US2594629A - Jet-reaction motor, including gas nozzle generating steam - Google Patents

Jet-reaction motor, including gas nozzle generating steam Download PDF

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US2594629A
US2594629A US774046A US77404647A US2594629A US 2594629 A US2594629 A US 2594629A US 774046 A US774046 A US 774046A US 77404647 A US77404647 A US 77404647A US 2594629 A US2594629 A US 2594629A
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jet
rotor
motor
generating steam
including gas
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US774046A
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Exner Hellmuth Alfredo Arturo
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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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F02C3/165—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust

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  • the present invention relates to jet propulsion motors and has for a main object improvements over other known types of motor and consisting in the provision of means conducting the combustion and evaporation products from a stator chamber housing the rotor to an expulsion conduit.
  • the centrifugal force developed by the rotor of the motor is utilized in compressing the air prior .to combustion and the conventional turbine driving the rotor is dispensed with since the burnt gases by their reaction on jets emitting them drive the rotor at high speed.
  • FIG. 1 is a fragmentary section of the jet propulsion motor constituting the preferred embodiment of my invention
  • Figure 2 is a section at right angles to the section of Figure 1;
  • Figure 3 is a top plan view of a modification of two motors including two stator chambers
  • Figure 4 is an elevation partly in section oi the modification.
  • Figures 1 and 2 illustrate a motor comprising a rotor l divided by radial partitions into a plurality of sectoral air chambers 2 each communicating with a precombustion air heating chamber 3 arranged at the periphery of an air chamber by an opening 4.
  • the rotor includes a shaft 5 having two axial conduits 6 and I communicating with a plurality of radial conduits 8 and 9, respectively.
  • Each conduit 8 is connected to an atomizer or injection nozzle Ill atomizing the fluid fuel while conduit 9 conduct-s water or other non-combustible liquid.
  • Nozzle H has an opening l2 whereby it communicates with a combustion chamber l3 housing an ignition rod i5 opposite opening 12 and in turn communicating with the precombustion chamber 3 by an aperture I4.
  • the gases burned by ignition rod 15 are expelled through an opening 16 after having passed through a plurality of pipes ll extending through a vaporization chamber ll which communicates at one end with the outside by a nozzle l8 terminating. in an outwardly expanding cone i9 and is supplied at the other end with water by conduit 9.
  • Cones t5 and openings 6 are arranged on the periphery of the rotor and the steam andproducts of combustion respectively expelled. there-- from impinge. against blades or vanes 2!] fixed an annular chamber of stator 2
  • Air for combustion is supplied to chambers 2 by central openings 23 concentric with shaft 5 and while the motor is rotating at about 500 revolutions per minute, is impelled by centrifugal force through openings 41 into precombustion chambers 3 and thence through openings 14 into combustion chambers l3.
  • the mixture of compressed air and atomized fuel is ignited by rod l5 and hurled against stator blades 2
  • Opening of valve 25 causes inoculation of the non-combustible liquid through conduits 1 and 9 to chamber H where the liquid is vaporized by contact with tubes l'I conducting the burnt gases.
  • Figures 3 and 4 illustrate a modification applying the motor to an aircraft by providing a housing 255 with an internal spirally-shaped surface and communicating with the outside through expulsion conduit 21.
  • Housing 26 functions as a stator of a motor the rotor of which is spaced from the internal housing surface to form a channel 29 having a cross section increasing toward conduit 21 through which the gases leave as a high powered J'et.
  • the formers are used only during the time the craft is airborne or in cases of emergency. Under normal conditions the atomizers work alternatively, the supply of fuel to the idle atomizers being shut-off, but since air will circulate through all openings 23, the temperature Within conduit 29 will be lowered.
  • the motor operates exclusively by means of the products of combustion, therefore no evaporation chambers are provided, the displacement of the aircraft being elfected by the reaction of the gas at the outer end of conduit 27.
  • the same may be provided with an outlet opening in a direction opposite to the direction of that causing the displacement of the aircraft in order that the products of combustion may be utilized to exert a braking effect.
  • an annular stator housing open on its inner periphery, a pair of bearings fixed to the stator housing, a shaft journaled in the bearings, a hollow rotor fixed to the shaft and extending into the inner periphery of the stator and having an air inlet adjacent the shaft, a plurality of angularly spaced air heating chambers in the rotor adjacent the periphery thereof and supplied with air entering through the inlet by the rotation of the rotor, a plurality of combustion chambers one in each air heating chamber and having an air intake communicating therewith, a plurality of ignition means one in each combustion chamber and disposed in a plane at right angles to the rotor axis, said plane also containing the corresponding intake, a plurality of atomizers one in each combustion chamber and disposed in said plane and on the side of the corresponding ignition means opposite the corresponding air intake, a plurality of spaced vaporization chambers in the rotor adjacent the periphery thereof.
  • a plurality of radial water conduit means each supplying one of the vaporization chambers with water by the rotation of the rotor and one for each combustion chamber
  • a plurality of other conduit means at least one for each of the vaporization chamber means and conducting the burnt gases from a combustion chamber through the corresponding vaporization chamber, substantial tangential outlets each connected to a vaporization chamber, and separate substantial tangential outlets for the other conduit means.

Description

April 1952 H. A. A. EXNER JET REACTION MOTOR, INCLUDING GAS NOZZLE GENERATING STEAM 2 SHEETS-SHEET Filed Sept. 15, 1947 INVENTOR Hellmul'k Alfredo Arl'uro Eaczzer.
ATTORNEY A ril 29, 1952 H. A. A. EXNER JET REACTION-.MOTOR, INCLUDING GAS NOZZLE GENERATING STEAM 2 SHEETS-SHEET 2 Filed Sept. 15, 1947 INVENTOR .HellmufihAbz-edo Ariuro Eocner.
ATTORNEY Patented Apr. 29, 1952 JET-REACTION RIOTOR, INCLUDING GAS NQZZ-LE GENERATING STEAM Heiimuth Alfredo Arturo Exner, Florida, Argentina Application September 15, 1947, SerialNo. 774,046- In Argentina March 29, 1947 2 Claims. 1
The present invention relates to jet propulsion motors and has for a main object improvements over other known types of motor and consisting in the provision of means conducting the combustion and evaporation products from a stator chamber housing the rotor to an expulsion conduit.
The most modern motor of that type is at present the Derwent of Rolls-Royce; yet its outstanding disadvantage is the loss of about two-thirds of the total power generated, being lost in the ventilator or turbine system in an efiort to compress the air prior to combustion.
According to the present invention the centrifugal force developed by the rotor of the motor is utilized in compressing the air prior .to combustion and the conventional turbine driving the rotor is dispensed with since the burnt gases by their reaction on jets emitting them drive the rotor at high speed.
By conducting these gases through jets of a certain direction and sense, unequalled speed is attained with a fuel consumption far lower than that of known motors.
Other objects will become apparent after reading the following description.
To fully understand the invention, the description should be read in connection with the accompanying drawings forming part of the application and illustrating the invention by means of an example rather than by a limitation and wherein:
Figure 1 is a fragmentary section of the jet propulsion motor constituting the preferred embodiment of my invention;
Figure 2 is a section at right angles to the section of Figure 1;
Figure 3 is a top plan view of a modification of two motors including two stator chambers;
Figure 4 is an elevation partly in section oi the modification.
In the drawings, in which like characters of reference designate like or similar parts, Figures 1 and 2 illustrate a motor comprising a rotor l divided by radial partitions into a plurality of sectoral air chambers 2 each communicating with a precombustion air heating chamber 3 arranged at the periphery of an air chamber by an opening 4.
The rotor includes a shaft 5 having two axial conduits 6 and I communicating with a plurality of radial conduits 8 and 9, respectively. Each conduit 8 is connected to an atomizer or injection nozzle Ill atomizing the fluid fuel while conduit 9 conduct-s water or other non-combustible liquid.
Nozzle H) has an opening l2 whereby it communicates with a combustion chamber l3 housing an ignition rod i5 opposite opening 12 and in turn communicating with the precombustion chamber 3 by an aperture I4.
The gases burned by ignition rod 15 are expelled through an opening 16 after having passed through a plurality of pipes ll extending through a vaporization chamber ll which communicates at one end with the outside by a nozzle l8 terminating. in an outwardly expanding cone i9 and is supplied at the other end with water by conduit 9.
Cones t5 and openings 6 are arranged on the periphery of the rotor and the steam andproducts of combustion respectively expelled. there-- from impinge. against blades or vanes 2!] fixed an annular chamber of stator 2| which is open at its inner periphery and rigid with bearings for motor shaft 5 and receive a part of the outer periphery of the rotor. The steam is then condensed in a condensing means guided by channel means 22.
Air for combustion is supplied to chambers 2 by central openings 23 concentric with shaft 5 and while the motor is rotating at about 500 revolutions per minute, is impelled by centrifugal force through openings 41 into precombustion chambers 3 and thence through openings 14 into combustion chambers l3. The mixture of compressed air and atomized fuel is ignited by rod l5 and hurled against stator blades 2|.
Opening of valve 25 causes inoculation of the non-combustible liquid through conduits 1 and 9 to chamber H where the liquid is vaporized by contact with tubes l'I conducting the burnt gases.
The high pressure steam leaving through nozzle I3 out cones I9 is hurled against blades 20 of stator 2! and is then conducted through conduit 22 to a suitable condenser.
Figures 3 and 4 illustrate a modification applying the motor to an aircraft by providing a housing 255 with an internal spirally-shaped surface and communicating with the outside through expulsion conduit 21.
Housing 26 functions as a stator of a motor the rotor of which is spaced from the internal housing surface to form a channel 29 having a cross section increasing toward conduit 21 through which the gases leave as a high powered J'et.
In order to lower the temperature of the heat produced in the combustion chambers and conduit 29, the formers are used only during the time the craft is airborne or in cases of emergency. Under normal conditions the atomizers work alternatively, the supply of fuel to the idle atomizers being shut-off, but since air will circulate through all openings 23, the temperature Within conduit 29 will be lowered.
In the embodiment illustrated in Figures 3 and 4, the motor operates exclusively by means of the products of combustion, therefore no evaporation chambers are provided, the displacement of the aircraft being elfected by the reaction of the gas at the outer end of conduit 27.
The same may be provided with an outlet opening in a direction opposite to the direction of that causing the displacement of the aircraft in order that the products of combustion may be utilized to exert a braking effect.
I claim:
1. In a jet-reaction motor, the combination,
comprising, an annular stator housing open on its inner periphery, a pair of bearings fixed to the stator housing, a shaft journaled in the bearings, a hollow rotor fixed to the shaft and extending into the inner periphery of the stator and having an air inlet adjacent the shaft, a plurality of angularly spaced air heating chambers in the rotor adjacent the periphery thereof and supplied with air entering through the inlet by the rotation of the rotor, a plurality of combustion chambers one in each air heating chamber and having an air intake communicating therewith, a plurality of ignition means one in each combustion chamber and disposed in a plane at right angles to the rotor axis, said plane also containing the corresponding intake, a plurality of atomizers one in each combustion chamber and disposed in said plane and on the side of the corresponding ignition means opposite the corresponding air intake, a plurality of spaced vaporization chambers in the rotor adjacent the periphery thereof. a plurality of radial water conduit means each supplying one of the vaporization chambers with water by the rotation of the rotor and one for each combustion chamber, and a plurality of other conduit means at least one for each of the vaporization chamber means and conducting the burnt gases from a combustion chamber through the corresponding vaporization chamber, substantial tangential outlets each connected to a vaporization chamber, and separate substantial tangential outlets for the other conduit means.
2. The combination according to claim 1 and also comprising a pair of axial conduits formed in the shaft one supplying air and the other supplying water to the water conduit means, and radial air conduits each connecting the axial air conduit with an atomizer.
HELLMUTH ALFREDO ARTURO EXNER.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 2,256,198 Hahn Sept. 16, 1941 FOREIGN PATENTS Number Country Date 378,868 France Aug. 24, 1907 440,593 France May 7, 1912 499,874 Germany June 14, 1930 598,991 Germany June 22, 1934 287,701 Great Britain Apr. 26, 1928
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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3005311A (en) * 1957-08-08 1961-10-24 Frederick W Ross Gas turbine engine with combustion inside compressor
US3053048A (en) * 1961-02-02 1962-09-11 James N Preston Fire jet torque and propulsion reaction engine
US3092967A (en) * 1961-09-15 1963-06-11 James N Preston Super-charged fire jet torque and propulsion reaction engine
US3095703A (en) * 1961-09-19 1963-07-02 James N Preston Super-charged jet torque and propulsion reverse reaction engine
US3321911A (en) * 1965-02-12 1967-05-30 Myles Tommie Lynn Gas turbine engine with rotating combustion chamber
US4024705A (en) * 1974-01-14 1977-05-24 Hedrick Lewis W Rotary jet reaction turbine
FR2385899A1 (en) * 1977-03-29 1978-10-27 Hedrick Lewis Combined gas turbine and jet IC engine - has combustion chamber in rotor with exhaust producing reaction jet turning effect
US4625509A (en) * 1980-04-21 1986-12-02 Sheppard Sr Darrel J Combustion engine
WO1998016722A2 (en) * 1996-10-01 1998-04-23 H.P.G. Promotion & Investment (1993) Ltd. Orbiting engine
US6298653B1 (en) 1996-12-16 2001-10-09 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6347507B1 (en) 1992-09-14 2002-02-19 Ramgen Power Systems, Inc. Method and apparatus for power generation using rotating ramjets
US6446425B1 (en) 1998-06-17 2002-09-10 Ramgen Power Systems, Inc. Ramjet engine for power generation
US20050235648A1 (en) * 2002-06-26 2005-10-27 David Lior Orbiting combustion nozzle engine
US9291095B2 (en) 2013-03-15 2016-03-22 Randy Koch Rotary internal combustion engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR378868A (en) * 1906-06-14 1907-10-18 Turbo-Moteurs] Improvements to turbo-engines or gas turbines with continuous combustion under constant pressure
FR440593A (en) * 1911-05-06 1912-07-13 Alhonse Papin Method for providing the lift and propulsion of bodies immersed in a fluid
GB287701A (en) * 1925-01-03 1928-04-26 Benjamin Charles Carter Improvements in internal combustion turbines
DE499874C (en) * 1927-02-15 1930-06-14 Joseph Hetterich Jr Gas steam turbine with rotating combustion chambers arranged on a wheel rim
DE598991C (en) * 1932-07-30 1934-06-22 Gustav Brueckner Internal combustion turbine, in which the compression of the propellant gases takes place in channels of the impeller that are open to the circumference
US2256198A (en) * 1938-05-27 1941-09-16 Ernst Heinkel Aircraft power plant

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR378868A (en) * 1906-06-14 1907-10-18 Turbo-Moteurs] Improvements to turbo-engines or gas turbines with continuous combustion under constant pressure
FR440593A (en) * 1911-05-06 1912-07-13 Alhonse Papin Method for providing the lift and propulsion of bodies immersed in a fluid
GB287701A (en) * 1925-01-03 1928-04-26 Benjamin Charles Carter Improvements in internal combustion turbines
DE499874C (en) * 1927-02-15 1930-06-14 Joseph Hetterich Jr Gas steam turbine with rotating combustion chambers arranged on a wheel rim
DE598991C (en) * 1932-07-30 1934-06-22 Gustav Brueckner Internal combustion turbine, in which the compression of the propellant gases takes place in channels of the impeller that are open to the circumference
US2256198A (en) * 1938-05-27 1941-09-16 Ernst Heinkel Aircraft power plant

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3005311A (en) * 1957-08-08 1961-10-24 Frederick W Ross Gas turbine engine with combustion inside compressor
US3053048A (en) * 1961-02-02 1962-09-11 James N Preston Fire jet torque and propulsion reaction engine
US3092967A (en) * 1961-09-15 1963-06-11 James N Preston Super-charged fire jet torque and propulsion reaction engine
US3095703A (en) * 1961-09-19 1963-07-02 James N Preston Super-charged jet torque and propulsion reverse reaction engine
US3321911A (en) * 1965-02-12 1967-05-30 Myles Tommie Lynn Gas turbine engine with rotating combustion chamber
US4024705A (en) * 1974-01-14 1977-05-24 Hedrick Lewis W Rotary jet reaction turbine
FR2385899A1 (en) * 1977-03-29 1978-10-27 Hedrick Lewis Combined gas turbine and jet IC engine - has combustion chamber in rotor with exhaust producing reaction jet turning effect
US4625509A (en) * 1980-04-21 1986-12-02 Sheppard Sr Darrel J Combustion engine
US6510683B1 (en) 1992-09-14 2003-01-28 Ramgen Power Systems, Inc. Apparatus for power generation with low drag rotor and ramjet assembly
US6347507B1 (en) 1992-09-14 2002-02-19 Ramgen Power Systems, Inc. Method and apparatus for power generation using rotating ramjets
WO1998016722A3 (en) * 1996-10-01 1998-07-09 H P G Promotion & Investment 1 Orbiting engine
US6295802B1 (en) * 1996-10-01 2001-10-02 David Lior Orbiting engine
WO1998016722A2 (en) * 1996-10-01 1998-04-23 H.P.G. Promotion & Investment (1993) Ltd. Orbiting engine
US6298653B1 (en) 1996-12-16 2001-10-09 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6434924B1 (en) 1996-12-16 2002-08-20 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6446425B1 (en) 1998-06-17 2002-09-10 Ramgen Power Systems, Inc. Ramjet engine for power generation
US20050235648A1 (en) * 2002-06-26 2005-10-27 David Lior Orbiting combustion nozzle engine
US7404286B2 (en) 2002-06-26 2008-07-29 R-Jet Engineering Ltd. Orbiting combustion nozzle engine
US9291095B2 (en) 2013-03-15 2016-03-22 Randy Koch Rotary internal combustion engine
US9828907B2 (en) 2013-03-15 2017-11-28 Randy Koch Rotary internal combustion engine

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