in the full closed position. InFIG. 6 , all of the fluid enters the run inlet, and a portion exits therun outlet 42 and the other portion flow through theflow diffuser 32 and exits thebypass outlet 46.FIG. 3 may sometimes be described as the split flow position. - A
movable valve element 52 includes aprimary valve element 54 and abypass valve element 56. Aprimary valve seat 58 is formed opposite to abypass valve seat 60 on a protruding portion of the flow diffuser, better seen inFIG. 13 . InFIG. 1 thebypass valve element 56 is in sealing engagement with thebypass valve seat 60 sealing against fluid flow into theflow diffuser 32 and thebypass outlet 46. InFIG. 2 , theprimary valve element 54 is in sealing engagement with theprimary valve seat 58 sealing against fluid flow to therun outlet 42. InFIG. 3 , there is no seal on either theprimary valve seat 58 or thebypass valve seat 60, thus allowing fluid to flow to both therun valve outlet 42 and thebypass outlet 46. A channel and seal 62 are formed in theremovable cap 26 to seal against thebypass valve element 56. Theseals - A
support 64 is connected to thetail cone 66. The support extends from the primary frame 24 to the tail cone and may be a plurality of vanes or a single column to hold the tail cone in place. Thesupport 64 holds thetail cone 66 in position in the three-way valve. Thetail cone 66 supports theprimary valve element 54 and a channel 68 supports thebypass valve element 56. Together, themovable valve element 52 is supported by the channel 68 on the end proximate therun inlet 40 and by thesupport 64 on the end proximate therun outlet 42. The movable valve element slides back and forth in the channel 68 and over thetail cone 66 which act as supports. These supports allow themovable valve element 54 to move back and forth to the different positions shown inFIGS. 1 , 5 and 6. - The
movable valve element 54 may be actuated by any suitable means 78, such as a mechanical screw, not shown or by hydraulic means shown inFIGS. 1 , 5 and 6. The hydraulic actuation means includes a pressurized source of hydraulic fluid, not shown, and a control means, not shown, to apply and drain pressurized hydraulic fluid through theconduit 80. Theprimary valve element 54 forms acylinder 82 that slides over thetail cone 66 forming achamber 84 to receive hydraulic fluid from the pressurized source, not shown. Pressurized fluid flows through theconduit 80 to thechamber 84. Thetail cone 66 is held in a stationary position by thesupport 64. As the pressure builds in thechamber 84, it drives the movable valve element towards therun inlet 40 and into sealing engagement with theprimary valve seal 58, as best seen inFIG. 5 in which the bypass valve is in the full open position. When the hydraulic pressure in thechamber 84 is reduced, the movable valve element moves to the position ofFIG. 6 , the split flow position, with fluid exiting both therun outlet 42 and thebypass outlet 46. When there is no hydraulic pressure in thechamber 84, pressure from the fluid flowing through the three-way valve 14 forces the movable valve element back into the position ofFIG. 1 . wherein the bypass valve is fully closed and the run valve is fully open. The hydraulic means shown is single acting. However, in some cases it may be designed as double acting if it is desirable to control the speed of closing thebypass valve 56. Therun valve 16 includes thebody 22, themovable valve element 52, and the means for actuating 78. The bypass valve includes theflow diffuser 32, themovable valve element 52, thebody 22 and the means for actuating 78. The three-way valve 14 includes therun valve 16 and thebypass valve 18. - Referring now to
FIGS. 2 , 3 and 4, themovable valve element 52, will be shown in greater detail. The movable valve element includes theprimary valve element 54 and thebypass valve element 56, which are dissembled and shown in section view inFIG. 2 . Apointed bolt 70 is a means for connecting the bypass valve element to the primary valve element. The bypass valve element forms a cylindrical closure 72, as best seen inFIG. 3 , with a plurality ofwebs 74 extending from the cylindrical closure to acenter 76 which is sized and arranged to receive thebolt 70. A threadedreceptacle 71 is formed in the primary valve element to receive thebolt 70. Thewebs 74 are aerodynamic in cross section as shown inFIG. 4 . Themovable valve element 52 is shown in these figures being formed from several different parts; however, the actual construction is a matter of manufacturing convenience. For example, movable valve element formed from one part may also be suitable for this invention. - Referring now to
FIGS. 7 and 8 , athrust controller 98 is positioned in ajet aircraft 100. The jet aircraft is designed for vertical takeoff and landing (“VTOL”). The jet aircraft has ajet engine 102, schematically portrayed in these drawings, with anair intake 104 and anexhaust 106 connected to thethrust controller 98 which is connected to both thetail pipe 108 andvertical takeoff outlet 110. Anadjustable door 112 covers thevertical takeoff outlet 110 and normally is in the closed position as shown inFIG. 7 during flight. However, the door is opened to various angles during vertical takeoff and landing maneuvers. If thedoor 112 is only partially opened, it helps theaircraft 100 to slow down in preparation for landing. Thedoor 112 will be fully opened during the vertical phase of takeoff and landing. - The
thrust controller 98 is the same as the three-way valve 14, except that theseals thrust controller 98 have the same names and identification numerals of the three-way valve 14. Thebypass outlet 46 is in fluid communication with thevertical takeoff outlet 110 to allow VTOL. - To commence vertical takeoff, the
thrust controller 98 is actuated into the position ofFIG. 5 and theadjustable door 112 will be fully opened, prior to starting thejet engine 102. The hot exhaust from the jet engine will pass through thebypass outlet 46 and into thevertical takeoff outlet 110 of theaircraft 100. This thrust will be directed towards the ground, allowing the aircraft to lift off. Once in a hover position, the thrust controller will be shifted to the position ofFIG. 6 , allowing some of the hot gases to exit thetailpipe 108 of the aircraft. As the aircraft commences forward movement, thethrust controller 98 will be adjusted to the position ofFIG. 1 with all the hot gases from the jet engine exiting thetailpipe 108. Before the jet picks up much speed, theadjustable door 112 is fully closed. - Referring now to
FIGS. 9 and 10 , aship 130 is shown in plan view and in section view. The ship may sometimes be generically referred to as a watercraft. Thewatercraft 130 has abow 132, astem 134, aport side 136 and astarboard side 138. The watercraft has aport power plant 140 to drive aport propulsion unit 142 which is in fluid communication with aport thrust controller 144. The watercraft has astarboard power plant 146 to drive astarboard propulsion unit 148 which is in fluid communication with astarboard thrust controller 150. Theport water intake 152 is located at the bottom 154 of the watercraft. The starboard water intake, not shown, is likewise located at the bottom of the watercraft. Theport turbine outlet 156 is in fluid communication with therun inlet 40 of the port thrustcontroller 144 and therun outlet 42 is in fluid communication with the port thrustconduit 158. The port thrustconduit outlet 160 is located at the stem of the watercraft. Thestarboard turbine outlet 162 is in fluid communication with therun inlet 40A of thestarboard thrust controller 150 and therun outlet 42A is in fluid communication with thestarboard thrust conduit 164. The starboard thrustconduit outlet 166 is located at the stern of the watercraft. - A
port rudder 168 is supported by an upper port rudder stanchion and a lower port rudder stanchion. Astarboard rudder 174 is supported by an upper starboard rudder stanchion, not shown, and a lower starboard rudder stanchion, not shown. A rudder control means, not shown, independently controls the direction of each rudder. Fluid flows from the port water intake, through the port propulsion unit 143, the port thrustcontroller 144, the port thrustconduit 158 and exits the port thrustconduit outlet 160 at theport rudder 168. Likewise fluid flows through the starboard water intake, not shown, through thestarboard propulsion unit 148, thestarboard thrust controller 150, thestarboard thrust conduit 164 and exits the starboard thrustconduit outlet 166 atstarboard rudder 174. - An adjustable
port turning plane 182 is positioned proximate the port amidshipsoutlet 184 and an adjustablestarboard turning plane 186 is positioned proximate the starboard amidships outlet. Thebypass outlet 46 of the port thrustcontroller 144 is in fluid communication with the port amidshipsoutlet 184; thebypass outlet 46A of thestarboard thrust controller 150 is in fluid communication with the starboard amidshipsoutlet 188. These amidships outlets may be used to reverse direction or slow down forward progress of the watercraft as shown inFIG. 11 or they may be used to help maneuver the watercraft as shown inFIG. 12 . -
FIG. 11 is a plan view of thewatercraft 130 ofFIG. 9 , except the port thrustcontroller 144 and thestarboard thrust controller 150 have been actuated so fluid passes through thebypass outlet conduit outlet 160 or the starboard thrustconduit outlet 166 at thestem 134. In addition, the adjustableport turning plane 182 and the adjustablestarboard turning plane 186 have been opened to redirect the fluid flow towards thebow 132 of thewatercraft 130. Fluid flow as shown inFIG. 11 will slow forward progress of the watercraft, if it has been making way, and will ultimately bring the watercraft to a stop. If the watercraft is not making way, the fluid flow inFIG. 11 will cause the watercraft to move in a reverse direction. -
FIG. 13 is a plan view of thewatercraft 130 ofFIG. 9 , except the port thrust controller has been actuated so fluid exits through thebypass outlet 46 as shown by the flow arrow. Further, the starboard rudder has been turned to direct fluid flow from the starboard thrustconduit outlet 166 in the starboard direction. The net effect of the fluid flow pattern shown inFIG. 12 is to turn the watercraft in the starboard direction as indicated by the arrow at thebow 132. -
FIG. 13 is a plan view of theremovable flow diffuser 32 along the line 13-13 ofFIG. 1 . The cylindrical closure 72 and the pointedbolt 70 have been omitted fromFIG. 13 to better show theflow diffuser 32. Thealignment pin 34 is shown in phantom and is responsible for properly aligning the vanes in the three-way valve 14. Similar flow diffusers are shown in U.S. Pat. Nos. 5,469,388; 6,250,330; 6,289,934 and 6,439,267 which are incorporated herein by reference. -
FIG. 14 is an enlargement of theprimary valve seat 58 and thebypass valve seat 60 which are a part of theremovable flow diffuser 32. The opposingvalve seats - In
FIG. 13 , a frontcentral vane 200 points towards thebypass outlet 46 as better seen inFIG. 1 . A rearcentral vane 202 receives thealignment pin 34 shown in phantom. Disposed between the frontcentral vane 200 and the rearcentral vane 202 is a firstright vane 204, a secondright vane 206, a thirdright vane 208, a fourthright vane 210, a fifthright vane 212, a sixthright vane 214 and a seventhright vane 216. Between the frontcentral vane 200 and the firstright vane 204 is a firstright flow passageway 220. Between the firstright vane 204 and the secondright vane 206 is a secondright flow passageway 222. Between the secondright vane 206 and the thirdright vane 208 is a thirdright flow passageway 224. Between the thirdright vane 208 and the fourthright vane 210 is a fourthright flow passageway 226. Between the fourthright vane 210 and the fifthright vane 212 is a fifthright flow passageway 228. Between the fifthright vane 212 and the sixthright vane 214 is a sixthright flow passageway 230. Between the sixthright vane 214 and the seventhright vane 216 is the seventhright flow passageway 232. Between the seventhright vane 216 and the rearcentral vane 202 is aneighth flow passageway 234. - Between the front
central vane 200 and the firstleft vane 240 is a firstleft flow passageway 260. Between the firstleft vane 240 and the secondleft vane 242 is a secondleft flow passageway 262. Between the secondleft vane 242 and the thirdleft vane 244 is a thirdleft flow passageway 264. Between the thirdleft vane 244 and the fourthleft vane 246 is a fourthleft flow passageway 266. Between the fourthleft vane 246 and the fifthleft vane 248 is a fifthleft flow passageway 268. Between the fifth left vane 249 and the sixthleft vane 250 is a sixthleft flow passageway 270. Between the sixthleft vane 250 and the seventhleft vane 252 is a seventhleft flow passageway 272. Between the seventhleft vane 252 and the rearcentral vane 202 is the eighthleft flow passageway 274. - Referring now to
FIGS. 5 , 13 and 15, fluid enters the three-way valve 14 as shown by the flow arrow A, through therun inlet 40. The fluid then passes through thebypass valve element 56 as indicated by the flow arrows E and F. The fluid then flows into thebypass inlet 44, the circularflow diffuser inlet 48 and into the right flow passageways 220, 222, 224, 226, 228, 230, 232 and 234 and the left flow passageways, 260, 262, 264, 266, 268, 270, 272 and 274. The flow path of the fluid into the flow diffuser is best seen inFIG. 15 and is represented by the starburst of flow arrows at the center of the figure. - The shortest pathway from the
flow diffuser inlet 48 to theflow diffuser outlet 50 is through the firstright flow passageway 220 and the firstleft flow passageway 260. The flow arrow F shows fluid passing from theflow diffuser inlet 48 into the firstright flow passageway 220. The flow arrow G shows fluid leaving the first right flow passageway and passing through theflow diffuser outlet 50. The longest distance that fluid must travel from theflow diffuser inlet 48 to theflow diffuser outlet 50 is through the eighthright flow passageway 234 and the eighthleft flow passageway 274. The flow arrow E shows fluid leaving theflow diffuser inlet 48 and passing into the eighthright flow passageway 234. The flow arrow I shows fluid leaving the eighthright flow passageway 234 and theflow diffuser outlet 50. - The prior art flow diffuser of U.S. Pat. No. 6,439,267 created a non-uniform velocity flow profile as shown pictorially in
FIG. 15 of that patent. One purpose of theflow diffuser 32 of the present invention is to produce a generally flat velocity profile indicated by the dashedline 294, as better seen inFIG. 15 of the present patent application. A generallyflat velocity profile 294 is helpful to ultrasonic flow meters. The non-uniform velocity profile in the prior art sometimes distorts the accuracy of ultrasonic flow meters. - The generally
flat velocity profile 294 of the present application is created by strategically positioning choke points and flow restrictions in the left and right flow passageways to slow down some fluid molecules and to accelerate others. The fluid molecules, represented by flow arrows F and G, moving through the shortest passageways, i.e. 220 and 260 must be slowed down and the fluid molecules, represented by flow arrows E and I, moving through the longest passageways, i.e. 234 and 274 must be accelerated. - Referring now to
FIGS. 5 , 13 and 15, the flow paths through the flow diffuser will be discussed in greater detail and the control of the velocities through various flow passageways will be explained. The choke point indicated by the dashedcircle 280, better seen inFIG. 13 , encloses aprotrusion 282 on firstright vane 204. Theprotrusion 282 creates a choke point at the dashedcircle 280 in the secondright flow passageway 222 which slows the speed of fluid as it passes through thechoke point 280. Asimilar protrusion 284 is formed on firstleft vane 240 which slows the speed of fluid as it passes through the secondleft flow passageway 262. Aright protrusion 286 is formed on the right side of frontcentral vane 200 and aleft protrusion 288 is formed on the left side of the frontcentral vane 200 creating choke points in the firstright passageway 220 and the firstleft flow passageway 260. The closer the protrusions are to the circularflow diffuser inlet 48, the more the fluid flow is slowed down as a result of the Venturi exit after the choke point. In contrast, theright flow constriction 290 in the eighthright flow passageway 234 and theleft flow constriction 292 in the eighthleft flow passageway 274 are as far away from the circularflow diffuser inlet 48 as possible to speed up the fluid flow in the two longest passageways. The fluid molecules traveling through the flow passageways, 220 and 260 have the shortest distance to travel from the circularflow diffuser inlet 48, better seen inFIG. 5 , to theflow diffuser outlet 50, as better seen inFIGS. 5 and 15 ; thus the velocity of these molecules needs to be slowed down by thechoke points right flow passageway 234 and the eighthleft flow passageway 274.Choke points flow passageways flow passageways flow diffuser inlet 48 to theflow diffuser outlet 250. Aprotrusion 296 is formed onvane 206, creating a choke point inright flow passageway 226 to slow the velocity of the fluid molecules; aprotrusion 298 is formed onvane 242 creating a choke point inleft flow passageway 264 to slow the velocity of the fluid molecules. Anadditional protrusion 298 is formed onvane 242 andprotrusion 300 is formed onvane 242, again creating choke points to slow the velocity of the fluid molecules passing through the aforementioned passageways. - In the longer flow passageways, flow restrictions are placed as far away from the flow diffuser inlet 49 as possible to speed up the flow of fluid molecules so they can catch up with those traveling through the shorter passageways. A
flow restriction 304 is placed in theright flow passageway 234 and aflow restriction 306 is placed in theleft flow passageway 272. Likewise, aflow restriction 308 is placed inright flow passageway 230 and aflow restriction 310 is placed inleft flow passageway 270. Aflow restriction 312 is placed inright flow passageway 228 and aflow restriction 314 is placed inleft flow passageway 268 to speed up the fluid molecules so theoverall velocity profile 294 is substantially flat. - The cross sectional profile of the
bypass outlet 46 is similar to the cross sectional profile shown in FIGS. 6-9 of U.S. Pat. No. 6,289,934, which is incorporated herein by reference. The cross sectional area of therun inlet 40 shall be approximately equal to the cross sectional area of therun outlet 42. The cross sectional area of therun inlet 40 shall be approximately equal to the cross sectional area of thebypass outlet 46.
Claims (3)
1. A watercraft comprising:
a port propulsion unit and a port thrust controller axially aligned along a port side of the watercraft, the port propulsion unit having a fluid inlet and outlet;
the port thrust controller having an inlet and an outlet, the inlet in fluid communication with the outlet of the port propulsion unit and the outlet of the port thrust controller positioned proximate a port rudder on a stem of the watercraft;
the port thrust controller having a bypass thruster with an amidships outlet aligned generally normal to the port side of the watercraft;
a starboard propulsion unit and a starboard thrust controller axially aligned along a starboard side of the watercraft, the starboard propulsion unit having a fluid inlet and outlet;
the starboard thrust controller having an inlet and an outlet, the inlet in fluid communication with the outlet of the starboard propulsion unit and the outlet of the starboard thrust controller positioned proximate a rudder on a starboard rudder on a stem of the watercraft; and
the starboard thrust controller having a bypass thruster with an amidships outlet aligned generally normal to the starboard of the watercraft.
2. The watercraft of claim 1 further including:
a port turning plane connected to an outside port hull of the watercraft proximate the amidships outlet of the port bypass thruster to direct fluid from the port bypass thruster and
a starboard turning plane connected to an outside hull of the watercraft proximate the amidships outlet of the starboard bypass thruster to direct fluid flow from the starboard bypass thruster.
3. The watercraft of claim 1 wherein the port thrust controller comprises:
a body defining an flow passageway in fluid communication with the fluid inlet and the outlet, the fluid inlet also in fluid communication with the bypass thruster inlet and the amidships outlet;
a removable flow diffuser in a receptacle in the body, the flow diffuser having a flow diffuser inlet in fluid communication with the bypass inlet and a flow diffuser outlet in fluid communication with the bypass outlet;
a movable valve element sized and arranged to alternatively engage and seal against a primary valve seat and a bypass valve seat;
a support extending from the body to position the movable valve element in the flow passageway;
the removable flow diffuser aligned generally transverse to the flow passageway; and
means to move the movable valve element from an open position to direct all the thrust to the outlet, to a closed position to direct all the thrust to the bypass outlet and various intermediate positions to direct some of the thrust to the outlet and some to the bypass outlet.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/365,152 US20090137165A1 (en) | 2005-07-20 | 2009-02-03 | Newtonian thrust cowl array |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/161,033 US7493914B2 (en) | 2005-07-20 | 2005-07-20 | Newtonian thrust cowl array |
US12/365,152 US20090137165A1 (en) | 2005-07-20 | 2009-02-03 | Newtonian thrust cowl array |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/161,033 Division US7493914B2 (en) | 2005-07-20 | 2005-07-20 | Newtonian thrust cowl array |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090137165A1 true US20090137165A1 (en) | 2009-05-28 |
Family
ID=37677800
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/161,033 Active 2027-05-21 US7493914B2 (en) | 2005-07-20 | 2005-07-20 | Newtonian thrust cowl array |
US12/365,152 Abandoned US20090137165A1 (en) | 2005-07-20 | 2009-02-03 | Newtonian thrust cowl array |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/161,033 Active 2027-05-21 US7493914B2 (en) | 2005-07-20 | 2005-07-20 | Newtonian thrust cowl array |
Country Status (1)
Country | Link |
---|---|
US (2) | US7493914B2 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2492103C1 (en) * | 2012-02-14 | 2013-09-10 | Виктор Семенович Савченков | Marine hydromechanical propulsor |
CN104648645A (en) * | 2015-03-04 | 2015-05-27 | 武汉理工大学 | Jet-propelled boat capable of realizing boat motion vector control |
CN109178263A (en) * | 2018-11-05 | 2019-01-11 | 江西理工大学 | A kind of impulse jet type underwater robot based on tubulose origami structure |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8281810B2 (en) * | 2008-04-30 | 2012-10-09 | The Viking Corporation | Dry valve for sprinkler system |
US9423034B2 (en) * | 2013-07-22 | 2016-08-23 | Luke S. Colby | Locking poppet valve |
KR102014726B1 (en) * | 2019-01-15 | 2019-08-27 | 김형오 | Thrust vectoring apparatus for jet VTOL aircraft |
Citations (65)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US313981A (en) * | 1885-03-17 | Chables edwin buech | ||
US917201A (en) * | 1906-05-21 | 1909-04-06 | David F Vollmer | Hydrostatic propelling and steering apparatus. |
US1547962A (en) * | 1922-03-17 | 1925-07-28 | English Electric Co Ltd | Valve for hydraulic purposes |
US1676150A (en) * | 1926-10-25 | 1928-07-03 | Mawby John Henry | Pneumatically-driven ship |
US2483163A (en) * | 1945-05-07 | 1949-09-27 | Gen Electric | Shutoff valve |
US2618925A (en) * | 1947-01-31 | 1952-11-25 | Packard Motor Car Co | Flow control means for pulse jet combustion units |
US2774554A (en) * | 1952-05-30 | 1956-12-18 | Power Jets Res & Dev Ltd | Jet flow control for jet-sustained and jet-propelled aircraft |
US2868176A (en) * | 1954-07-14 | 1959-01-13 | Robert H Bennett | Rotary plug valve |
US2947501A (en) * | 1952-10-21 | 1960-08-02 | Power Jets Res & Dev Ltd | Jet deflectors for aircraft |
US2974680A (en) * | 1959-02-05 | 1961-03-14 | Buensod Stacey Corp | Valve |
US3137266A (en) * | 1960-11-29 | 1964-06-16 | Perrier Robert | Jet propulsion apparatus for watercrafts |
US3348380A (en) * | 1965-01-11 | 1967-10-24 | Rolls Royce | Power plant for vtol or stol aircraft having means to augment jet thrust when the same is directed vertically |
US3354648A (en) * | 1966-03-24 | 1967-11-28 | Asahina Jiro | Water-jet engine |
US3381713A (en) * | 1965-10-14 | 1968-05-07 | Gordon R. Jacobsen | Turning vane and rail construction |
US3451404A (en) * | 1966-12-05 | 1969-06-24 | Richard E Self | High energy loss fluid control |
US3474966A (en) * | 1968-03-01 | 1969-10-28 | Us Army | Mechanical wall attachment diverter valve |
US3492965A (en) * | 1961-06-12 | 1970-02-03 | David J Wayfield | Propulsion system and related devices |
US3618861A (en) * | 1970-01-14 | 1971-11-09 | Us Army | Diverter valve flow throttle |
US3675611A (en) * | 1970-02-27 | 1972-07-11 | John P Glass | Jet steering boat |
US3680315A (en) * | 1970-10-12 | 1972-08-01 | Twin Disc Inc | Hydraulic jet propulsion apparatus |
US3700189A (en) * | 1970-07-02 | 1972-10-24 | Gen Electric | Vtol propulsion system |
US3756266A (en) * | 1972-02-08 | 1973-09-04 | Sun Olin Chemical Co | Removal of liquid from pipe carrying gas |
US4023355A (en) * | 1972-02-24 | 1977-05-17 | Thiokol Corporation | Combination diffuser, thermal barrier, and interchamber valve for rockets |
US4056073A (en) * | 1974-07-25 | 1977-11-01 | Omnithruster Inc. | Boat thruster |
US4138963A (en) * | 1977-10-26 | 1979-02-13 | Thompson William C | Boat steering mechanism |
US4155372A (en) * | 1977-09-12 | 1979-05-22 | Northern Natural Gas Company | Portable siphon apparatus for removing concentrations of liquid from a gas pipeline |
US4177676A (en) * | 1978-05-25 | 1979-12-11 | Welker Robert H | Sensor positioning apparatus |
US4193422A (en) * | 1978-11-24 | 1980-03-18 | The United States Of America As Represented By The United States Department Of Energy | Annular flow diverter valve |
US4241876A (en) * | 1979-03-22 | 1980-12-30 | General Motors Corporation | Variable area exhaust nozzle |
US4245613A (en) * | 1978-11-01 | 1981-01-20 | Black Body Corporation | Tunnel oven |
US4265192A (en) * | 1979-02-05 | 1981-05-05 | Dunn Garf L | Auxiliary hydraulic maneuvering system for small boats |
US4282894A (en) * | 1977-09-12 | 1981-08-11 | Northern Natural Gas Company | Pressure-operated portable siphon apparatus for removing concentrations of liquid from a gas pipeline |
US4346611A (en) * | 1980-12-19 | 1982-08-31 | Welker Robert H | Insertion regulator for pressurized pipelines |
US4387592A (en) * | 1981-07-01 | 1983-06-14 | Welker Engineering Company | Probe insertion apparatus |
US4455960A (en) * | 1981-11-10 | 1984-06-26 | Omnithruster, Inc. | Fluid valve actuated boat thruster |
US4559275A (en) * | 1982-06-23 | 1985-12-17 | Bbc Brown, Boveri & Company, Limited | Perforated plate for evening out the velocity distribution |
US4631967A (en) * | 1985-05-17 | 1986-12-30 | Welker Engineering Company | Automatic insertion device |
US4807552A (en) * | 1986-11-21 | 1989-02-28 | Fowler Larrie M | Small boat bow thruster |
US4881567A (en) * | 1987-12-02 | 1989-11-21 | Brooklyn Union Gas | Liquid removal system |
US5024254A (en) * | 1989-04-27 | 1991-06-18 | Hi-Sonic Co., Ltd. | Liquid shut-off valve |
US5062588A (en) * | 1989-02-08 | 1991-11-05 | Boeing Of Canada Ltd. | Segmented rotatable nozzles |
US5098022A (en) * | 1991-01-07 | 1992-03-24 | United Technologies Corporation | Flow diverting nozzle for a gas turbine engine |
US5110047A (en) * | 1989-08-21 | 1992-05-05 | Moog Inc. | Vane-type nozzle(s) for varying the magnitude and direction of a thrust vector, and methods of operating same |
US5129846A (en) * | 1991-01-07 | 1992-07-14 | Berge A. Dimijian | Vessel propulsion and turning control system |
US5307830A (en) * | 1993-05-18 | 1994-05-03 | Welker Engineering Company | Flow distribution method and apparatus reducing downstream turbulence |
US5454640A (en) * | 1994-01-28 | 1995-10-03 | Welker; Robert H. | Flow diffuser for redistributing stratified liquids in a pipeline |
US5469388A (en) * | 1992-11-23 | 1995-11-21 | Samsung Electronics Co., Ltd. | Row redundancy circuit suitable for high density semiconductor memory devices |
US5481868A (en) * | 1993-04-30 | 1996-01-09 | Gec-Marconi Limited | Variable area nozzle with fixed convergent-divergent walls and relatively movable parallel sideplates |
US5531484A (en) * | 1994-02-10 | 1996-07-02 | Kawano; Michihiko | Elbow provided with guide vanes |
US5642684A (en) * | 1996-06-17 | 1997-07-01 | Omnithruster Inc. | Thrust director unit for a marine vessel |
US5699966A (en) * | 1980-03-31 | 1997-12-23 | General Electric Company | Exhaust nozzle of a gas turbine engine |
US5730416A (en) * | 1995-06-07 | 1998-03-24 | Welker Engineering Company | Method and apparatus for quieting turbulence in a gas flow line valve |
US5756906A (en) * | 1997-03-11 | 1998-05-26 | Welker Engineering Company | Stabilized insertion device |
US5769388A (en) * | 1997-04-28 | 1998-06-23 | Welker Engineering Company | Flow diffuser and valve |
US5936168A (en) * | 1993-10-15 | 1999-08-10 | Welker; Robert H. | Dual injector cylinder automatic insertion device for use with high pressure pipelines |
US6085777A (en) * | 1998-02-19 | 2000-07-11 | Welker Engineering Company | Dual cylinder insertion apparatus |
US6142841A (en) * | 1998-05-14 | 2000-11-07 | Brunswick Corporation | Waterjet docking control system for a marine vessel |
US6250330B1 (en) * | 1999-11-08 | 2001-06-26 | Welker Engineering Company | Diaphragm regulator with removable diffuser |
US6289934B1 (en) * | 1999-07-23 | 2001-09-18 | Welker Engineering Company | Flow diffuser |
US6338359B1 (en) * | 1998-02-19 | 2002-01-15 | Welker Engineering Company | Dual automatic insertion device |
US6439267B2 (en) * | 1999-07-23 | 2002-08-27 | Welker Engineering Company | Adjustable flow diffuser |
US6554660B2 (en) * | 2000-09-28 | 2003-04-29 | John T. Irish | Propulsion system for yachts, trawlers and the like |
US6568635B2 (en) * | 2001-07-02 | 2003-05-27 | Lockheed Martin Corporation | Apparatus and method for flight control of an aircraft |
US6827486B2 (en) * | 2002-11-22 | 2004-12-07 | Welker Engineering Company | Temperature probe and insertion device |
US7000634B2 (en) * | 2000-10-26 | 2006-02-21 | Lindinvent Ab | Adjustable valve for variable flows and a method for reducing flow through a valve |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3137268A (en) * | 1962-05-23 | 1964-06-16 | Clive H Bramson | Warning device |
US3618881A (en) * | 1969-07-31 | 1971-11-09 | Northrop Corp | Cockpit enclosure |
US4058073A (en) * | 1974-09-10 | 1977-11-15 | Janome Sewing Machine Co. Ltd. | Case for portable sewing machines |
JPS59140973A (en) | 1983-01-31 | 1984-08-13 | Yamatake Honeywell Co Ltd | Valve seat for control valve and manufacturing method thereof |
JPS62258722A (en) | 1986-04-10 | 1987-11-11 | Nitta Kk | Air purifier |
FR2708103B1 (en) | 1993-06-30 | 1995-09-01 | Snecma | Air intake duct at the entrance to a test bench for turbomachinery. |
JP2003194018A (en) | 2001-12-26 | 2003-07-09 | Mitsubishi Heavy Ind Ltd | Elbow with built-in straightening guide vane and cavitation tunnel |
-
2005
- 2005-07-20 US US11/161,033 patent/US7493914B2/en active Active
-
2009
- 2009-02-03 US US12/365,152 patent/US20090137165A1/en not_active Abandoned
Patent Citations (66)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US313981A (en) * | 1885-03-17 | Chables edwin buech | ||
US917201A (en) * | 1906-05-21 | 1909-04-06 | David F Vollmer | Hydrostatic propelling and steering apparatus. |
US1547962A (en) * | 1922-03-17 | 1925-07-28 | English Electric Co Ltd | Valve for hydraulic purposes |
US1676150A (en) * | 1926-10-25 | 1928-07-03 | Mawby John Henry | Pneumatically-driven ship |
US2483163A (en) * | 1945-05-07 | 1949-09-27 | Gen Electric | Shutoff valve |
US2618925A (en) * | 1947-01-31 | 1952-11-25 | Packard Motor Car Co | Flow control means for pulse jet combustion units |
US2774554A (en) * | 1952-05-30 | 1956-12-18 | Power Jets Res & Dev Ltd | Jet flow control for jet-sustained and jet-propelled aircraft |
US2947501A (en) * | 1952-10-21 | 1960-08-02 | Power Jets Res & Dev Ltd | Jet deflectors for aircraft |
US2868176A (en) * | 1954-07-14 | 1959-01-13 | Robert H Bennett | Rotary plug valve |
US2974680A (en) * | 1959-02-05 | 1961-03-14 | Buensod Stacey Corp | Valve |
US3137266A (en) * | 1960-11-29 | 1964-06-16 | Perrier Robert | Jet propulsion apparatus for watercrafts |
US3492965A (en) * | 1961-06-12 | 1970-02-03 | David J Wayfield | Propulsion system and related devices |
US3348380A (en) * | 1965-01-11 | 1967-10-24 | Rolls Royce | Power plant for vtol or stol aircraft having means to augment jet thrust when the same is directed vertically |
US3381713A (en) * | 1965-10-14 | 1968-05-07 | Gordon R. Jacobsen | Turning vane and rail construction |
US3354648A (en) * | 1966-03-24 | 1967-11-28 | Asahina Jiro | Water-jet engine |
US3451404A (en) * | 1966-12-05 | 1969-06-24 | Richard E Self | High energy loss fluid control |
US3474966A (en) * | 1968-03-01 | 1969-10-28 | Us Army | Mechanical wall attachment diverter valve |
US3618861A (en) * | 1970-01-14 | 1971-11-09 | Us Army | Diverter valve flow throttle |
US3675611A (en) * | 1970-02-27 | 1972-07-11 | John P Glass | Jet steering boat |
US3700189A (en) * | 1970-07-02 | 1972-10-24 | Gen Electric | Vtol propulsion system |
US3680315A (en) * | 1970-10-12 | 1972-08-01 | Twin Disc Inc | Hydraulic jet propulsion apparatus |
US3756266A (en) * | 1972-02-08 | 1973-09-04 | Sun Olin Chemical Co | Removal of liquid from pipe carrying gas |
US4023355A (en) * | 1972-02-24 | 1977-05-17 | Thiokol Corporation | Combination diffuser, thermal barrier, and interchamber valve for rockets |
US4056073A (en) * | 1974-07-25 | 1977-11-01 | Omnithruster Inc. | Boat thruster |
US4155372A (en) * | 1977-09-12 | 1979-05-22 | Northern Natural Gas Company | Portable siphon apparatus for removing concentrations of liquid from a gas pipeline |
US4282894A (en) * | 1977-09-12 | 1981-08-11 | Northern Natural Gas Company | Pressure-operated portable siphon apparatus for removing concentrations of liquid from a gas pipeline |
US4138963A (en) * | 1977-10-26 | 1979-02-13 | Thompson William C | Boat steering mechanism |
US4177676A (en) * | 1978-05-25 | 1979-12-11 | Welker Robert H | Sensor positioning apparatus |
US4245613A (en) * | 1978-11-01 | 1981-01-20 | Black Body Corporation | Tunnel oven |
US4193422A (en) * | 1978-11-24 | 1980-03-18 | The United States Of America As Represented By The United States Department Of Energy | Annular flow diverter valve |
US4265192A (en) * | 1979-02-05 | 1981-05-05 | Dunn Garf L | Auxiliary hydraulic maneuvering system for small boats |
US4241876A (en) * | 1979-03-22 | 1980-12-30 | General Motors Corporation | Variable area exhaust nozzle |
US5699966A (en) * | 1980-03-31 | 1997-12-23 | General Electric Company | Exhaust nozzle of a gas turbine engine |
US4346611A (en) * | 1980-12-19 | 1982-08-31 | Welker Robert H | Insertion regulator for pressurized pipelines |
US4387592A (en) * | 1981-07-01 | 1983-06-14 | Welker Engineering Company | Probe insertion apparatus |
US4455960A (en) * | 1981-11-10 | 1984-06-26 | Omnithruster, Inc. | Fluid valve actuated boat thruster |
US4559275A (en) * | 1982-06-23 | 1985-12-17 | Bbc Brown, Boveri & Company, Limited | Perforated plate for evening out the velocity distribution |
US4631967A (en) * | 1985-05-17 | 1986-12-30 | Welker Engineering Company | Automatic insertion device |
US4807552A (en) * | 1986-11-21 | 1989-02-28 | Fowler Larrie M | Small boat bow thruster |
US4881567A (en) * | 1987-12-02 | 1989-11-21 | Brooklyn Union Gas | Liquid removal system |
US5062588A (en) * | 1989-02-08 | 1991-11-05 | Boeing Of Canada Ltd. | Segmented rotatable nozzles |
US5024254A (en) * | 1989-04-27 | 1991-06-18 | Hi-Sonic Co., Ltd. | Liquid shut-off valve |
US5110047A (en) * | 1989-08-21 | 1992-05-05 | Moog Inc. | Vane-type nozzle(s) for varying the magnitude and direction of a thrust vector, and methods of operating same |
US5098022A (en) * | 1991-01-07 | 1992-03-24 | United Technologies Corporation | Flow diverting nozzle for a gas turbine engine |
US5129846A (en) * | 1991-01-07 | 1992-07-14 | Berge A. Dimijian | Vessel propulsion and turning control system |
US5469388A (en) * | 1992-11-23 | 1995-11-21 | Samsung Electronics Co., Ltd. | Row redundancy circuit suitable for high density semiconductor memory devices |
US5481868A (en) * | 1993-04-30 | 1996-01-09 | Gec-Marconi Limited | Variable area nozzle with fixed convergent-divergent walls and relatively movable parallel sideplates |
US5307830A (en) * | 1993-05-18 | 1994-05-03 | Welker Engineering Company | Flow distribution method and apparatus reducing downstream turbulence |
US5936168A (en) * | 1993-10-15 | 1999-08-10 | Welker; Robert H. | Dual injector cylinder automatic insertion device for use with high pressure pipelines |
US5454640A (en) * | 1994-01-28 | 1995-10-03 | Welker; Robert H. | Flow diffuser for redistributing stratified liquids in a pipeline |
US5531484A (en) * | 1994-02-10 | 1996-07-02 | Kawano; Michihiko | Elbow provided with guide vanes |
US5730416A (en) * | 1995-06-07 | 1998-03-24 | Welker Engineering Company | Method and apparatus for quieting turbulence in a gas flow line valve |
US5642684A (en) * | 1996-06-17 | 1997-07-01 | Omnithruster Inc. | Thrust director unit for a marine vessel |
US5756906A (en) * | 1997-03-11 | 1998-05-26 | Welker Engineering Company | Stabilized insertion device |
US5769388A (en) * | 1997-04-28 | 1998-06-23 | Welker Engineering Company | Flow diffuser and valve |
US6085777A (en) * | 1998-02-19 | 2000-07-11 | Welker Engineering Company | Dual cylinder insertion apparatus |
US6338359B1 (en) * | 1998-02-19 | 2002-01-15 | Welker Engineering Company | Dual automatic insertion device |
US6142841A (en) * | 1998-05-14 | 2000-11-07 | Brunswick Corporation | Waterjet docking control system for a marine vessel |
US6289934B1 (en) * | 1999-07-23 | 2001-09-18 | Welker Engineering Company | Flow diffuser |
US6439267B2 (en) * | 1999-07-23 | 2002-08-27 | Welker Engineering Company | Adjustable flow diffuser |
US6250330B1 (en) * | 1999-11-08 | 2001-06-26 | Welker Engineering Company | Diaphragm regulator with removable diffuser |
US6554660B2 (en) * | 2000-09-28 | 2003-04-29 | John T. Irish | Propulsion system for yachts, trawlers and the like |
US7000634B2 (en) * | 2000-10-26 | 2006-02-21 | Lindinvent Ab | Adjustable valve for variable flows and a method for reducing flow through a valve |
US6568635B2 (en) * | 2001-07-02 | 2003-05-27 | Lockheed Martin Corporation | Apparatus and method for flight control of an aircraft |
US6827486B2 (en) * | 2002-11-22 | 2004-12-07 | Welker Engineering Company | Temperature probe and insertion device |
US6964517B2 (en) * | 2002-11-22 | 2005-11-15 | Welker Engineering Company | Temperature probe and insertion device |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2492103C1 (en) * | 2012-02-14 | 2013-09-10 | Виктор Семенович Савченков | Marine hydromechanical propulsor |
CN104648645A (en) * | 2015-03-04 | 2015-05-27 | 武汉理工大学 | Jet-propelled boat capable of realizing boat motion vector control |
CN109178263A (en) * | 2018-11-05 | 2019-01-11 | 江西理工大学 | A kind of impulse jet type underwater robot based on tubulose origami structure |
Also Published As
Publication number | Publication date |
---|---|
US7493914B2 (en) | 2009-02-24 |
US20070017209A1 (en) | 2007-01-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20090137165A1 (en) | Newtonian thrust cowl array | |
US7143983B2 (en) | Passive jet spoiler for yaw control of an aircraft | |
US2681548A (en) | Reversible thrust nozzle for jet engines | |
US4037405A (en) | Two dimensional nozzle with rotating plug | |
US4298089A (en) | Vortex generators for internal mixing in a turbofan engine | |
US7984879B2 (en) | Flow control actuators | |
US3346216A (en) | Airship | |
US3939794A (en) | Marine pump-jet propulsion system | |
US7290738B1 (en) | Dual jet emerging lift augmentation system for airfoils and hydrofoils | |
US7124698B1 (en) | Auxiliary facilities for the maneuvering of submerged water jet propelled sea craft | |
GB1121703A (en) | Fluid propulsion system | |
US3610262A (en) | Stowable vane sonic throat inlet for jet aircraft noise suppression | |
US3362431A (en) | Apparatus for the rapid mixture of fluids, especially on a turbo-ram-jet unit | |
US2928627A (en) | Aircraft propulsion systems | |
CN111175021A (en) | Device and method for testing supercavitation water holes under action of head ventilation and tail jet flow | |
US3933113A (en) | Marine vessel propulsion system | |
RU2623762C1 (en) | Combined control actuator system (options) | |
US3106179A (en) | Propulsion system for a hydrofoil vessel | |
US4040577A (en) | Lockwood airfoil used in conjunction with man transport device | |
US3525577A (en) | Propellers | |
US2841956A (en) | Combination variable area converging-diverging nozzle and thrust destroyer | |
GB1240589A (en) | Motorboat with water jet propulsion | |
US3181818A (en) | Shock wave position controller | |
US3181817A (en) | Air inlet control | |
US20110239656A1 (en) | Water Augmentation System |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |