US2536599A - Steam-operated rotating combustion chamber - Google Patents

Steam-operated rotating combustion chamber Download PDF

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Publication number
US2536599A
US2536599A US79A US7948A US2536599A US 2536599 A US2536599 A US 2536599A US 79 A US79 A US 79A US 7948 A US7948 A US 7948A US 2536599 A US2536599 A US 2536599A
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Prior art keywords
combustion chamber
chamber
steam
combustion
jacket
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US79A
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Esther C Goddard
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DANIEL AND FLORENCE GUGGENHEIM
DANIEL AND FLORENCE GUGGENHEIM FOUNDATION
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DANIEL AND FLORENCE GUGGENHEIM
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Priority to US79A priority Critical patent/US2536599A/en
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60Constructional parts; Details not otherwise provided for
    • F02K9/62Combustion or thrust chambers
    • F02K9/66Combustion or thrust chambers of the rotary type
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S60/00Power plants
    • Y10S60/915Collection of goddard patents

Definitions

  • This invention relates to rotating combustion chambers as used in rockets vand rocket craft and in which a blast of combustion gases is discharged through a rearwardly projecting nozzle.
  • FIG. 1 is a sectional side elevation of a rotating combustion chamber embodying this invention
  • Fig. 2 is a partial transverse sectional elevation, taken along the line 2-2 in Fig. 1;
  • Fig. 3 is a detail perspective view of certain parts to be described.
  • a rotating combustion chamber C which comprises oppositely facing chamber walls l and
  • the wall I0 may be supported on an ignition device
  • the chamber Wall is connected into a tapered discharge nozzle N.
  • a casing encloses a portion of the chamber wall Ill and provides a jacket space S to which gasoline may be supplied through a nozzle 22.
  • casing 24 encloses a portion ofthe vchamber wall .-I'l and provides a jacket space S' to which liquid oxygen may be supplied throughv a nozzle 26.
  • are separated by an annular partition 32 and provide jacket spaces S2 and S3 which may be supplied with cooling water through nozzles 35 and 36.
  • may be reenforced by a criss-cross winding of piano wire as indicated at 54, and a bearing 38 supports the outer casing 3
  • , 42 and 43 are provided in the jacket spaces S, S', S2 and S3 and l are effective in holding the chamber walls I0 and the jacket casings 20 and 24, andthe outer casing members 30 and 3
  • , 42 and 43 are preferably curved forward in the direction of rotation as indicated in Fig. 3, so that injected liquids will be more quickly and easily picked up and directed outward by centrifugal force in the jacket space portions between adjacent partitions.
  • a plurality of reaction nozzles (Figs. 1 and 2) are mounted in a circumferential series about the outer casing members 3
  • Gasoline from the space S is sprayed into the combustion chamber C through spray openings 60, and liquid oxygen from the space S' is similarly sprayed into the chamber C through spray openings 6
  • are preferably more numerous than the spray openings 60, and the oxygen sprays are directed away from the nozzle N.
  • the mixed combustion liquids and vapors will thus be directed toward and ignited by the igniter I2, and the combustiongases Will be discharged through the nozzle N as is usual in rocket propulsion.
  • the cooling water in the spaces S2 and S3 is forced outward by centrifugal force and becomes highly heated from the hot combustion gases in the chamber C.
  • Mixed Water and steam is then discharged into the outerperipheral portion of the chamber C through port openings 65 and 66, where it is immediately turned .to highly heated steam which escapes through the ports 52- Ato the nozzles 50.
  • a mixture of steamand'combustion gasesy then escapes to the atmosphere through chamber without the application of external power.
  • a rotating combustion chamber unit of high efficiency and unusual simplicity is thus achieved.
  • jacket means to cool the Wall of saidcombustion chamber, means to discharge a cooling liquid from the peripheral portion of said jacket means to the peripheral portion of said combustion chamber, a
  • combustion apparatus comprising a rotating combustion chamber of generally bulbous form and having a rearwardly-directed discharge nozzle and means to feed fuel and oxidizer to said combustion chamber, in combination, a Jacket for said combustion chamber, means to supply a cooling liquid to said jacket adjacent the axis of said combustion chamber, partition means providing radial jacket spaces in which said liquid is forced outward by centrifugal force, means to spray said liquid into the peripheral portion of said combustion chamber, a plurality of chamber-rotating nozzles mounted on said rotating chamber, and communicating connections from the peripheral portion of said chamber .to

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Description

Jan. 2, 1951 R. H. GODDARD STEAM-OPERATED ROTATING coMBusTloN CHAMBER Filed Jan. 2, 1948 INVENTOR. jPozijijoddmd, Dead 5775,63 060mm iran-35X ATTORNEYS UNITED l STATES 7 OFFICE STEAM-OPERATEDROTATING COMBUSTIONCHAMBER Robert H. ,'Goddard, deceased, ,late of Annapolis, Md., by Esther IC. Goddard, execlitrix, Worcester, Mass., assigner of one-half toThe Daniel and Florence Guggenheim Foundation, New York, N. Y., a corporation of New York Application January 2, 1948, Serial No. 79
(Cl. fio-35.6)
2 claims. l
This invention relates to rotating combustion chambers as used in rockets vand rocket craft and in which a blast of combustion gases is discharged through a rearwardly projecting nozzle.
It is one object of the present invention to l provide improved means for rotating the comand combinations of parts which will be hereinafter described and more particularly pointed out in the appended claims.
A preferred form of the invention is shown in the drawing, in which Fig. 1 is a sectional side elevation of a rotating combustion chamber embodying this invention;
Fig. 2 is a partial transverse sectional elevation, taken along the line 2-2 in Fig. 1; and
Fig. 3 is a detail perspective view of certain parts to be described.
Referring to the drawing, a rotating combustion chamber C is shown which comprises oppositely facing chamber walls l and The wall I0 may be supported on an ignition device |2, which in turn is rotatably mounted in a supporting thrust bearing |4. The chamber Wall is connected into a tapered discharge nozzle N.
A casing encloses a portion of the chamber wall Ill and provides a jacket space S to which gasoline may be supplied through a nozzle 22. A
casing 24 encloses a portion ofthe vchamber wall .-I'l and provides a jacket space S' to which liquid oxygen may be supplied throughv a nozzle 26.
Outer casing members and 3| are separated by an annular partition 32 and provide jacket spaces S2 and S3 which may be supplied with cooling water through nozzles 35 and 36. The outer casing members 30 and 3| may be reenforced by a criss-cross winding of piano wire as indicated at 54, and a bearing 38 supports the outer casing 3|.
Radiating partitions 40, 4|, 42 and 43 are provided in the jacket spaces S, S', S2 and S3 and l are effective in holding the chamber walls I0 and the jacket casings 20 and 24, andthe outer casing members 30 and 3| all in definite spaced relation.
The inner ends of the partitions or vanes 40, 4 I,
, 42 and 43 are preferably curved forward in the direction of rotation as indicated in Fig. 3, so that injected liquids will be more quickly and easily picked up and directed outward by centrifugal force in the jacket space portions between adjacent partitions.
2 A plurality of reaction nozzles (Figs. 1 and 2) are mounted in a circumferential series about the outer casing members 3|) and 3| of the rotating combustion chamber C and communicate with the chamber through ports or openings 52.
Gasoline from the space S is sprayed into the combustion chamber C through spray openings 60, and liquid oxygen from the space S' is similarly sprayed into the chamber C through spray openings 6|. As the mass of oxygen required for complete combustion is muchv larger than the mass of gasoline, the spray openings 6| are preferably more numerous than the spray openings 60, and the oxygen sprays are directed away from the nozzle N.
The mixed combustion liquids and vapors will thus be directed toward and ignited by the igniter I2, and the combustiongases Will be discharged through the nozzle N as is usual in rocket propulsion.
The cooling water in the spaces S2 and S3 is forced outward by centrifugal force and becomes highly heated from the hot combustion gases in the chamber C. Mixed Water and steam is then discharged into the outerperipheral portion of the chamber C through port openings 65 and 66, where it is immediately turned .to highly heated steam which escapes through the ports 52- Ato the nozzles 50. A mixture of steamand'combustion gasesy then escapes to the atmosphere through chamber without the application of external power. A rotating combustion chamber unit of high efficiency and unusual simplicity is thus achieved.
Having thus described the invention andthe advantages thereof, it will be understood that the invention is not to be limited to the details herein disclosed, otherwise than as set forth inl the claims, but what is claimed is:
l. In combustion apparatus comprising a rotating combustion chamber of generally bulbous form and a rearwardly-directed discharge nozzle and means to feed fuel and oxidizer to said combustion chamber, in combination, jacket means to cool the Wall of saidcombustion chamber, means to discharge a cooling liquid from the peripheral portion of said jacket means to the peripheral portion of said combustion chamber, a
plurality of chamber-rotating nozzles mounted on said combustion chamber, and means to discharge a mixture of steam and combustion gases from the peripheral portion of said combustion chamber to said latter nozzles, said nozzles traversing the Jacket means, and the outer end portions of said nozzles constituting substantially elongated cones which discharge tangentially to the periphery or said combustion chamber at its point of largest diameter.
2. In combustion apparatus comprising a rotating combustion chamber of generally bulbous form and having a rearwardly-directed discharge nozzle and means to feed fuel and oxidizer to said combustion chamber, in combination, a Jacket for said combustion chamber, means to supply a cooling liquid to said jacket adjacent the axis of said combustion chamber, partition means providing radial jacket spaces in which said liquid is forced outward by centrifugal force, means to spray said liquid into the peripheral portion of said combustion chamber, a plurality of chamber-rotating nozzles mounted on said rotating chamber, and communicating connections from the peripheral portion of said chamber .to
REFERENCES man The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 1,677.198 Naileigh July 17, 1928 1,945,608 Hill Feb. 8, 1934 FOREIGN PATENTS Number Country Date 2,497 Great Britain Nov. 8. 1858 OTHER REFERENCES Journal of the Aeronautical Sciences. issued June 1936, page 289, The Design of a Stratosphere Rocket," by Alfred Africano.
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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2923348A (en) * 1950-10-17 1960-02-02 Reginald P Fraser Fuel combustion apparatus
US2927632A (en) * 1955-02-09 1960-03-08 Fraser Reginald Percy Fuel combustion apparatus and the production of controlled gaseous effluents therefrom
US2989380A (en) * 1953-11-24 1961-06-20 Exxon Research Engineering Co Apparatus for carrying out chemical reactions
US3886732A (en) * 1973-09-27 1975-06-03 Joseph Gamell Ind Inc Internal combustion engine having coaxially mounted compressor combustion chamber, and turbine
US4031697A (en) * 1976-04-18 1977-06-28 Joseph Bryan Adair Combination steam-gas generator engine
US5457954A (en) * 1993-12-21 1995-10-17 Solar Turbines Inc Rolling contact mounting arrangement for a ceramic combustor
WO2000071880A2 (en) * 1999-05-14 2000-11-30 Bowery James A Simplified high-efficiency propulsion system
US20040154281A1 (en) * 2003-02-10 2004-08-12 Feodor Koudinov Concept design of heat engines combustion chamber configuration in the earth atmosphere and airless conditions
US20050241315A1 (en) * 2001-08-20 2005-11-03 Andrew Schlote Rotary heat engine
US20070151226A1 (en) * 2006-01-03 2007-07-05 Innovative Energy, Inc. Rotary heat engine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1677198A (en) * 1926-09-27 1928-07-17 Naileigh Ellis Wood Internal-combustion turbine
US1945608A (en) * 1931-11-06 1934-02-06 Hulda Nordstrom Constant pressure reaction gas turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1677198A (en) * 1926-09-27 1928-07-17 Naileigh Ellis Wood Internal-combustion turbine
US1945608A (en) * 1931-11-06 1934-02-06 Hulda Nordstrom Constant pressure reaction gas turbine

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2923348A (en) * 1950-10-17 1960-02-02 Reginald P Fraser Fuel combustion apparatus
US2989380A (en) * 1953-11-24 1961-06-20 Exxon Research Engineering Co Apparatus for carrying out chemical reactions
US2927632A (en) * 1955-02-09 1960-03-08 Fraser Reginald Percy Fuel combustion apparatus and the production of controlled gaseous effluents therefrom
US3886732A (en) * 1973-09-27 1975-06-03 Joseph Gamell Ind Inc Internal combustion engine having coaxially mounted compressor combustion chamber, and turbine
US4031697A (en) * 1976-04-18 1977-06-28 Joseph Bryan Adair Combination steam-gas generator engine
US5457954A (en) * 1993-12-21 1995-10-17 Solar Turbines Inc Rolling contact mounting arrangement for a ceramic combustor
WO2000071880A2 (en) * 1999-05-14 2000-11-30 Bowery James A Simplified high-efficiency propulsion system
WO2000071880A3 (en) * 1999-05-14 2001-01-18 James A Bowery Simplified high-efficiency propulsion system
US6212876B1 (en) * 1999-05-14 2001-04-10 Roger Everett Gregory Simplified high-efficiency propulsion system
US20050241315A1 (en) * 2001-08-20 2005-11-03 Andrew Schlote Rotary heat engine
US6996971B2 (en) * 2001-08-20 2006-02-14 Innovative Energy, Inc. Rotary heat engine
US20040154281A1 (en) * 2003-02-10 2004-08-12 Feodor Koudinov Concept design of heat engines combustion chamber configuration in the earth atmosphere and airless conditions
US20070151226A1 (en) * 2006-01-03 2007-07-05 Innovative Energy, Inc. Rotary heat engine
US7708522B2 (en) 2006-01-03 2010-05-04 Innovative Energy, Inc. Rotary heat engine

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