US3386246A - Composite gas-liquid pressurizing engine - Google Patents

Composite gas-liquid pressurizing engine Download PDF

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US3386246A
US3386246A US530161A US53016166A US3386246A US 3386246 A US3386246 A US 3386246A US 530161 A US530161 A US 530161A US 53016166 A US53016166 A US 53016166A US 3386246 A US3386246 A US 3386246A
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liquid
gas
water
pump
engine
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Sugimura Hiroshi
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Priority to US530161A priority Critical patent/US3386246A/en
Priority to SE2561/67A priority patent/SE324970B/xx
Priority to DE19671626106 priority patent/DE1626106A1/de
Priority to FR96453A priority patent/FR1512712A/fr
Priority to GB8878/67A priority patent/GB1161779A/en
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    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • 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
    • B63H11/04—Marine propulsion by water jets the propulsive medium being ambient water by means of pumps
    • 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
    • B63H11/04—Marine propulsion by water jets the propulsive medium being ambient water by means of pumps
    • B63H11/08—Marine propulsion by water jets the propulsive medium being ambient water by means of pumps of rotary type
    • 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
    • B63H11/04—Marine propulsion by water jets the propulsive medium being ambient water by means of pumps
    • B63H11/09—Marine propulsion by water jets the propulsive medium being ambient water by means of pumps by means of pressure pulses applied to a column of liquid, e.g. by ignition of an air/gas or vapour mixture
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H11/00—Marine propulsion by water jets
    • B63H11/12—Marine propulsion by water jets the propulsive medium being steam or other gas
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H11/00—Marine propulsion by water jets
    • B63H11/12—Marine propulsion by water jets the propulsive medium being steam or other gas
    • B63H11/14—Marine propulsion by water jets the propulsive medium being steam or other gas the gas being produced by combustion
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the separator which may be of the centrifugal type or of the gravity type, has a liquid outlet connected to a jet nozzle for performing useful work.
  • the separator also has a gas outlet which is connected to the inlet of a gas turbine through gas expansion means.
  • the drive shaft of the turbine is driveably connected to the pump or pumps and optionally to the separator.
  • a detector may be associated with the liquid level of the separator to control a valve in the gas intake of the pump.
  • Several variations include recycling liquid from the jet to the pump intake and recycling liquid from the outlet of the separator to its inlet.
  • the present invention relates in general to a composite gas-liquid pressurizing engine, and more particularly to a composite air-water pressurizing engine which is suitable for use in ships as a marine jet engine although it is not limited thereto.
  • This novel method of composite pressurizing results in advantages that thanks to the coexistence of the liquid the composite gas-liquid pressurizing pump can carry out a perfectly gas-tight compression without requiring any other lubricant which might be necessitated in a conventional gas compressor, and that the compression of the gas is carried out while being maintained at a temperature so low as possible and thus the eciency of the heat engine in the gas system may be enhanced.
  • a composite gas-liquid pressurizing engine comprising composite gas-liquid pump means for intaking gas and liquid separately and pressurizing them together, means for separating the pressurized gas and liquid fed from said composite gas-liquid pump means, and means for heating said pressurized and separated gas, wherein the energy possessed by said heated gas may be utilized by the intermediary of said separated liquid.
  • FIGS. la, 1b and lc show ilow diagrams with respect to gas, liquid and energy in the novel composite gasliquid pressurizing engine according to three representative embodiments of the present invention, respectively,
  • FIG. 1b is an explanatory table of symbols used in the drawings.
  • FIG. 2 shows a longitudinal cross-section view of one embodiment of the present invention
  • FIG. 3 shows a schematic longitudinal cross-section view of another embodiment of the present invention
  • FIG. 4 shows one example of the gas-to-liquid ratio regulating means to be incorporated in the embodiment of FIG. 2,
  • FIG. 5 shows another example of the gas-to-liquid ratio relating means to be incorporated in the embodiment of FG. 3, and
  • FIG. 6 shows a schematic longitudinal cross-section view of still another embodiment of the present invention.
  • FIG. 1 of the drawings three representative embodiments of the present invention are shown as FIGS. la, 1b and lc mainly for the purpose of illustrating the modes of ilows of gas, liquid and energy.
  • a thin-inked solid line arrow represents the gas ilow
  • a heavy-inked solid line arrow represents the liquid flow
  • a dash-dot line #arrow represents an energy flow.
  • a thin-inked dotted line arrow represents the gas flow which may be optionally provided depending upon whether the engine is of open type or closed type with respect to the gas system.
  • a heavy-inked dotted line arrow represents the liquid ow which may be optionally provided depending upon whether the engine is of open type or closed type with respect to the liquid system.
  • gas-liquid pump means 1 such as, for instance, a conventional screw pump a conventional nash pump where they are pressurized together
  • the pressurized gas and liquid being fed to separating means 2 where they are separated from each other, and the pressurized and separated gas is heated to an elevated temperature in heating mean-s 3 such as, for instance, a heat exchange charnber and a fuel combustion chamber of a conventional gas turbine.
  • the pressurized and heated gas gives its possessing energy to the above-mentioned composite gas-liquid pump means 1 for driving the same through any appropriate mechanisms such as a conventional gas turbine and a gear transmission system, and then the gas is exhausted to an outer atmosphere after it has susbtantially released its energy.
  • the above-mentioned engine forms an open system with respect to the gas.
  • the gas exhausted from this engine may be optionally fed back to the gas intake of the composite gas-liquid pump means l.
  • the engine forms a closed system with respect to the gas.
  • the pressurized and separated liquid from the separating means 2 serves as an output of this engine and gives its possessing energy to any desired load.
  • water is employed as the liquid and the engine output is realized as a water jet of a marine jet engine. Then the ship propelled by this marine jet engine is deemed to be the load with respect to the sea water. Accordingly, the closed system with respect to liquid as shown by a heavyinked dotted line cannot be realized.
  • the pressurized liquid serving as an engine output is used to generate a rotating power through a conventional hydraulic turbine, then the liquid may be, after releasing its possessing enero fed back to the liquid intake of the composite gas-liquid pump means 1 to complete a closed system with respect to the liquid.
  • the output of this type of engine may act upon the load either as a liquid jet or as a rotating power.
  • the origin of the energy is the fuel combustion in the heating means 3, and that the eventual energy output is the pressurized liquid fed from the separating means 2.
  • the composite gas-liquid pump means ll, separating means 2 and heating means 3 and their mutual relation is exactly the same as those shown in FIG. la.
  • the energy possessed by the heated gas is also applied to the composite gas-liquid pump means 1.
  • These transmissions of energy from the heated gas to the composite pump means l as well as the secondary pressurizing means 4 may be realized by means of a conventional gas turbine and a gear transmission system.
  • One preferred method is that relying upon a centrifugal force, in which the mixed and pressurized gas and liquid are rotated in a casing by means of a rotor having suitable vanes, and the pressurized gas is derived from the center portion of the casing while -the pressurized liquid is derived from the peripherical portion of the separator casing.
  • Another preferred method is that relying upon a difference in specific gravity between the gas and liquid in which the mixed and pressurized gas and liquid are guided to a bottom portion of the separator casing, then led upwardly through a vertical guide tube.
  • the pressurized liquid reaches the highest level and then descends downwardly in the casing around the vertical giude tube, and finally derived from the liquid output port provided at the bottom and peripherical portion of the separator casing.
  • the pressurized gas 1 s released from the highest level, that is, from the free liquid surface, and derived from the gas output port provided at the top of the casing.
  • the structure of the separator is somewhat complexed since it includes ya rotor which must be driven at a high speed.
  • this method is suitable for such case that the pressure of the liquid supplied from the separator is required to be higher than that of the gas which is supplied from the separator to the gas turbine, because as a nature of the centrifugal force the pressure of the gas localized at the center portion is lower than the pressure of the liquid which is shifted to the peripherical portion.
  • the second method Le., the gravitational method, the structure of the separtor is rela tively simple and it does not require a driving power.
  • the pressures of the separated gas and liquid are substantially equal to each other, and therefore, in some cases in which a higher liquid pressure is required by the load such as, for example, in the case of the marine water jet engine, the pressurized and separated liquid must be further pressurized by means of the energy supplied from the pressurized and heated gas before the liquid is yapplied to the load.
  • the embodiment shown in FIG. lb which incorporates the secondary pressurizing means 4 is often selected when the gravitational type of separator is employed.
  • the composiie gas-liquid pump means l, the separating means 2, and the heating means 3 and their mutual relation are also the same as those shown in FlGS. la and lb.
  • the secondary pressurizing means 4 just as provided in the second embodiment is also incorporated in this embodiment.
  • the energy possessed by the heated gas supplied from the heating means 3 is solely used to additionally pressurize the separated liquid from the separating means 2, and it is not directly applied to the composite gas-liquid pump means l just as done in the first and second embodiments.
  • the additionally pressurized liquid serving as an engine output acts not only upon the load but also upon the composite gasliquid pump means l for driving the same.
  • the engine output is used as a rotating power by means of a hydraulic turbine
  • the liquid system and the gas system may be formed either in an open type or in a closed type in the embodiments of FIGS. lb and lc as indicated by the thin-inked and heavy-inked dotted line arrows.
  • the engine according to the present invention is very efficient in function and relatively simple in construction which results in the reduction of weight, space and cost in comparison with the prior art engine such as formed by merely aggregating a conventional gas turbine and a hydraulic pump driven by said gas turbine.
  • the compression of the gas for use in the gas turbine and the pressurizing of the liquid for use as an engine output are carried out simultaneously at a relatively low temperature in a very gas-tight manner by means of the composite gas-liquid pump, without requiring to provide both the gas pump for the gas turbine and the hydraulic pump for the liquid output.
  • the additional pressurizing means 4 is used in the ernbodiments shown in FIGS. lb and lc, this additional pressurizing does not form an essential component of the general concept of the present invention, but it may be incorporated only when the load requires a higher liquid pressure than the pressure of the liquid at the liquid output of the separating means.
  • a composite gas-liquid pressuriziug engine according to the present invention is shown which is practiced as a water jet engine for propelling a ship.
  • this marine Water jet engine is mounted on the ship at a level lower than the Water level indicated by WL in such manner that a top opening of an air intake tube 11 is positioned above the water level WL and a water intake 12 and a water jet nozzle 13 are positioned at appropriate levels beneath the water level WL.
  • the composite gas-liquid pump 14 is essentially a conventional high speed screw pump, which functions to intake air and Water separately from the respective intake devices 11 and 12, to mix and pressurize them together while a screw rotor 20 is being rotated by the gas turbine 16 through the shafts 18, 19 and the gear transmission system 17, and to feed the pressurized air and Water leftwardly into the centrifugal separator 15.
  • the frusto-conical type of centrifugal separator 15 consists of a frusto-conical outer shell 21 which is xedly mounted and integrally coupled to an outer shell 22 of the high speed screw pulmp 14, and a frusto-conical rotor 23 which is coaxially and rotatably supported within the outer shell 21 by bearings 24 and 25 and has suitable form of blades for rotating the air and water held therein. In this gure, only the edges of the blades are shown at 26.
  • the rotor 23 having the blades is integrally coupled with the driving shaft 19 as well as the pump screw 20, so that the rotor may be rotated at a high speed when the gas turbine 16 operates.
  • the air and Water fed together from the high speed screw pump 14 and rotated within the rotor 23, are separated from each other owing to the centrifugal force acted upon during this rotation and the difference in specific gravity between the air and water.
  • the water occupies the peripherical region as indicated by W, while the air occupies the center region as indicated by A, the boundary surface Ibetween these two regions W, A being shown by a dotted line 27.
  • the separated Water is derived from the peripherical portion of the end surface of the rotor having a larger diameter through an opening 28 of the outer shell 21 and the water output nozzle 13.
  • the separated air is derived from the center portion of the end surface of the rotor having a larger diameter through a guide pipe 29 to a heat exchange chamber of the gas turbine 16.
  • the pressurized and separated gas is, after preheated in the heat exchange chamber by the remaining heat of the exhaust gas from the gas turbine 16, heated to an elevated temperature in the succeeding combustion chamber 31 by the combustion heat of the fuel supplied from a fuel nozzle 32. Then the heated gas serves to drive the gas turbine rotor coupled to the shaft 18, and after having released its possessing energy it is exhausted to an outer atmosphere through an exhaust tube 33, the heat exchanger 30 and an exhaust tube 34.
  • FIG. 2 comprises an apparatus for regulating the ratio of flowrate of the air to water, which consists of an adjusting valve 35 provided in the air intake tube 11 and a float 36 for detecting the position of the Water surface within the separator 15.
  • the oat 36 is rotatable about its pivot 37, and its left-side end moves in accordance with the change of the water surface. Therefore, the change of water surface may be detected as an angular displacement of the oat 36.
  • This angular displacement controls the position of the adjusting valve 35 through an appropriate mechanical linkage so that when the water surface in the separator is raised the adjusting valve 35 may -be further opened to permit more air being intaken to the composite pump 14.
  • the water jet eng-ine illustrated in FIG. 2 corresponds to the embodiment shown in FIG. la in connection to the mode of utilizing the energy possessed by the heated gas. Also it will be seen that the separator employed in this example is of centrifugal type, and both the gas system and liquid system are of open end type.
  • FIG. 3 With lreference t-o FIG. 3, there is shown another embodiment of the present invention which corresponds to the embodiment shown in FIG. lb in connection to the mode of utilization of energy, and in which a separator making use of the difference in specific gravity between the ⁇ air and water is employed.
  • This embodiment is Valso practiced as a water jet engine, which comprises an air intake 38, a water intake 39, a composite air-water pump 40 essentially consisting of a high speed screw pump, a gravita-tional type of separator 41, a secondary water pump 42, a water jet nozzle 43, an air output tube 44 of the separator, a heat exchanger 45, a combus-tion chamber 46, a conventional gas turbine 47, an ex'haust 48 of the gas turbine, and a gear transmission system 49.
  • the composite air-water pump 40 and the secondary water pump 42 are driven together by the gas turbine through the gear transmission system 49 and the bevel gear assembly 50 provided in the water intake region 39.
  • the air and water intaken respectively through the air intake 38 and the water intake 39 are mixed and pressurized together b-y the high speed screw pump 40 and then fed to the separator 41.
  • the separator 41 the water and air go upwardly along a guide tube 51. After arrival at the highest level ⁇ 52, the water goes downwardly outside the guide tube and Iis fed to the secondary water pump 42.
  • the pressure of the water output and the gas output is substantially equal, and consequently the water pressure is not suicient to be used as a water jet. Therefore, the pressure of the separated water is increased by the secondary water pump 42 and then ejected through the water jet nozzle 43 for propelling the ship on which this marine jet engine is mounted.
  • the air admixed with the water is released at the highest level 52 of the water in the separator 52, and then guided upwardly through the gas output tube 44.
  • the air is heated to an elevated temperature in the comfbustion chamber 46 by means of the combustion heat of the fuel supplied through a fuel nozzle 53.
  • the heated air serves to drive the gas turbine 47, and after releasing its possessing energy it is exhausted to an outer atmosphere through the heat exchanger 45 and the air exhaust tube 48.
  • thus generated rotating power is used to drive the composite pump 46 and the secondary pump 42.
  • both the water jet engines in FIGS. 2 and 3 form open systems with respectV to both the air and the water, they may be arbitrarily modified to closed systems by feeding back the air exhaust to the air intake, or by driving a wate-r turbine by means of the water output and feeding back the water exhaust of the water turbine to the water intake of this engine.
  • the combustion chamber asse 24e should be replaced by an indirect heating chain-ber which serves to heat the pressurized air Iby means of ⁇ an outside fuel burner. Since the cross-section view in FIG.
  • FIG. 3 is depicted in a schematic manner, the air-to-water ratio regulating apparatus as described with reference to FIG. 2 is not shown in this figure. However, it is apparent that if it is necessitated to regulate the air-to-water ratio, the similar apparatus may be incorporated in the water jet engine shown in FIG. 3.
  • FIG. 4 shows such regulatin y apparatus which is adapted to be incorporated in a centrifugal type of separator. This is an enlarged view of the regulating apparatus 35, 36 and 37 shown in FIG. 2. While, FIG. shows a regulating apparatus which is adapted to be incorporated in a gravitational type of separator such as shown in FIG. 3.
  • a choke valve 54 for adjusting the gas llow is provided in a gas intake tube 55 which corresponds to the gas intake l1, 38 in FIGS. 2 and 3 respectively.
  • the valve 54 is rotatable around its pivot Se and rigidly coupled to an actuating lever 57.
  • the valve S4 and the actuating lever 57 are subjected to a bias force on the anticlockwise direction by means of any suitable resilient means (not shown). Therefore, it no drag force is acted upon the lever 57 from the liquid level detecting device in the right hand side, the adjusting valve S4 takes the completely choked position as shown by the dotted line.
  • This adjusting valve is shown in FIG. 2 at 3S and also in FIG. 3 by three slant lines in the gas intake 38 schema-tically.
  • a movable iioat 58 is supported at a pivot 59, and an actuating lever 66 is rigidly coupled to this movable oat 53. Between the extreme ends of the levers 57 and 60 is stretched a thin wire or string 61.
  • the liquid level detecting device consisting of the iioat 5S and lever d() is schematically shown in FIG. 2 at 36, 37. It is assumed that the liquid level in the centrifugal separator such as shown in FIG. 2 will vary between the lowest level L1 and the highest level L2 depending upon the ratio of how rate of the gas to liquid. Obviously the movable oat S8 may swing between the two positions illustrated by the solid line and the dotted line respectively.
  • the float 58 and the lever 60 rotates integrally in the clockwise direction and thus causes a clockwise rotation of the valve S4 and the lever 57 through the wire or string 61. Accordingly, more gas iiow is introduced through the gas intake tube 55 into the composite gas-liquid pump and the separator. Since the gas-to-liquid ratio is enhanced, the liquid level in the separator is suppressed to rise, and thus the predetermined position of the liquid level between Ll and L2 may be maintained. Quite similarly, when the liquid level tends to fall toward the level Ll, it is suppressed by slightly choking the gas flow in the gas intake 55, and thus the predetermined liquid level may be maintained. Consequently the ratio of flow rate of the gas to liquid may be maintained at a predetermined value during the operation oi this engine.
  • FIG. 5 there is shown a gravitational type of separator provided with a liquid level detecting device.
  • a liquid detainer 62' is provided below Ithe outlet 65 whereby the separated gas in chamber 6 is permitted to hit the detainer and whereby the liquid splash involved therein falls to insure that air alone will pass through the gas outlet and prevent liquid from passing into the gas turbine.
  • a movable float 68 consisting of a oat head 69 which follows the liquid level 64 and an actuating lever '70 which is pivotably mounted at 7l.
  • the extreme end of the lever 74B is connected to a thin wire or string 72 which leads to an actuating lever of an adjusting valve such as shown in FIG. 4.
  • a guard tube 73 surrounds the iloat head 69.
  • the liquid level detecting device 68, 69, 76, 71, 72, 73 in FIG. 5 functions quite similarly to the detecting device 58, 59, et) in FIG. 4, if the arrowed end of the wire or string 72 is connected to the actuating lever of the adjusting choke valve in the gas intake tube such as shown in FIG. 4.
  • the liquid level 67 in the separator chamber 62 may be maintained at a xed level for keeping a predetermined value ot the gas-to-liquid ratio.
  • FIG. 6 there is shown another embodiment of the present invention which is equivalent to the mode shown in FIG. lc in connection to the method of utilizing the energy possessed by the heated gas.
  • the part 74 is a conventional nash pump having a rotor 7S mounted on a common drive shaft 76, an air intake 77, a water intake 78, an air outlet 79 and a water outlet Si). This nash pump 74, functions to mix and pressurize the gas and liquid together and supply them separately through the respective outlets by making use of a centrifugal force.
  • the nash pump is deemed to be essentially a combination of a composite gas-liquid pump and a centrifugal separator.
  • a cooling fan 8l for the water system and a water turbine 82 On the common drive shaft 76 are also mounted a cooling fan 8l for the water system and a water turbine 82, and any desired load may be coupled to the protruding free end 83 ofthe shaft 76.
  • the ⁇ air supplied from the air outlet 79 of the nas'h pump 74 passes through a check valve 84 into a heat exchanger S5.
  • the air flows through a heating chamber 86 where it is heated to an elevated temperature by means of an outside fuel burner S7.
  • the energized air goes through an interaction chamber 88 where the air gives its possessing energy to the encountered water yfed from the water outlet Sil of the nash pump 74 so that the water is further pressurized.
  • the air in the interaction chamber S is, after releasing its energy, led to the air intake 77 of the nash pump 74 through an air exhaust tube 88 and heat exchanger 85 as shown by the thin-inked solid line arrows.
  • the additionally pressurized water in the interaction chamber 88 acts upon the water turbine 82 so that a rotating power may be generated on the drive shaft 76, and then it is fed back to the water intake 7S of the nash pump 74 through a cooler where the water is cooled by means of the cooling fan 8l mounted on the drive shaft 76.
  • the above-described engine is formed in a closed type with respect to air, it may be easily modified to an open end type by opening the exhausttube 89 and the air intake toward an outer atmosphere.
  • the high speed screw pump referred to above is particularly used for water jet, which pump is abled to rotate at fa-r higher speed than any conventional screw pump could. This is due not only to the fact that the air is admixed but also that water flows quite naturally into the pump from the stream caused relatively by water pressure or advance of ship, instead of sucking water as seen in the conventional pumps. In order that water may readily get into the pump, water inlet is widely enough opened with a screw-thread cutting. Of course hence air is sucked into the pump by created low pressure, such Water inlet should not be opened too wide to interfere with the air inlet portion.
  • a composite gas-liquid engine comprising composite gas-liquid pump means for intaking gas and liquid, a liquid intake and a separate gas intake, means within the pump for combining under pressure liquid and gas passing through said intakes, said pump having an outlet for the combined gas and liquid under pressure, separation means connected to said outlet -for separating the liquid from the gas, a jet discharge device for the separated liquid, a gas turbine having a gas inlet, and means, including a gas expansion unit, for conducting the separated gas from the separation means to the gas turbine inlet.
  • a composite gas-liquid engine comprising composite gas-liquid pump means for intaking gas and liquid, a liquid intake and a separate gas intake, means within the pump for combining under pressure liquid and gas passing through said intakes, said pump having an outlet for the combined gas and liquid under pressure, separation means connected to ⁇ said outlet for separating the liquid from the gas, means, including a gas expansion unit, for conducting the separated gas from the separation means to the separated liquid to further pressurize the liquid, a hydraulic motor having a liquid inlet, and means for conducting the separated and further pressurized liquid from the separator means to said hydraulic motor inlet.
  • a composite gas-liquid engine as claimed in claim 3 in which the centrifuge comprises a frusto-conical 70 stator and a corresponding frusto-conical rotor within the stator, inlet means at the narrower end of the stator connected to the outlet of the pump, a rst outlet means at .the Wider end of the stator adjacent the periphery for the discharge of the separated liquid and a second outlet means at said wider end adjacent the center for the discharge of separated gas.
  • a composite gas-liquid engine as claimed in claim 1 in which the gas intake includes a valve to control the ilow of air therethrough, a detector in said separation means for detecting the position of the level of separated liquid therein and means responsive to said detector for actuating said valve.
  • a composite gas-liquid engine as claimed in claim 1 in which the pump has a rotary member, said rotary member being connected to and driven by the turbine.
  • a composite gas-liquid engine as claimed in claim 4 in which the liquid outlet of the centrifuge is connected directly to the liquid inlet of a hydraulic motor.
  • a composite gas-liquid pressurizing engine as claimed in claim 4 in which the gravity chamber comprises a chamber having therein an upwardly extending inlet means at the lower portion of the chamber connected to the outlet of the pump, a rst outlet means at the u-pper portion of the chamber for the discharge of the separated gas, a second outlet means at the lower portion of the chamber for the discharge of the separated liquid, the upper end of said inlet means being below the lowest attainable level of the separated liquid in the chamber.
  • a composite gas-liquid engine as claimed in claim 2 in which the pump and separator have rotary members, said rotary members being connected to yand driven by the hydraulic motor.
  • a composite gas-liquid engine as claimed in claim 17 in which the liquid intake of the screw pump is cut along the screw thread of the pump and the separate gas intake is adjacent to said liquid intake.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
US530161A 1966-02-25 1966-02-25 Composite gas-liquid pressurizing engine Expired - Lifetime US3386246A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US530161A US3386246A (en) 1966-02-25 1966-02-25 Composite gas-liquid pressurizing engine
SE2561/67A SE324970B (fr) 1966-02-25 1967-02-24
DE19671626106 DE1626106A1 (de) 1966-02-25 1967-02-24 Kombiniertes Gas- und Fluessigkeitsdruck-Triebwerk
FR96453A FR1512712A (fr) 1966-02-25 1967-02-24 Moteur à compression combinée gaz-liquide
GB8878/67A GB1161779A (en) 1966-02-25 1967-02-24 Composite Gas-Liquid Pressurizing Engine.

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US530161A US3386246A (en) 1966-02-25 1966-02-25 Composite gas-liquid pressurizing engine

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US3386246A true US3386246A (en) 1968-06-04

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US (1) US3386246A (fr)
DE (1) DE1626106A1 (fr)
FR (1) FR1512712A (fr)
GB (1) GB1161779A (fr)
SE (1) SE324970B (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3803836A (en) * 1970-10-02 1974-04-16 Waagner Biro Ag Thermal power plants and methods for operating the same
US3951094A (en) * 1973-10-15 1976-04-20 Jastram-Werke Gmbh Kg Gas-driven, pulsating water jet propulsive duct drive for watercraft
WO1991004907A1 (fr) * 1989-09-28 1991-04-18 Allied-Signal Inc. Systeme de propulsion a reaction sous l'eau

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2033210A (en) * 1934-05-14 1936-03-10 Stephens Pump Company Pump
US2069338A (en) * 1934-05-14 1937-02-02 Stephens Pump Company Pump
US2151949A (en) * 1934-07-30 1939-03-28 Edward T Turner Method and apparatus for converting heat energy into mechanical energy
US2268357A (en) * 1939-03-06 1941-12-30 Edward T Turner Method and apparatus for producing power
US3137234A (en) * 1959-08-10 1964-06-16 Roper Hydraulics Inc Method of pumping and separating liquid and gaseous fluids

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2033210A (en) * 1934-05-14 1936-03-10 Stephens Pump Company Pump
US2069338A (en) * 1934-05-14 1937-02-02 Stephens Pump Company Pump
US2151949A (en) * 1934-07-30 1939-03-28 Edward T Turner Method and apparatus for converting heat energy into mechanical energy
US2268357A (en) * 1939-03-06 1941-12-30 Edward T Turner Method and apparatus for producing power
US3137234A (en) * 1959-08-10 1964-06-16 Roper Hydraulics Inc Method of pumping and separating liquid and gaseous fluids

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3803836A (en) * 1970-10-02 1974-04-16 Waagner Biro Ag Thermal power plants and methods for operating the same
US3951094A (en) * 1973-10-15 1976-04-20 Jastram-Werke Gmbh Kg Gas-driven, pulsating water jet propulsive duct drive for watercraft
WO1991004907A1 (fr) * 1989-09-28 1991-04-18 Allied-Signal Inc. Systeme de propulsion a reaction sous l'eau

Also Published As

Publication number Publication date
DE1626106A1 (de) 1971-03-25
GB1161779A (en) 1969-08-20
FR1512712A (fr) 1968-02-09
SE324970B (fr) 1970-06-15

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