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Publication numberUS1828784 A
Publication typeGrant
Publication dateOct 27, 1931
Filing dateAug 16, 1927
Priority dateNov 28, 1923
Publication numberUS 1828784 A, US 1828784A, US-A-1828784, US1828784 A, US1828784A
InventorsRene Perrin
Original AssigneeFrance Etat
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Pressure fluid generator
US 1828784 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

R. PERRIN Oct. 27, 1931.

PRESSURE FLUID GENERATOR Filed Aug. 16. 1927 2 Sheets-Sheet R. Perri? Oct. 27, 1931. PERRm 1,828,784

PRESSURE FLUID GENERATOR Filed Aug. 16, 1 927. 2 Sheets-Sheet 2 VIIIIIIIIIIIIA JNVEN 73K Patented Oct. 27, 1931 UNITED STATES PATENT OFFICE RENE PERRIN, OF TO'ULON, FRANCE, ASSIGNOR TO THE STATE OF FRANCE, BEPBESENT- ED BY THE MINISTER OF THE NATIONAL NAVY, F PARIS, FRANCE ranssunn rLum GENERATOR Application filed August 16, 1927, Serial No. 213,403, and in France November 28, 1923.

The present invention relates to a gas generator producing power ,gas under pressure for the supply of the engines used in torpedoes of the modern types, the said generator being suitably arranged and supplied with a comburant (oxygen or a fluid containing oxygen), fuel and optionally with a coolmg liquid in a particular manner whereby the consumption of the comburant for a given amount of work will be reduced.

The said gas generator is of the type in which the power fluid under pressure is produced by the combustion reaction of a gaseous comburant such as air or oxygen with a liquid fuel, a cooling fluid being further introduced into the gases of combustion whereby they will be cooled to a point at which they wlll offer no damage to the engine, while permitting the use of the comburant as com- 90 pletely as possible.

In the said invention, suitable fuel feeding devices are placed at successive points upon the path of the gases, between the comburant inlet and the discharge end of the generator.

Due to this special method of feeding the fuel, the whole of the comburant supplied to the generator will enter into the combustion reaction, and this oflers an advantage in the case of torpedoes, since the consumption of comburant for a 'ven amount of work is reduced to a minimum, which comburant, being in the gaseous state, requires the use of containers of an excessive weight. This advantage results in particular from the fact that it becomes easier to regulate the successive temperatures to which the reacting bodies are heated, and on the other hand this will further the construction of the apparatus.

It has already been proposed to supply the combustion chamber with a mixture of comburant with an excess of fuel, which excess serves to cool the gases of combustion to the proper point for feeding the engine, but since the whole amount of the fuel is admitted together with the whole amount of the comburant, the ignition becomes difiicult, especially if the gas is to be supplied to the engine at a low temperature, so that the combustion is imperfect, and a part of the comburant repoints on the path of the gases in combustion,

it is feasible to burn the whole of the comburant in the interior of the generator and hence to utilize it to the maximum degree of the production of energy, and without danger of the backfiring above mentioned.

The said invention comprises other features by which the energy will be increased,

while limiting the temperature of the gas to a degree at which there will to the engine.

In the diagrammatic drawings which are given by way of example:

F1g. 1 is an axial section of a gas generator accordlng to the invention comprising two combustion chambers and a vaporizing chamber.

Fig. 2 is an axial section of a simplified gas generator comprising two combustion chambers, the last chamber also serving as a vaporizing chamber.

Figs. 3, 4 and 5 are modifications of this simplified construction.

As shown in Fig. 1, the said generator comprises a strong casing 1 which is divided into three chambers 234 by the partitions 56, these being each provided with a central aperture for gas circulation. The comburant is admitted at 7 into the chamber 2, and is subdivided by a distributing device, for instance a perforated concave member 8 situated at the upper part of the said chamher; the comb prant is burned for the major part in the in with the fuel which is injected by means of a sprayer '9 of suitable construction.

In this apparatus, the combustion chamber 2 is bounded by a thin wall 10 which extends throughout its whole length and terminates in the form of a nozzle 11 disposed in the central aperture of the partition 5. The annular space 12 between the wall 10 and the be no damage erior of the latter in contact casing 1 communicates by the small orifices .thus prepared will enter the nozzle 11 through the small orifices 16 formed on its periphery, and thus mingles with the gases discharged from the chamber 2. at a point at which the gas stream has a reduced cross section. Due to these conditions, the gases and vapours will be properly stirred up and mixed, and this assures the combustion of the last parts of the comburant in the supplementary combustion chamber 3. It should be noted that when issuing from the nozzle 11, the gases will have a much lar er flow section in the chamber 3, so that thelr speed will be reduced, with the formation of whirls which further the complete combustion of the comburent.

The chamber 3 is bounded by the thin wall 17, terminated by a nozzle 20 which is situated in the central opening of the partition 6 and which forms around the said chamber an annular space 18, connected through the orifices 22 with the annular channel 21 which is supplied with a cooling liquid by the pipe 7 23; the space 18 is connected with the nozzle 20 by the small orifices 24. The cooling liquid passing through the space 18 becomes heated and vaporized, (it may also be decomposed) and is injected through the orifices 24 into the stream of gas discharged from the chamber 3; it is thus completely vaporized or decomposed, and is mixed in the chamber 4 with the products of the combustion and lowers their temperature before they are supplied to the engine through the discharge orifice 25.

The narrowing of the chambers 2 and 3 at the bottom affords an advantage, since these parts form an obstacle to the streams of the reacting bodies and these latter are more effectively stirred up.

Although the parts of the wall or 17 converging towards the nozzle 11 or are directly in contact with the "flame, they will efi'ectively resist the destructive action of the latter, since they are thin and are well cooled by contact with the liquid and vapours circulating through the annular space 12 or 18.

The cooling liquid is injected into the gases of combustion solely at a point at which the whole of the comburant is already burned, so that there will be no danger of improperly arresting the combustion by this supply of liquid, as may occur in the known generators in which a cooling liquid is supplied to the combustion chamber at a point at which the combustion commences or is still very incomplete, and the fact that water is usually employed as the cooling liquid tends to make this occurrence more frequent.

With my said generator, water may be utilized without any premature stopping of the combustion nor will there be any ignition of the gas in the pipes; however it may be advantageous to substitute for the water a cooling liquid which is itself a combustible, such as petrol, gasoline, alcohol or the like, or a liquid having thermo-dynamic or thermochemical properties of such nature that for a given amount of heat used to vaporize it, there will be obtained a weight of the vaporized body which will supply a greater amount of energy than water will produce, when expanding between given pressures, if a turbine is used, or between given volumes, for reciprocating engines. This is the case for example with ethyl alcohol.

To increase the energy supplied, it may be useful to more or less heat the liquid to be vaporized before it is admitted to the generator, so as to decompose it into substances which will afford a better output.

For instance in the case in which the said liquid is ethyl alcohol, the following decomposition may be obtained by the use of a suitable temperature:

C H O Hz CH4 Although this reaction absorbs heat, it will finally produce a greater number of gaseous molecules at a determined temperature and pressure. which is chiefly favourable for the supply of a reciprocating engine.

It might be supposed that this preliminary preparation of the cooling liquid is of no use, considering that this decomposition takes place when the liquid to be vaporized meets with the hot gases.

This however is not true. The use of catalysts is often indispensable. Even should the heat act alone. the operator is not able, when making injections into the gas, to regulate the temperature supported by the injected liquid, and decompositions of quite another kind which are less favourable to the efliciency may take place.

Fig. 2 shows a simplified construction which differs from Fig. 1 by the elimination of the chamber 3, the wall 17 and the pipe 23. Herein I employ only an additional supply of fuel wh ch is delivered through the orifices 16 into the nozzlell and which completes the combustion of the last parts of the comburant in the chamber 4. I thus inject a considerable amount of fuel, so that the gases dis charged from the generator will be properly 1 cooled.

This simplified apparatus may prove satisfactory, if its size, shape and supply are properly determined. The ignition 1n the first chamber 2 will always take place, since the proportion of fuel is not excessive, and the completion of the combustion will be practicall assured by the fact that the temperature of t e comburant meeting with the fuel and completing the combustion of the fuel and cooling the latter, is sufiiciently high.

The amount of comburant which should be burned in each of the combustion chambers to obtain the optimum result will be shown by experiment.

In the present invention, I am thus enabled in all cases to obtain the advantages offered by the complete combustion of the comburant and those resulting from the use of a single liquid, which advantages consist in a great simplifying of the arrangement, so that the apparatus will be lightened, and other advantages are afforded.

In the various constructions herein specified the stirring or mixing of the fuel with the gases issuing from the first combustion chamber results from the disposition of the small orifices 16 around the nozzle 11 and from the subsequent enlarging. I may obviously employ for the same purpose any other suitable means for subdividing and deflecting the streams. and these can be properly deflected by the use of thin walls which are suitably cooled.

As shown in Fig. 3, the wall 10 of the combustion chamber forms a restricted part 26 which separates th s chamber from the next; the hollow ring 27 is held in the said restricted part by various tubes 26 for the circulation of the vaporized or decomposed fuel issuing from the annular space 12; this fuel is discharged into the products of combustion leaving the chamber 2, through the small orifices 29-30 in the wall of the ring 27.

The modified apparatus shown in Fig. 4 differs from the preceding from the fact that the ring 27 is replaced by a hollow device 31 of a somewhat conical shape, provided with the small orifices 2930 for discharging the combustible into the annular stream of gas which flows from the chamber 2 into the following chamber.

Fig. 5 shows another construction in which the wall of the combustion chamber consists of a tube 32 which is wound in a spiral worm with the spiral turns in close contact, the outline of this wall resembling that of the wall 10 (Figs. 1 or 2). The fuel supplied to this worm is vaporized or is decomposed more or less completely and issues through i a set of small orifices 34 in the last turns, and is thus discharged into the restricted part of the stream of gas leaving the com bustion chamber.

From these examples it will be observed that the forms of construction of the several parts of the generator may vary considerably without any change in the essential features of the invention. It should be further noted that the appended drawings are of a diagrammatic character, and for instance they do not represent the ignition device which forms part of all gas generators of this class and is known per se.

Having thus described my apparatus, what I claim as new therein, and my own invention, is:

1. In a pressure fluid generator adapted to be supplied with a liquid fuel and a gaseous comburant, the combination of a receptacle with resisting wall and divided by means of partitions into three successive compartments, a hollow body with a thin wall in the two first compartments and adapted to provide between itself and the wall of the receptacle an annular space, the said hollow body being provided with an outlet nozzle which opens into the following compartment through the respective partition, and the said nozzle having in its wall orifices for causing the annular space to communicate with the interior of the said nozzle, means for injecting the whole of the comburant and part of the liquid fuel into the hollow body of the first compartment, andmeans for introducing the rest of the fuel into the annular space around the first hollow body, and for introducing a cooling liquid around the last hollow body, the said liquids being adapted to become heated in the said annular spaces and to cool the said hollow bodies.

2. In a pressure fluid generator adapted to be supplied with a liquid fuel and a gaseous comburant, the combination of a receptacle with a resisting wall and divided by means of partition into two successive comartmeuts, a hollow body with a thin wall 1n the first compartment and adapted to provide between itself and the wall of the receptacle an annular space, the said hollow body being provided with an outlet nozzle which opens into the second compartment through the respective partition, and the said nozzle having in its wall orifices which cause the annular space to communicate with the interior of the said nozzle, means for injecting the whole of the comburant and part of the fuel into the hollow body of the first compartment and means for introducing the fix m signature. 7


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2453378 *Jul 7, 1943Nov 9, 1948Asiatic Petroleum Co LtdLiquid-cooled nozzle arrangement for combustion chambers of jet propulsion apparatus
US2456402 *Oct 20, 1942Dec 14, 1948Daniel And Florence GuggenheimCombustion chamber and means for supplying plural liquid fuels thereto
US2500925 *Mar 13, 1943Mar 21, 1950Claude A BonvillianApparatus for the combustion of fuel
US2510572 *Mar 22, 1947Jun 6, 1950Esther C GoddardMixing partition for combustion chambers
US2523656 *Nov 1, 1947Sep 26, 1950Daniel And Florence GuggenheimCombustion apparatus comprising successive combustion chambers
US2569446 *Oct 18, 1943Oct 2, 1951Claude A BonvillianApparatus for the combustion of fuel, including a tubular walled combustion chamber
US2697910 *Jul 29, 1950Dec 28, 1954Thermal Res And Engineering CoFluid fuel burner with self-contained fuel vaporizing unit
US2728192 *Jun 20, 1945Dec 27, 1955Aerojet General CoCombustion chamber for gas generation provided with cooling means and a system for operating the same
US2734578 *Feb 14, 1952Feb 14, 1956 Walter
US2781637 *Dec 15, 1950Feb 19, 1957Gen Motors CorpCombustion chamber with fuel vaporizer
US2836036 *Oct 27, 1953May 27, 1958Star CoFuel feeding and ignition means for pulse jet type hot gas or steam generator
US2934410 *Jun 21, 1955Apr 26, 1960Union Carbide CorpTwo-stage burner apparatus
US2952122 *Apr 29, 1955Sep 13, 1960Phillips Petroleum CoFuel system for ducted rocket ramjet power plants
US2958189 *May 31, 1955Nov 1, 1960Phillips Petroleum CoMethod and apparatus for providing improved combustion in jet engines
US2975746 *Dec 23, 1957Mar 21, 1961Thompson Ramo Wooldridge IncPropulsion system
US2991617 *Dec 1, 1950Jul 11, 1961Gen ElectricJet motor combustion chamber
US3067594 *May 11, 1959Dec 11, 1962Catacycle CompanyCooling with endothermic chemical reactions
US3078666 *Aug 25, 1959Feb 26, 1963Meir LevyMethod and apparatus for the combustion of fuel
US3101593 *Jul 27, 1960Aug 27, 1963Phillips Petroleum CoMethod and apparatus for providing improved combustion in jet engines
US3182554 *Jan 17, 1964May 11, 1965Barakauskas Edward JMissile ejection method and apparatus
US3262272 *Jan 17, 1964Jul 26, 1966Barakauskas Edward JMethod of ejecting a missile from a launching tube
US3267986 *Jun 4, 1965Aug 23, 1966Borje Olsson KarlApparatus for pulsating combustion
US3298278 *Apr 15, 1965Jan 17, 1967Barakauskas Edward JStandpipe for underwater launching system
US3357186 *Oct 6, 1964Dec 12, 1967Multer Robert KHigh energy propulsion method using aluminum and water
US3886733 *Aug 24, 1973Jun 3, 1975Nrg IncPneumatic energy source utilizing liquid oxygen
US4010607 *Jan 2, 1973Mar 8, 1977Hopping Alvin SInternal combustion engine with afterburner, venturi cooler and exhaust turbine
US4448577 *Jan 29, 1982May 15, 1984Glowny Instytut GornictwaDevice for production of inert gases
US4899538 *Nov 20, 1987Feb 13, 1990Sundstrand CorporationHot gas generator
US4955202 *Mar 12, 1989Sep 11, 1990Sundstrand CorporationHot gas generator
US4974415 *Nov 17, 1988Dec 4, 1990Sundstrand CorporationStaged, coaxial multiple point fuel injection in a hot gas generator
US5088287 *Jul 13, 1989Feb 18, 1992Sundstrand CorporationCombustor for a turbine
US5092128 *Dec 22, 1989Mar 3, 1992Sundstrand CorporationStored energy combustor
US5307636 *Jan 10, 1992May 3, 1994Sundstrand CorporationStaged, coaxial, multiple point fuel injection in a hot gas generator having a sufficiently wide cone angle
US5408825 *Dec 3, 1993Apr 25, 1995Westinghouse Electric CorporationDual fuel gas turbine combustor
US5709077 *Aug 25, 1995Jan 20, 1998Clean Energy Systems, Inc.Reduce pollution hydrocarbon combustion gas generator
US5865030 *Feb 1, 1996Feb 2, 1999Mitsubishi Jukogyo Kabushiki KaishaGas turbine combustor with liquid fuel wall cooling
US6176075 *Dec 2, 1997Jan 23, 2001Arthur T. Griffin, Jr.Combustor cooling for gas turbine engines
US6523349Jun 19, 2001Feb 25, 2003Clean Energy Systems, Inc.Clean air engines for transportation and other power applications
US6598398May 21, 2002Jul 29, 2003Clean Energy Systems, Inc.Hydrocarbon combustion power generation system with CO2 sequestration
US6622470May 14, 2001Sep 23, 2003Clean Energy Systems, Inc.Semi-closed brayton cycle gas turbine power systems
US6637183May 14, 2001Oct 28, 2003Clean Energy Systems, Inc.Semi-closed brayton cycle gas turbine power systems
US6824710May 14, 2001Nov 30, 2004Clean Energy Systems, Inc.Working fluid compositions for use in semi-closed brayton cycle gas turbine power systems
US6868677May 24, 2002Mar 22, 2005Clean Energy Systems, Inc.Combined fuel cell and fuel combustion power generation systems
US6910335Aug 22, 2003Jun 28, 2005Clean Energy Systems, Inc.Semi-closed Brayton cycle gas turbine power systems
US6945029Nov 17, 2003Sep 20, 2005Clean Energy Systems, Inc.Low pollution power generation system with ion transfer membrane air separation
US7021063Mar 10, 2004Apr 4, 2006Clean Energy Systems, Inc.Reheat heat exchanger power generation systems
US7043920Jul 8, 2003May 16, 2006Clean Energy Systems, Inc.Hydrocarbon combustion power generation system with CO2 sequestration
US7882692Apr 30, 2007Feb 8, 2011Clean Energy Systems, Inc.Zero emissions closed rankine cycle power system
CN103291269A *May 20, 2013Sep 11, 2013江苏大江石油科技有限公司Diesel type composite heat carrier generator system
CN103291269B *May 20, 2013Mar 9, 2016江苏大江石油科技有限公司柴油型复合热载体发生器系统
DE3838574A1 *Nov 14, 1988Jun 1, 1989Sundstrand CorpHeissgaserzeuger
WO1990011438A1 *Feb 7, 1990Oct 4, 1990Sundstrand Corporation, Inc.Hot gas generator
U.S. Classification60/39.59, 62/4, 60/730, 60/736, 114/20.2
International ClassificationF42B19/20, F42B19/00
Cooperative ClassificationF42B19/20
European ClassificationF42B19/20