US2544420A - Combustion chamber in rotating annular casing - Google Patents

Combustion chamber in rotating annular casing Download PDF

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Publication number
US2544420A
US2544420A US746615A US74661547A US2544420A US 2544420 A US2544420 A US 2544420A US 746615 A US746615 A US 746615A US 74661547 A US74661547 A US 74661547A US 2544420 A US2544420 A US 2544420A
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United States
Prior art keywords
casing
combustion chamber
annular casing
rotating annular
combustion chambers
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Expired - Lifetime
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US746615A
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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 US746615A priority Critical patent/US2544420A/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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S60/00—Power plants
    • Y10S60/915—Collection of goddard patents

Definitions

  • a plurality oi combustion chambers are disposed in a circumferential or annular series, and the longitudinal axis of each separate combustion chamber is curved along its circumferential path. Furthermore. all of the combustion chambers are enclosed in a single annular streamlined casing.
  • the invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed;
  • FIG. 1 is a transverse sectional view of a pair 01' the improved combustion chambers and their supporting structure;
  • Fig. 2 is an axial sectionof the chambers and the enclosing casing, taken along the line 2-2 in Fig. 1;
  • Fig. 3 is an enlarged cross section, taken along thelinei-linFighand
  • Fig. 4 is an enlarged cross section. taken along thelinel-linFigJ.
  • Propellers may be mounted directly on the shaft It, or power may be taken oflindirectly for any desired. purpose. For larger units, more combustion chambers may be added in series or in parallel.
  • the annular casing i0 is mounted on tubular arms 20 which enclose feed pipes 22 for the combustion mixture and which may also enclose pipes 24 through which wires or other control devices may be conducted to the combustion chambers.
  • the casing l0 preferably has the streamlined section shown in Figs. 2 and 3 and is well adapted to enclose the combustion chambers and to shield 2 the chambers and nozzles from the air stream produced by flight.
  • a streamlined casing sleeve 40 is desirably mounted on each arm 20 and is free to turn thereon. when in flight, these sleeves assume positions due to the combined eflect of rotationand of the air stream, and the positions thus automatically assumed are the positions of least air resistance.
  • combustion chambers may be effectively utilized directly for driving a propeller in'an aircraft. and the air resistance of the driving mechanism will be reduced to a minimum.
  • a rotatable shaft a coaxial hollow annular casing, means to support said casing for rotation with said shaft but substantially spaced outward therefrom, the leading portion of said casing being substantially semicircular in radial cross section and the remaining portion being rearwardly tapered for streamlining, a plurality of combustion chambers of circular cross section mounted in equally circumierentially spaced relation in the leading portion or saidannuiar casing and said chambers being curved longitudinally to correspond to the circumierential curvature of said annular casing.
  • said casing having spaced peripheral outer openings and said combustion chambers having rearward discharge nozzles entirely enclosed in said casing and angularly disposed with respect to the associated combustion chambers to iacihtate discharge irom said nozzles through said peripheral openings.

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

Description

March 6, 1951 Q R. H. GODDARD 2,544,420
COMBUSTION CHAMBER IN ROTATING CASING Filed May 7, 1947 NVENT 7 gm. W W
Patented Mar. 6, 1951 UNITED STATES PATENT OFFICE COMBUSTION CHAMBER m aorarmc ANNULAR CASING Robert H. Goddard, deceased, late of Annapolis,
Md., by Esther O. Goddard, executrix, Worcester, Mass., assignor of one-half to The Daniel and Florence Guggenheim Foundation, New York, N. Y., a corporation of New York Application May "I. 1947, Serial No. 746,615
1 Claim.
It is the general object of the present invention I to provide a construction by which air resistance in flight may be greatly reduced for such combustion chambers and by which air resistance from rotation may be correspondingly reduced.
To the attainment of these general objects, a plurality oi combustion chambers are disposed in a circumferential or annular series, and the longitudinal axis of each separate combustion chamber is curved along its circumferential path. Furthermore. all of the combustion chambers are enclosed in a single annular streamlined casing.
The invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed;
out in the appended claim.
A preferred form of the invention is shown in 4 the drawing. in which Fig. 1 is a transverse sectional view of a pair 01' the improved combustion chambers and their supporting structure;
Fig. 2 is an axial sectionof the chambers and the enclosing casing, taken along the line 2-2 in Fig. 1;
Fig. 3 is an enlarged cross section, taken along thelinei-linFighand Fig. 4 is an enlarged cross section. taken along thelinel-linFigJ.
' shaft is is thus attained.
Propellers may be mounted directly on the shaft It, or power may be taken oflindirectly for any desired. purpose. For larger units, more combustion chambers may be added in series or in parallel.
The annular casing i0 is mounted on tubular arms 20 which enclose feed pipes 22 for the combustion mixture and which may also enclose pipes 24 through which wires or other control devices may be conducted to the combustion chambers.
The casing l0 preferably has the streamlined section shown in Figs. 2 and 3 and is well adapted to enclose the combustion chambers and to shield 2 the chambers and nozzles from the air stream produced by flight.
In order to reduce the air resistance of the arms 20, a streamlined casing sleeve 40 is desirably mounted on each arm 20 and is free to turn thereon. when in flight, these sleeves assume positions due to the combined eflect of rotationand of the air stream, and the positions thus automatically assumed are the positions of least air resistance.
By the use of this invention, combustion chambers may be effectively utilized directly for driving a propeller in'an aircraft. and the air resistance of the driving mechanism will be reduced to a minimum.
Having thus described the invention and the advantages thereof, it will be understood that the invention is not to be limited to the details herein disclosed, otherwise than as set forth in the claim, but what isclaimed is:
I In propulsion apparatus, a rotatable shaft, a coaxial hollow annular casing, means to support said casing for rotation with said shaft but substantially spaced outward therefrom, the leading portion of said casing being substantially semicircular in radial cross section and the remaining portion being rearwardly tapered for streamlining, a plurality of combustion chambers of circular cross section mounted in equally circumierentially spaced relation in the leading portion or saidannuiar casing and said chambers being curved longitudinally to correspond to the circumierential curvature of said annular casing. said casing having spaced peripheral outer openings and said combustion chambers having rearward discharge nozzles entirely enclosed in said casing and angularly disposed with respect to the associated combustion chambers to iacihtate discharge irom said nozzles through said peripheral openings.
ESTHER C. GODDARD. Executria: of the Last Wm and Testament of Robert H. Goddard, Deceased.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 1,291,273 Tyler Jan. 14, 1919 2,220,066 Cornell, Jr. Nov. 5, 1940 2,281,203 Pitcairn Apr. 28, 1942 2,425,904 Vernon Aug. 19, 1947 FOREIGN PATENTS Number Country Date 3,561 Great Britain of 1881 13,019 Great Britain June 23, 1905
US746615A 1947-05-07 1947-05-07 Combustion chamber in rotating annular casing Expired - Lifetime US2544420A (en)

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2633701A (en) * 1951-05-28 1953-04-07 Urban A Moores Rotary ram jet propelled motor
US2743576A (en) * 1952-02-28 1956-05-01 Crockett Sydney Robert Propellant impelled turbine
US5408824A (en) * 1993-12-15 1995-04-25 Schlote; Andrew Rotary heat engine
US20030010013A1 (en) * 2001-07-10 2003-01-16 Duncan Johnstone Rotary impeller driven turbine
US6668539B2 (en) 2001-08-20 2003-12-30 Innovative Energy, Inc. Rotary heat engine
US20040020185A1 (en) * 2002-04-16 2004-02-05 Martin Brouillette Rotary ramjet engine
US20070151226A1 (en) * 2006-01-03 2007-07-05 Innovative Energy, Inc. Rotary heat engine
US20100307129A1 (en) * 2007-03-31 2010-12-09 Jiubin Chen Flywheel Engine
US8117824B1 (en) * 2009-02-04 2012-02-21 The United States of America as represented by the Secterary of the Navy Pollution free engine using hydrogen as a fuel
WO2012056470A2 (en) 2010-10-25 2012-05-03 Arvind Sharma Arvind Kumar Rotary three dimentional variable volume machine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB188103561A (en) * 1881-08-16
GB190513019A (en) * 1904-06-24 Rappaport Rosa Improvements in Gas Turbines.
US1291273A (en) * 1918-03-12 1919-01-14 Alva W Tyler Gas-turbine.
US2220066A (en) * 1938-07-27 1940-11-05 Jr Edward S Cornell Liquid fuel burner unit
US2281203A (en) * 1939-11-14 1942-04-28 Autogiro Co Of America Driving mechanism for air rotors, especially aircraft sustaining rotors
US2425904A (en) * 1941-11-29 1947-08-19 James B Vernon Turbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB188103561A (en) * 1881-08-16
GB190513019A (en) * 1904-06-24 Rappaport Rosa Improvements in Gas Turbines.
US1291273A (en) * 1918-03-12 1919-01-14 Alva W Tyler Gas-turbine.
US2220066A (en) * 1938-07-27 1940-11-05 Jr Edward S Cornell Liquid fuel burner unit
US2281203A (en) * 1939-11-14 1942-04-28 Autogiro Co Of America Driving mechanism for air rotors, especially aircraft sustaining rotors
US2425904A (en) * 1941-11-29 1947-08-19 James B Vernon Turbine

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2633701A (en) * 1951-05-28 1953-04-07 Urban A Moores Rotary ram jet propelled motor
US2743576A (en) * 1952-02-28 1956-05-01 Crockett Sydney Robert Propellant impelled turbine
US5408824A (en) * 1993-12-15 1995-04-25 Schlote; Andrew Rotary heat engine
US5560196A (en) * 1993-12-15 1996-10-01 Schlote; Andrew Rotary heat engine
US20030010013A1 (en) * 2001-07-10 2003-01-16 Duncan Johnstone Rotary impeller driven turbine
US6672048B2 (en) * 2001-07-10 2004-01-06 Duncan Johnstone Rotary impeller driven turbine
US20050241315A1 (en) * 2001-08-20 2005-11-03 Andrew Schlote Rotary heat engine
US6668539B2 (en) 2001-08-20 2003-12-30 Innovative Energy, Inc. Rotary heat engine
US6996971B2 (en) 2001-08-20 2006-02-14 Innovative Energy, Inc. Rotary heat engine
US20040020185A1 (en) * 2002-04-16 2004-02-05 Martin Brouillette Rotary ramjet engine
US7337606B2 (en) * 2002-04-16 2008-03-04 Universite De Sherbrooke Rotary ramjet engine
WO2004005684A1 (en) * 2002-07-10 2004-01-15 Duncan Johnstone Rotary impeller driven turbine
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
US20100307129A1 (en) * 2007-03-31 2010-12-09 Jiubin Chen Flywheel Engine
US8850791B2 (en) * 2007-03-31 2014-10-07 Jinan Metal Haber Metallurgical Technology Development Co., Ltd Flywheel engine
US8117824B1 (en) * 2009-02-04 2012-02-21 The United States of America as represented by the Secterary of the Navy Pollution free engine using hydrogen as a fuel
US8250850B2 (en) 2009-02-04 2012-08-28 The United States Of America, As Represented By The Secretary Of The Navy Engine using hydrogen as a fuel
WO2012056470A2 (en) 2010-10-25 2012-05-03 Arvind Sharma Arvind Kumar Rotary three dimentional variable volume machine

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