US2523655A - Rotating combustion chamber - Google Patents

Rotating combustion chamber Download PDF

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Publication number
US2523655A
US2523655A US686387A US68638746A US2523655A US 2523655 A US2523655 A US 2523655A US 686387 A US686387 A US 686387A US 68638746 A US68638746 A US 68638746A US 2523655 A US2523655 A US 2523655A
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United States
Prior art keywords
combustion chamber
chamber
nozzles
gases
rotating
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Expired - Lifetime
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US686387A
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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 US686387A priority Critical patent/US2523655A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/88—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/66—Combustion or thrust chambers of the rotary type
    • 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

  • This invention relates to a rotating combustion chamber adapted for use in the propulsion of rockets or rocket craft.
  • the invention relatesmore specificall to the type of rdtating combustion chamber in which a portion of the combustion gases are discharged through aseries of small auxiliary nozzles arranged tangentially about the peripherybf the combustion chamber and providing power to rotate said chamber.
  • FIG. 1 is a perspective view of a combustion chamber having this invention applied thereto;
  • Fig. 2 is a perspective view of the gas-diverting structure
  • Fig. 3 is a sectional plan view, taken along the irregular section line 33 in Fig. 2;
  • Fig. 4 is a transverse sectional view, taken in the plane of the line 4-4 in Fig. 2;
  • Fig. 5 is a partial perspective view of a modiiied construction.
  • a combustion chamber C is provided with an axial discharge nozzle N and is mounted to rotate in bearings B and B about the axis of a supporting shaft S.
  • the chamber C is provided with a plurality of small auxiliary nozzles i0 rotating therewith.
  • the nozzles ID are mounted about the periphery of the chamber C near the discharge end thereof and are inclined with respect to the periphery to producerotation of the combustion chamber in the direction of the arrow a.
  • Such rotation may be utilized to drive fuel feed pumps for the combustion chamber or other devices associated with the rotating shaft S.
  • the rotation of the combustion chamber also acts to cool the cylindrical chamber wall which is necessarily made very thin to save weight when used in rocket craft.
  • the rate of travel of the portion of combustion gases discharged through the auxiliary nozzles N is very much greater than the peripheral-speed of rotation of the chamber C, and the substantial momentum of these discharged gases would be lost if no provision were made for changing the direction of travel of these gases.
  • annular casing 20 is mounted in fixed position concentric with the rotating combustion chamber C and loosely surrounding the chamber.
  • the member 20 is of U-shaped cross section with an open inner side, as shown in Fig. 1, and is positioned to provide clearance for the nozzles III, which discharge into the member '20 and in a substantially tangential direction opposite to the direction of rotation of the chamber.
  • Rearwardly directed discharge tubes 22 are mounted on the member 20 at diametrically opposite points and at each side of the discharge nozzle N.
  • a curved deflecting vane 25 extends inward from one side face of each tube 22 and has its curved end portion abutting and secured to the opposite side of the member 20.
  • the vanes 25 have fairly close clearance with respect to the nozzles in but the nozzles move at a smaller radius which avoids interference of the nozzles with the vanes.
  • each deflecting vane 44 i given a warped surface and is curved in two directions, so that the gases are given a combined outward and rearward deflection into the tubes 42.
  • This construction tends to reduce any tendency of the gases to escape through the annular openings between the inner edges of the annular member 40 and. the outer surface of the rotating chamber C.
  • a rotating combustion chamber having a main axial discharge nozzle. a plurality of auxiliary nozzles mounted adjacent the discharge end of said chamber and discharging substantially tangentially from the periphery thereof to rotate said chamber, and stationary means to divert the gases tangentially-discharged from saidauxiliary nozzles rearward to aid propulsion.
  • a rotating combustion chamber having a main axial discharge nozzle, a plurality of auxiliary nozzles mounted adjacent the discharge end of said chamber and dlscharging'substantially tangentially from the. periphery thereoi to rotate said chamber, a fixed annular casing enclosing said auxiliary nozzles, and rearwardly directed discharge tubes mounted on and secured to said annular casing.
  • a rotating combustion chamber having a main axial discharge nozzle, means to discharge a portion of the combustion gases from said chamber tangentially to produce rotation of said chamber, and means to deflect said portion of gasesrearwardiy to aid propulsion, said latter means being fixed in said apparatus and including a gas-collecting member and rearwardiy directed discharge tubes mounted on and secured to said member.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Description

p 1950 R. H. GODDARD 2,523,655
ROTATING COMBUSTION CHAMBER Filed July 26, 1946 INV TOR. M g tgg aswigw MM- "/7 MAW Patented Sept. 26, 1950 Robert H. Goddard, deceased, late ofAnnapolis, Md., by Esther C. Goddard, executrix, Paxton, Mass, assignor of one-half to The Daniel and Florence Guggenheim Foundation, New York, N. Y., a corporation of New York Applicationylnly as, 1940, Serial No. 686,887
(01. Gil-35.6)
9 Claims. 1
This invention relates to a rotating combustion chamber adapted for use in the propulsion of rockets or rocket craft. The invention relatesmore specificall to the type of rdtating combustion chamber in which a portion of the combustion gases are discharged through aseries of small auxiliary nozzles arranged tangentially about the peripherybf the combustion chamber and providing power to rotate said chamber.
These gases as they leave the auxiliary nozzles are travelling very much faster than the peripheral speed of the combustion chamber and they possess a substantial amount of momentum.
It is the general object of the present invention to provide means to conserve the power in these rapidly moving gases by diverting and redirecting the gases so that they are discharged axially rearward and thus aid propulsion.
The invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the appended claims.
Preferred forms of the invention are shown in the drawing, in which Fig. 1 is a perspective view of a combustion chamber having this invention applied thereto;
Fig. 2 is a perspective view of the gas-diverting structure;
Fig. 3 is a sectional plan view, taken along the irregular section line 33 in Fig. 2;
Fig. 4 is a transverse sectional view, taken in the plane of the line 4-4 in Fig. 2; and
Fig. 5 is a partial perspective view of a modiiied construction.
Referring to the drawing, a combustion chamber C is provided with an axial discharge nozzle N and is mounted to rotate in bearings B and B about the axis of a supporting shaft S.
The chamber C is provided with a plurality of small auxiliary nozzles i0 rotating therewith. The nozzles ID are mounted about the periphery of the chamber C near the discharge end thereof and are inclined with respect to the periphery to producerotation of the combustion chamber in the direction of the arrow a. Such rotation may be utilized to drive fuel feed pumps for the combustion chamber or other devices associated with the rotating shaft S. The rotation of the combustion chamber also acts to cool the cylindrical chamber wall which is necessarily made very thin to save weight when used in rocket craft.
As has been previously stated, the rate of travel of the portion of combustion gases discharged through the auxiliary nozzles N is very much greater than the peripheral-speed of rotation of the chamber C, and the substantial momentum of these discharged gases would be lost if no provision were made for changing the direction of travel of these gases.
For the purpose of producing such changes in direction, an annular casing 20 is mounted in fixed position concentric with the rotating combustion chamber C and loosely surrounding the chamber. The member 20 is of U-shaped cross section with an open inner side, as shown in Fig. 1, and is positioned to provide clearance for the nozzles III, which discharge into the member '20 and in a substantially tangential direction opposite to the direction of rotation of the chamber.
Rearwardly directed discharge tubes 22 are mounted on the member 20 at diametrically opposite points and at each side of the discharge nozzle N. A curved deflecting vane 25 extends inward from one side face of each tube 22 and has its curved end portion abutting and secured to the opposite side of the member 20. The vanes 25 have fairly close clearance with respect to the nozzles in but the nozzles move at a smaller radius which avoids interference of the nozzles with the vanes.
As the combustion chamber C is rotated and the combustion gases are discharged from the nozzles l0, they enter the U-shaped annular member 20 and travel around the annular passage within said member until they are deflected by the vanes 25 which cause them to be diverted and discharged axially rearward through the associated tubes 22. The momentum of the gases is thus conserved and acts with the gases discharged through the main nozzle N to increase the propulsive effect. Water may be injected through supply nozzles 30 for cooling the annular member 20.
In the construction shown in Fig. 5, the annular member 40 and discharge tubes 2 are as previously described, but each deflecting vane 44 i given a warped surface and is curved in two directions, so that the gases are given a combined outward and rearward deflection into the tubes 42. This construction tends to reduce any tendency of the gases to escape through the annular openings between the inner edges of the annular member 40 and. the outer surface of the rotating chamber C.
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 claims, but what is claimed is:
1. In aerial propulsion apparatus, a rotating combustion chamber having a main axial discharge nozzle. a plurality of auxiliary nozzles mounted adjacent the discharge end of said chamber and discharging substantially tangentially from the periphery thereof to rotate said chamber, and stationary means to divert the gases tangentially-discharged from saidauxiliary nozzles rearward to aid propulsion.
2. In aerial propulsion apparatus, a rotating combustion chamber having a main axial discharge nozzle, a plurality of auxiliary nozzles mounted adjacent the discharge end of said chamber and dlscharging'substantially tangentially from the. periphery thereoi to rotate said chamber, a fixed annular casing enclosing said auxiliary nozzles, and rearwardly directed discharge tubes mounted on and secured to said annular casing.
3. The combination in aerial propulsion apparatus as set forth in claim 2, in which the annular casing is of U-shaped cross section and has an open inner side to clear said rotating nozzles.
4. The combination in aerial propulsion apparatus as set forth in claim 2, in which the annular casing is of U-shaped cross section and has an open inner side to clear said rotating nozzles, and in which a deflecting vane is provided in said annular casing adiacent each discharge tube.
5. The combination in aerial propulsion apparatus as set forth in claim 2, in which the annular casing is of U-shaped cross section and has an open inner side in clear said rotating nozzles, and in which a deflecting vane having a warped surface twisted outward and sideways is provided in said annular casing adjacent each discharge ube.
6. The combination in aerial propulsion apparatus as set forth in claim 2, in which means is provided to cool said annular casing.
'I. The combination in aerial propulsion apparatus as set forth in claim 2, in which fixed nozzles deliver a cooling liquid at spaced points into said annular casing.
8. In aerial propulsion apparatus, a rotating combustion chamber having a main axial discharge nozzle, means to discharge a portion of the combustion gases from said chamber tangentially to produce rotation of said chamber, and means to deflect said portion of gasesrearwardiy to aid propulsion, said latter means being fixed in said apparatus and including a gas-collecting member and rearwardiy directed discharge tubes mounted on and secured to said member.
9. The combination in aerial propulsion apparatus as set forth in claim 8, in which two discharge tubes are'mounted in a balanced pair.
ESTHER. C. GODDARD, Executria: ofthe Last Will and Testament of Robert H. Goddard, Deceased.
REFERENCES CITED The following references are of record in the die of this patent:
UNITED STATES PATENTS Number Name Date 2,395,114 Goddard Feb. 19, 1946 2,412,286 Hoagland Dec. 10, 1946
US686387A 1946-07-26 1946-07-26 Rotating combustion chamber Expired - Lifetime US2523655A (en)

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2709895A (en) * 1949-07-22 1955-06-07 Wadsworth W Mount Jet thrust burner power generator
US2709889A (en) * 1951-06-22 1955-06-07 Wadsworth W Mount Gas turbine using revolving ram jet burners
US3046736A (en) * 1958-02-10 1962-07-31 Thompson Ramo Wooldridge Inc Direction control for gelatin monopropellant rocket engine
US3107488A (en) * 1960-09-27 1963-10-22 Astrosyst Inc Rotating rocket motor
US5709076A (en) * 1992-09-14 1998-01-20 Lawlor; Shawn P. Method and apparatus for power generation using rotating ramjet which compresses inlet air and expands exhaust gas against stationary peripheral wall
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
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

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2395114A (en) * 1942-10-12 1946-02-19 Daniel And Florence Guggenheim Rotating combustion chamber for rocket apparatus
US2412266A (en) * 1944-02-22 1946-12-10 Reginald W Hoagland Reaction propelled device

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2395114A (en) * 1942-10-12 1946-02-19 Daniel And Florence Guggenheim Rotating combustion chamber for rocket apparatus
US2412266A (en) * 1944-02-22 1946-12-10 Reginald W Hoagland Reaction propelled device

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2709895A (en) * 1949-07-22 1955-06-07 Wadsworth W Mount Jet thrust burner power generator
US2709889A (en) * 1951-06-22 1955-06-07 Wadsworth W Mount Gas turbine using revolving ram jet burners
US3046736A (en) * 1958-02-10 1962-07-31 Thompson Ramo Wooldridge Inc Direction control for gelatin monopropellant rocket engine
US3107488A (en) * 1960-09-27 1963-10-22 Astrosyst Inc Rotating rocket motor
US5709076A (en) * 1992-09-14 1998-01-20 Lawlor; Shawn P. Method and apparatus for power generation using rotating ramjet which compresses inlet air and expands exhaust gas against stationary peripheral wall
US6347507B1 (en) 1992-09-14 2002-02-19 Ramgen Power Systems, Inc. Method and apparatus for power generation using rotating ramjets
US6298653B1 (en) 1996-12-16 2001-10-09 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6334299B1 (en) 1996-12-16 2002-01-01 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
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

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