US2518002A - Means for feeding concentric liquid sprays to a rotating combustion chamber - Google Patents
Means for feeding concentric liquid sprays to a rotating combustion chamber Download PDFInfo
- Publication number
- US2518002A US2518002A US82A US8248A US2518002A US 2518002 A US2518002 A US 2518002A US 82 A US82 A US 82A US 8248 A US8248 A US 8248A US 2518002 A US2518002 A US 2518002A
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- United States
- Prior art keywords
- combustion chamber
- feeding
- liquid sprays
- concentric
- rotating combustion
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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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
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- 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 rotating combustion chambers having rearwardly directed discharge nozzles and as used in propulsion apparatus. It is the general object of this invention to provide improved concentric means for feeding combined sprays of two different combustion liquids to a rotating combustion chamber.
- a further feature of the "invention relates to an improved construction by which the relative inner and outer positions of the two combustion liquids in adjacent sprays may be alternated.
- Fig. l is a sectional longitudinal elevation showing one embodiment of this invention
- Fig. 2 is a detail transverse sectional view, taken along the line 2-2 in Fig. 1;
- Fig. 3 is an enlarged sectional detail of certain parts shown in Fig. 1;
- Fig. 4 is a view similar to Fig. 2 but showing a modified construction
- Fig. 5 is a diagrammatic view to be described.
- Figs. 6 and '7 are perspective views of outer and inner rotator members to be described.
- a combustion chamber C is shown as comprising oppositely disposed conical portions l and II and a rearwardly directed discharge nozzle l2.
- Jacket casing members I4 and i are mounted outside of the combustion chamber portions i0 and II and are maintained in spaced relation therefrom by partitions l6 and I1. These partitions divide the jacket spaces S and S into outwardly extending compartments in which rapid rotation of the liquids supplied to the jacket spaces S and S will be induced.
- the combustion chamber and enclosing casings are mounted in bearings and 2
- a drive shaft 22 is connected to the combustion chamber at the end thereof opposite the nozzle I2.
- the shaft 22 may be rotated from any convenient source of power.
- the casing members are displaced inwardly as shown in Fig. 3 to provide end partitions Ma and lie. which combine to alternately close the ends of the jacket spaces S and S.
- the space S communicates with the chamber C through an opening in an inner spray portion Ila of the casing member II, and the jacket space S communicates with the chamber C through an opening in an outer spray portion 10a of the chamber portion II.
- a spirally ribbed rotator 30 is mounted in the spray portion Ila, and spirally ribbed rotator ring 32 is mounted in the space between the concentric spray portions lDa and l l a.
- a rotating spray of one liquid as gasoline
- a rotating spray of a second combustion liquid as liquid oxygen
- the outward projection of the jacket casing portions l4 and i5 preferably alternates circumferentially about the chamber C, sothat, for each two adjacent combined sprays, the inner and outer relation of the two combustion liquids is reversed.
- Fig. 4 a modified construction is shown which is similar in construction and operation to that shown in Fig. 2, but in which the spray openings ill and ll are tangentially disposed in the direction of rotation of the combustion chamber, so that even more effective intermingling of the combustion liquids may take place.
- propulsion apparatus having a rotating combustion chamber with opposed and substantially conical jacketed body portions and with a rearwardly-directed discharge nozzle
- improvement which consists in providing devices to deliver concentric sprays of two different combustion liquids from the jacket spaces into said chamber at each of a series of circumterentially spaced points which are located substantially at the greatest chamber diameter and substantially at the juncture of said opposed conical body portions, and in providing means to supply an inner liquid and an outer liquid concentrically to each delivery device from the jacket spaces, and in providing means to reverse the inner and outer concentric relationship of said liquids in circumferentially adjacent delivery devices.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Description
Aug. 8, 1950 R H GODDAR 2,518,002
D MEANS FOR FEEDING CONCENTRIC LIQUID SPRAYS TO A ROTATING COMBUSTION CHAMBER Filed Jan. 2, 1948 l NVENTOR.
m6, E /ecUi X. j l j BY [675%656 Godda (7 (y I I Z5 ATTORNEYS.
Patented Aug. 8, 1950 2,518,002 MEANS FOR FEEDING CONCENTBIC LIQUID SPRAYS TO A CHAMBER Robert H.
Md., by Esther C.
and Florence ROTATING CODIBUSTION Goddard, deceased, late of Annapolis,
Goddard, executrlx, Worcester, Mass., assignor of one-half to The Daniel Guggenheim Foundation,
New
York, N. Y., a corporation of New York Application January 2, 1948, Serial No. 82
(Cl. Gil-35.6)
3 Claim.
This invention relates to rotating combustion chambers having rearwardly directed discharge nozzles and as used in propulsion apparatus. It is the general object of this invention to provide improved concentric means for feeding combined sprays of two different combustion liquids to a rotating combustion chamber.
In the preferred form, are fed to the rotating combustion chamber at the locus of greatest diameter, and are fed by centrifugal force which is developed by the rapid rotation of the combustion chamber.
A further feature of the "invention relates to an improved construction by which the relative inner and outer positions of the two combustion liquids in adjacent sprays may be alternated.
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. l is a sectional longitudinal elevation showing one embodiment of this invention;
Fig. 2 is a detail transverse sectional view, taken along the line 2-2 in Fig. 1;
Fig. 3 is an enlarged sectional detail of certain parts shown in Fig. 1;
Fig. 4 is a view similar to Fig. 2 but showing a modified construction;
Fig. 5 is a diagrammatic view to be described; and
Figs. 6 and '7 are perspective views of outer and inner rotator members to be described.
Referring to the drawing, a combustion chamber C is shown as comprising oppositely disposed conical portions l and II and a rearwardly directed discharge nozzle l2. Jacket casing members I4 and i are mounted outside of the combustion chamber portions i0 and II and are maintained in spaced relation therefrom by partitions l6 and I1. These partitions divide the jacket spaces S and S into outwardly extending compartments in which rapid rotation of the liquids supplied to the jacket spaces S and S will be induced.
The combustion chamber and enclosing casings are mounted in bearings and 2| and are rotatable as a unit therein. A drive shaft 22 is connected to the combustion chamber at the end thereof opposite the nozzle I2. The shaft 22 may be rotated from any convenient source of power.
A combustion liquid. as gasoline, is supplied to the jacket space S through a nozzle 25, and a second combustion liquid, as liquid oiwgen, is
the concentric sprays 2 supplied to the jacket space S through a second nozzle 28.
At the juncture of the chamber portions Iii and II and of the jacket casing members H and IS, the casing members are displaced inwardly as shown in Fig. 3 to provide end partitions Ma and lie. which combine to alternately close the ends of the jacket spaces S and S.
On the section shown in Fig.- 3, the space S communicates with the chamber C through an opening in an inner spray portion Ila of the casing member II, and the jacket space S communicates with the chamber C through an opening in an outer spray portion 10a of the chamber portion II.
A spirally ribbed rotator 30 is mounted in the spray portion Ila, and spirally ribbed rotator ring 32 is mounted in the space between the concentric spray portions lDa and l l a.
With this construction, a rotating spray of one liquid, as gasoline, will be injected under pressure through the outer conical passage between the parts Ilia and Ila and around the rotator ring 32, and a rotating spray of a second combustion liquid, as liquid oxygen, will be similarly injected through the opening in the inner part Ila and around the rotator 30. The outward projection of the jacket casing portions l4 and i5 preferably alternates circumferentially about the chamber C, sothat, for each two adjacent combined sprays, the inner and outer relation of the two combustion liquids is reversed.
This alternation is shown diagrammatically in Fig. 5, with the alternately projecting portions indicated as a serpentine partition 35.
In Fig. 4 a modified construction is shown which is similar in construction and operation to that shown in Fig. 2, but in which the spray openings ill and ll are tangentially disposed in the direction of rotation of the combustion chamber, so that even more effective intermingling of the combustion liquids may take place.
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 propulsion apparatus having a rotating combustion chamber with opposed and substantially conical jacketed body portions and with a rearwardly-directed discharge nozzle, that improvement which consists in providing devices to deliver concentric sprays of two different combustion liquids from the jacket spaces into said chamber at each of a series of circumterentially spaced points which are located substantially at the greatest chamber diameter and substantially at the juncture of said opposed conical body portions, and in providing means to supply an inner liquid and an outer liquid concentrically to each delivery device from the jacket spaces, and in providing means to reverse the inner and outer concentric relationship of said liquids in circumferentially adjacent delivery devices.
2. The combination in propulsion apparatus as set forth in claim 1, in which the concentric delivery devices in said circumferential series are.
tangentially disposed.
3. The combination in propulsion apparatus as set forth in claim 1, in which the end portions of the jacketed body portions comprise a serpentine partition separating the Jacket spaces and re- REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 1,343,098 Stephens June 8, 1920 1,637,772 Heckel et a1 Aug. 2, 1927 1,897,092 Weir Feb. 14, 1933 Goddard Feb. 19, 1946
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US82A US2518002A (en) | 1948-01-02 | 1948-01-02 | Means for feeding concentric liquid sprays to a rotating combustion chamber |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US82A US2518002A (en) | 1948-01-02 | 1948-01-02 | Means for feeding concentric liquid sprays to a rotating combustion chamber |
Publications (1)
Publication Number | Publication Date |
---|---|
US2518002A true US2518002A (en) | 1950-08-08 |
Family
ID=21689838
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US82A Expired - Lifetime US2518002A (en) | 1948-01-02 | 1948-01-02 | Means for feeding concentric liquid sprays to a rotating combustion chamber |
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US (1) | US2518002A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3013389A (en) * | 1960-06-13 | 1961-12-19 | Paul T Barnes | Liquid propellant rocket |
US3136123A (en) * | 1959-08-20 | 1964-06-09 | Stein Samuel | Rocket engine injector |
US4007586A (en) * | 1975-11-10 | 1977-02-15 | The United States Of America As Represented By The Secretary Of The Army | Spin nozzle and thrust augmentor mechanism |
US5473885A (en) * | 1994-06-24 | 1995-12-12 | Lockheed Corporation | Pulse detonation 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 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1343098A (en) * | 1919-07-11 | 1920-06-08 | Stephens Mfg Company | Process and apparatus for burning gaseous fuel with high efficiency |
US1637772A (en) * | 1923-03-22 | 1927-08-02 | Messer Griesheim Gmbh | Air-blast gas burner |
US1897092A (en) * | 1929-01-11 | 1933-02-14 | Autogiro Co Of America | Aircraft with rotative wings |
US2395114A (en) * | 1942-10-12 | 1946-02-19 | Daniel And Florence Guggenheim | Rotating combustion chamber for rocket apparatus |
-
1948
- 1948-01-02 US US82A patent/US2518002A/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1343098A (en) * | 1919-07-11 | 1920-06-08 | Stephens Mfg Company | Process and apparatus for burning gaseous fuel with high efficiency |
US1637772A (en) * | 1923-03-22 | 1927-08-02 | Messer Griesheim Gmbh | Air-blast gas burner |
US1897092A (en) * | 1929-01-11 | 1933-02-14 | Autogiro Co Of America | Aircraft with rotative wings |
US2395114A (en) * | 1942-10-12 | 1946-02-19 | Daniel And Florence Guggenheim | Rotating combustion chamber for rocket apparatus |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3136123A (en) * | 1959-08-20 | 1964-06-09 | Stein Samuel | Rocket engine injector |
US3013389A (en) * | 1960-06-13 | 1961-12-19 | Paul T Barnes | Liquid propellant rocket |
US4007586A (en) * | 1975-11-10 | 1977-02-15 | The United States Of America As Represented By The Secretary Of The Army | Spin nozzle and thrust augmentor mechanism |
US5473885A (en) * | 1994-06-24 | 1995-12-12 | Lockheed Corporation | Pulse detonation 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 |
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