US2551111A - Revolving combustion chamber - Google Patents

Revolving combustion chamber Download PDF

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Publication number
US2551111A
US2551111A US680230A US68023046A US2551111A US 2551111 A US2551111 A US 2551111A US 680230 A US680230 A US 680230A US 68023046 A US68023046 A US 68023046A US 2551111 A US2551111 A US 2551111A
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Prior art keywords
chambers
shaft
combustion
air
jacket
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US680230A
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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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    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/005—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the engine comprising a rotor rotating under the actions of jets issuing from this rotor
    • 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
    • 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; aircraft propulsion mechanism in. which a propeller is rotated by a plurality of small combustion. chambers of rocket type which are mounted.v to revolve in; a. circular path about the. axis of the. propeller. and to supply power to rotate the propeller., i
  • the general object of the invention to provide; an. improved construction. in such propulsion mechanism, in which the revolving combus ⁇ tion. chambers will present a minimum. air resistance and will. most effectively apply power to turn the propel-ler.
  • a construction ⁇ in which the combustion. chambers are self-adjusting to air resistance and automatically' orient themselves to positions of minimum resistance. Means is also provided to prevent such automatic adjustment during the. starting up ⁇ of the apparatus, and also for disconnecting the propeller from the. revolving chambers so that the chambers may be started in operation and may b e brought up to the desired speed of revolution withminimum resistance.
  • FIG. 1 A preferred form of the invention is shownv in the drawing, i-nwhich Fig; lis a side elevation of the improved construction;
  • Fig. 2 ⁇ is anenlarged sectional side elevation of one combustion chamber
  • Fig. 3 is a transverse sectional view, taken along the line 3-3 in- Fig. 2.
  • a pair of combustion chambersA C are shown mounted on a shaft' S wl'iichy isj rotatable in suitable bearings inv an aircraftand which is aligned with a shaft Si' which is similarly mounted and which is provided with propeller blades P.
  • a clutch Lv is provided by whichv the propeller shaft S may beA connected or disconnected with respect to the shaft S by shifting a. handle lever H;
  • Liquid fuel for the combustion chamber may be fed rto the space 20 within the casing through a feed pipe 2
  • a second tubey 25 is mounted in spaced relationV outside of the tube
  • a liquid oxidizer isv fed to thel annular space 28. between the: casings and 2.1 through a feed pipe 39 and ⁇ a. hollow ring 3
  • Feed pipes3'5 and 36 connect the tubes l0 and 25. with the. combustion chamber C, and spacing partitions 46: and 4
  • The. liquid combustion agents are fed through the tubes Ill and 25; by centrifugal force.
  • Provision. is thus made for continuous feed of liquid fuel and a liquid oxidizer to the combustion chambery C, while at the same time the chamber Ci is free to rotate about the axis of the. cross shaftJ
  • a magnetic or solenoid type brake 44 may bev provided.
  • a funnel is mounted concentric with the shaft S and is spaced outwardly from the sleeve 2T.
  • projects radially from the funnel 66 and is aligned with al tube 62 concentric with the tube 25 previously described and rotatable therewith.
  • the tube 62 communicates with a supplementary jacket casing 64, spaced from the jacket casing 50 and having its rear end portion reentrant, as clearly/shown in Fig. 2.
  • Air entering the funnel 60 travels outward through the sleeve 6
  • the flow of air through this auxiliary jacket space is much increased by centrifugal force in the tubes 62 as high speedsvof rotation are attained.
  • a streamlined casing (Fig. 3) is provided outside of each sleeve 6
  • Vanes are mounted on the combustion chambers outside of the jacket casings and act to orient the chamberv C with respect to the resultant air resistance due to movement of the aircraft through the atmosphere and to revolution of the combustion chambers about the axis of the shaft S.
  • the chambers are held from movement about the axis of the cross shaft I4 by the magnetic or solenoid device 44 and the clutch L is disengaged so that the chambers may revolve freely about the axis of the shaft S until full operation of the chambers is attained.
  • the brake is then released and the clutch L is engaged, whereupon the propeller blades are positively rotated and the combustion chambers are correctly and automatically oriented to minimize air resistance.
  • propellers are quite independent of the combustion chambers, so that no modification of the propellers is necessary, and
  • any usual ignition means may also be provided.
  • a propeller shaft mounted to revolve bodily in a circular path and effective to supply power to thus revolve said chambers and also said propeller shaft, means to feed liquid combustion agents to said chambers,means to support said chambers for free rotation about radial axes, self-orienting means on said chambers eiective to orient said chambers on said axes in response to air resistance, jacket means for aircooling the combustion chambers and which 'jacket means are freely open at both the forward and rearward ends; and auxiliary air-cooling means, the effect of which is augmented by centrifugal force.
  • a propeller shaft mounted to revolve bodily in a circular path and effective to supply power to thus revolve said chambers and also said propeller shaft, means to feed liquid combustion agents to said chambers, means to support said chambers for free rotation about radial axes, self-orienting means onsaid chamber effective to orient said chambers on said axes in response to air resistance, braking means effective to selectively prevent free orientation of said combustion chambers during starting operations, and electrical means to render said braking means operative and inoperative.
  • combustion chambers rotatably mounted on said cross shaft, an air-cooling jacket for each chamber, a funnel concentric with said rotatable shaft and open at its forward end, and radial tubes connecting said funnel to said jackets, each chamber having an air-passage between said aircooling 'j acket and said chamber andopen at both ends, and air from said outer air-cooling jackets being discharged into said inner air-passages near the entrance end thereof.
  • a rotatable shaft In an aircraft propulsion mechanism, a rotatable shaft, a cross shaft mounted thereon, combustion chambers rotatablymounted on said crossshaft an air-cooling jacket yfor each chamber, a funnel concentric' with said rotatable shaft and open at its forward end, and radial tubes connecting said funnel to said jackets, Yeach chamber having an air-passage between said aircooling jacket and said chamber and open at both ends, and air from said outer air-cooling jackets being discharged into each inner air-passage near the entrance end thereof, and means being provided to redirect said air rearward as' so discharged.

Description

May 1, 1951 R. H. GODDARD 2,551,111
REVOLVING COMBUSTION CHAMBER Filed June 28, 1946 l 510 5b 4 35 lz v '6,0 l. d i 75- Patented May 1, 1951 STATES PATENT OFFICE REVOLVING COMBUSTIONv CHAMBER Application June 28, 1946, Serial No. 680,230 (c1. fsu- 41) y 4 Claims. Y 1
This invention relates; to; aircraft propulsion mechanism in. which a propeller is rotated by a plurality of small combustion. chambers of rocket type which are mounted.v to revolve in; a. circular path about the. axis of the. propeller. and to supply power to rotate the propeller., i
It is: the general object of the invention. to provide; an. improved construction. in such propulsion mechanism, in which the revolving combus` tion. chambers will present a minimum. air resistance and will. most effectively apply power to turn the propel-ler.
To the attainment of this generali object, a construction` is provided in which the combustion. chambers are self-adjusting to air resistance and automatically' orient themselves to positions of minimum resistance. Means is also provided to prevent such automatic adjustment during the. starting up` of the apparatus, and also for disconnecting the propeller from the. revolving chambers so that the chambers may be started in operation and may b e brought up to the desired speed of revolution withminimum resistance.
The invention further relates toy arrangements and combinations of parts which will. be hereinafter described and more particularly pointed out in the appended claims.
A preferred form of the invention is shownv in the drawing, i-nwhich Fig; lis a side elevation of the improved construction;
Fig. 2` is anenlarged sectional side elevation of one combustion chamber; and
Fig. 3 is a transverse sectional view, taken along the line 3-3 in- Fig. 2. Y Y
Referring to the drawing, a pair of combustion chambersA C are shown mounted on a shaft' S wl'iichy isj rotatable in suitable bearings inv an aircraftand which is aligned with a shaft Si' which is similarly mounted and which is provided with propeller blades P. A clutch Lv is provided by whichv the propeller shaft S may beA connected or disconnected with respect to the shaft S by shifting a. handle lever H;
`of a tube I 0, which tube is rotatably supported by a thrust bearing |2 at the outer end ofy a cross shaft |.4 secured to and rotatable withlthe shaft 'I'he lower end of each tube IU is open, and the tube rotates freely about a sleeve IB, projecting outward from a casing I'l mounted on and rotatable. with the shaft S. Liquid fuel for the combustion chamber may be fed rto the space 20 within the casing through a feed pipe 2| `connected to a hollow ring 22 mounted on the casing but non-rotatable therewith.
A second tubey 25 is mounted in spaced relationV outside of the tube |6, and the open lower end of the tube 25` surrounds a sleeve 2t,l sup.- ported on a casing. 21- concentric with and spaced from the.` casing I l previously described. A liquid oxidizer isv fed to thel annular space 28. between the: casings and 2.1 through a feed pipe 39 and` a. hollow ring 3| mounted on but non-rotatable with the casing 211. i
Feed pipes3'5 and 36 connect the tubes l0 and 25. with the. combustion chamber C, and spacing partitions 46: and 4| are provided within the tubes |0. and 25 and just above the points at which the feed pipes.' 35V and. 36 enter the tubes. The. liquid combustion agents are fed through the tubes Ill and 25; by centrifugal force.
Provision. is thus made for continuous feed of liquid fuel and a liquid oxidizer to the combustion chambery C, while at the same time the chamber Ci is free to rotate about the axis of the. cross shaftJ |f4` and is also. free to revolve bodily about the axis of the shaft S. i
In order to prevent angular movement of the combustion` chambers about the axis of the shaft |42 while they combustion chambers are being placed in operation, a magnetic or solenoid type brake 44 may bev provided.
Special provision is made for cooling the combustion chambers and comprises a jacket casing surrounding the combustion chamber C' and held in spaced relation thereto by axially extending spaced partitions 5|. Both ends of the jacket space betweenthe casing 50 and-the chamberlC are open, and the rush of air through this jacket space when the aircraft is in flight effectively cools the combustion chamber.
If additional cooling effect is desired, a funnel is mounted concentric with the shaft S and is spaced outwardly from the sleeve 2T. A sleeve 6| projects radially from the funnel 66 and is aligned with al tube 62 concentric with the tube 25 previously described and rotatable therewith.
The tube 62 communicates with a supplementary jacket casing 64, spaced from the jacket casing 50 and having its rear end portion reentrant, as clearly/shown in Fig. 2. Air entering the funnel 60 travels outward through the sleeve 6| and tube 62 to the auxiliary jacket space, where its direction of movement is reversed and it enters the open front end of-the main jacket space between the jacket casing 5G and the combustion chamber C. The flow of air through this auxiliary jacket space is much increased by centrifugal force in the tubes 62 as high speedsvof rotation are attained.
In order to reduce the air resistance of the tubes which support the combustion chambers, a streamlined casing (Fig. 3) is provided outside of each sleeve 6| and tube 62. This casing is mounted on the outer jacket casing 64 and turns with the combustion chamber about the axis of the shaft I4.
Vanes are mounted on the combustion chambers outside of the jacket casings and act to orient the chamberv C with respect to the resultant air resistance due to movement of the aircraft through the atmosphere and to revolution of the combustion chambers about the axis of the shaft S.
In starting this propulsion mechanism in operation, the chambers are held from movement about the axis of the cross shaft I4 by the magnetic or solenoid device 44 and the clutch L is disengaged so that the chambers may revolve freely about the axis of the shaft S until full operation of the chambers is attained. The brake is then released and the clutch L is engaged, whereupon the propeller blades are positively rotated and the combustion chambers are correctly and automatically oriented to minimize air resistance.
It will be noted that the propellers are quite independent of the combustion chambers, so that no modification of the propellers is necessary, and
the chambers, and any usual ignition means may also be provided.
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 an aircraft propulsion mechanism, a propeller shaft, combustion chambers mounted to revolve bodily in a circular path and effective to supply power to thus revolve said chambers and also said propeller shaft, means to feed liquid combustion agents to said chambers,means to support said chambers for free rotation about radial axes, self-orienting means on said chambers eiective to orient said chambers on said axes in response to air resistance, jacket means for aircooling the combustion chambers and which 'jacket means are freely open at both the forward and rearward ends; and auxiliary air-cooling means, the effect of which is augmented by centrifugal force.
2. In an aircraft propulsion mechanism, a propeller shaft, combustion chambers mounted to revolve bodily in a circular path and effective to supply power to thus revolve said chambers and also said propeller shaft, means to feed liquid combustion agents to said chambers, means to support said chambers for free rotation about radial axes, self-orienting means onsaid chamber effective to orient said chambers on said axes in response to air resistance, braking means effective to selectively prevent free orientation of said combustion chambers during starting operations, and electrical means to render said braking means operative and inoperative.
3. In an aircraft propulsion mechanism, a :ro-
vtatable shaft, a cross shaft mounted thereon,
combustion chambers rotatably mounted on said cross shaft, an air-cooling jacket for each chamber, a funnel concentric with said rotatable shaft and open at its forward end, and radial tubes connecting said funnel to said jackets, each chamber having an air-passage between said aircooling 'j acket and said chamber andopen at both ends, and air from said outer air-cooling jackets being discharged into said inner air-passages near the entrance end thereof.
` 4.. In an aircraft propulsion mechanism, a rotatable shaft, a cross shaft mounted thereon, combustion chambers rotatablymounted on said crossshaft an air-cooling jacket yfor each chamber, a funnel concentric' with said rotatable shaft and open at its forward end, and radial tubes connecting said funnel to said jackets, Yeach chamber having an air-passage between said aircooling jacket and said chamber and open at both ends, and air from said outer air-cooling jackets being discharged into each inner air-passage near the entrance end thereof, and means being provided to redirect said air rearward as' so discharged.
ESTHER C. GODDARD, Executrz' of thev Last -Will and Testament of Robert H. Goddard, Deceased.
REFERENCES CITED The following references are of record in the le of this patent:
UNITED STATES PATENTS Number Name Date 2,074,098 Adams Mar. 16, 1937 2,124,462 Cummings July 19, 1938 2,142,601 Bleecker Jan. 3, 1939 2,220,066 Cornell Nov. 5, 1940 2,396,130 Sbrilli Mar. 5, 1946 2,397,357 Kundig Mar. 26, 1946 2,409,551 Donnellan Oct'. 15, 1946 2,423,183 Forsyth July 1, 1947 2,432,359 Streid Dec. 9, 1947 2,433,107 Forsyth Dec. 23, 1947 `2,446,266 Cummings Aug. 3, 1948 2,474,685 McCollum June 28, 1949 2,485,502 McCollum Oct. 18, 1949 FOREIGN PATENTS Number Country Date 227,151 Great Britain Jan. 12, 1925 366,450 Great Britain July 30, 1930 648,107
France Dec. 5, 1928
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Cited By (8)

* 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
US2865168A (en) * 1952-07-09 1958-12-23 Alex Deutsch Fuel burning reaction motor powered hydraulic and electric power unit
US3077075A (en) * 1957-03-15 1963-02-12 Turanciol Fuad Rotary radial flow jet engine
US4625509A (en) * 1980-04-21 1986-12-02 Sheppard Sr Darrel J Combustion engine
WO1997021915A1 (en) * 1995-12-13 1997-06-19 Klein Hans U Propulsion engine driven by rotary rockets
US20170082022A1 (en) * 2014-03-28 2017-03-23 Brent Lee Engine, Biomass Powder Energy Conversion and/or Generation System, Hybrid Engines Including the Same, and Methods of Making and Using the Same
US11280265B2 (en) * 2019-05-07 2022-03-22 Evgeni Shamis Gas turbine engine having bladeless first stage and ejectors
US20230151765A1 (en) * 2023-01-04 2023-05-18 Robert Bado Tangential turbofan propulsion system

Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB227151A (en) * 1923-09-10 1925-01-12 Benjamin Charles Carter Improvements in or relating to internal combustion turbines
FR648107A (en) * 1927-02-18 1928-12-05 Jet engine
GB366450A (en) * 1929-07-31 1932-02-04 Frank Atherton Howard An improved internal combustion turbine and turbopropeller
US2074098A (en) * 1932-08-23 1937-03-16 Adams Herbert Luther Rocket airship
US2124462A (en) * 1937-08-18 1938-07-19 Charles R Cummings Rocket engine
US2142601A (en) * 1935-04-19 1939-01-03 Maitland B Bleecker Reaction propulsion device
US2220066A (en) * 1938-07-27 1940-11-05 Jr Edward S Cornell Liquid fuel burner unit
US2396130A (en) * 1944-01-06 1946-03-05 Sbrilli Anthony Air jet propelled helicopter
US2397357A (en) * 1942-03-09 1946-03-26 John J Kundig Reaction turbine propeller
US2409551A (en) * 1942-06-15 1946-10-15 Maurice L Donnellan Aircraft propulsion
US2423183A (en) * 1944-07-13 1947-07-01 Fairey Aviat Co Ltd Turbine type jet propulsion
US2432359A (en) * 1947-12-09 Internal-combustion turbine power
US2433107A (en) * 1944-08-31 1947-12-23 Fairey Aviat Co Ltd Power plant for helicopters
US2446266A (en) * 1946-02-23 1948-08-03 Thomas L Cummings Jet propelled helicopter rotor
US2474685A (en) * 1945-04-12 1949-06-28 Stewart Warner Corp Jet propulsion apparatus
US2485502A (en) * 1945-04-12 1949-10-18 Thelma Mccollum Jet propulsion means for helicopters

Patent Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2432359A (en) * 1947-12-09 Internal-combustion turbine power
GB227151A (en) * 1923-09-10 1925-01-12 Benjamin Charles Carter Improvements in or relating to internal combustion turbines
FR648107A (en) * 1927-02-18 1928-12-05 Jet engine
GB366450A (en) * 1929-07-31 1932-02-04 Frank Atherton Howard An improved internal combustion turbine and turbopropeller
US2074098A (en) * 1932-08-23 1937-03-16 Adams Herbert Luther Rocket airship
US2142601A (en) * 1935-04-19 1939-01-03 Maitland B Bleecker Reaction propulsion device
US2124462A (en) * 1937-08-18 1938-07-19 Charles R Cummings Rocket engine
US2220066A (en) * 1938-07-27 1940-11-05 Jr Edward S Cornell Liquid fuel burner unit
US2397357A (en) * 1942-03-09 1946-03-26 John J Kundig Reaction turbine propeller
US2409551A (en) * 1942-06-15 1946-10-15 Maurice L Donnellan Aircraft propulsion
US2396130A (en) * 1944-01-06 1946-03-05 Sbrilli Anthony Air jet propelled helicopter
US2423183A (en) * 1944-07-13 1947-07-01 Fairey Aviat Co Ltd Turbine type jet propulsion
US2433107A (en) * 1944-08-31 1947-12-23 Fairey Aviat Co Ltd Power plant for helicopters
US2474685A (en) * 1945-04-12 1949-06-28 Stewart Warner Corp Jet propulsion apparatus
US2485502A (en) * 1945-04-12 1949-10-18 Thelma Mccollum Jet propulsion means for helicopters
US2446266A (en) * 1946-02-23 1948-08-03 Thomas L Cummings Jet propelled helicopter rotor

Cited By (9)

* 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
US2865168A (en) * 1952-07-09 1958-12-23 Alex Deutsch Fuel burning reaction motor powered hydraulic and electric power unit
US3077075A (en) * 1957-03-15 1963-02-12 Turanciol Fuad Rotary radial flow jet engine
US4625509A (en) * 1980-04-21 1986-12-02 Sheppard Sr Darrel J Combustion engine
WO1997021915A1 (en) * 1995-12-13 1997-06-19 Klein Hans U Propulsion engine driven by rotary rockets
US20170082022A1 (en) * 2014-03-28 2017-03-23 Brent Lee Engine, Biomass Powder Energy Conversion and/or Generation System, Hybrid Engines Including the Same, and Methods of Making and Using the Same
US10280838B2 (en) * 2014-03-28 2019-05-07 Brent Lee Engine, biomass powder energy conversion and/or generation system, hybrid engines including the same, and methods of making and using the same
US11280265B2 (en) * 2019-05-07 2022-03-22 Evgeni Shamis Gas turbine engine having bladeless first stage and ejectors
US20230151765A1 (en) * 2023-01-04 2023-05-18 Robert Bado Tangential turbofan propulsion system

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