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Publication numberUS2476185 A
Publication typeGrant
Publication dateJul 12, 1949
Filing dateAug 23, 1947
Priority dateAug 23, 1947
Publication numberUS 2476185 A, US 2476185A, US-A-2476185, US2476185 A, US2476185A
InventorsEsther C Goddard
Original AssigneeDaniel And Florence Guggenheim
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Combustion chamber with refractory lining
US 2476185 A
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Description  (OCR text may contain errors)

July 12, W49. R. H. GODDARD COMBUSTION CHAMBER WITH REFRACTORY LINING Filed Aug. 23, 1947 R W N w w INVENTDR. cdazdflkcdb Patented July 12, 1949 umrso STATES PATENT OFFICE COMBUSTION CHAMBER WITH REFRACTORY LINING Application August 23, 1947, Serial No. 770,311 7 Claims. (o1. 6035.6)

grooves arranged in acircumferential series in the nozzle portion.

In the preferred form, the helical corrugations of the body portion increase in pitch and merge gradually into the longitudinal grooves of the nozzle portion.

A further object of the invention is to provide a combustion chamber having a metal wall or casing with similar corrugations and grooves in the body and nozzle portions. This metal casingsupports and positions the refractory lining. Provision is also made for cooling the outer surface of said metal casing.

lower end, so that the corrugations 23 merge gradually into longitudinal grooves 24 in the nozzle lining 22; The walls of the chamber and nozzle are of thin metal and are preferably simi- The invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the appended claims.

Apreferred form of the invention is shownin the drawing, in which Fig. 1 is a transverse sectional elevation of a combustion chamber embodying this invention;

Fig. 2 is an enlarged sectional elevation of a portion of Fig. 1;

Fig. 3 is a transverse sectional plan view of the nozzle structure, taken along the line 33 in Fig. l;-

Fig. 4 is a fragmentary vertical section of a portion of the nozzle structure, taken along the line 4-4 in Fig. 1; and

Fig. 5 is a fragmentary view of a portion of a supporting brace or partition.

Referring to the drawing, a combustion chamber is shown having a relatively thin metal casing providing a body portion Ill and a discharge nozzle portion I l. The combustion chamber is mounted within an outer jacket l5 and is firmly held in spaced relation thereto byperforated partitions l1 (Figs. 1 and 5). The nozzle portion H is similarly supported by longitudinally extending ribs or partitions l8 (Fig. 3)

A refractory lining is provided in the body portion Ill, and a similar refractory lining 22 is provided in the nozzle portion II. The lining portion 20 is provided with corrugations 23 (Fig. 2) which preferably form a continuous helix. The helix preferably increases in pitch at its larly corrugated and grooved.

The lining portions 20 and 22 may be formed of any suitable refractory material, such as carbon, a carbide or a high refractory oxide.

A suitable cooling liquid is supplied to the jacket space S through a pipe 30 and a volute passage 3| (Fig. 3). Openings 34 (Fig. 4) connect the volute 3| with the lower end of the jacket space S. The cooling liquid then flows upward through the perforated partitions I1 and preferably enters the upper end of the combustion chamber through tangentially disposed nozzle elements 35 (Figs. 1 and 2) Combustion liquids, such as gasoline and liquid oxygen, may be fed to the upper end of the combustion chamber through pipes 40 and 4| and spray openings 42 and 43. A suitable ignition device is also provided, indicated generally by the numeral 50. 1

The thickness of the refractory lining material in the lining portions 20 and 22 is preferably such that the material is slightly below its softening or melting point at its inner surface when the chamber is in operation, while the outer surface which is in contact with the metal walls of the combustion chamber and nozzle, is at a lower temperature at which injury to these walls will be avoided.

The corrugated and lined construction above described presents substantial advantages in combustion chamber operation. The chamber lining portion 20 serves to retain heat within the chamber, and prevents direct contact of the hot combustion gases with the metal wall H), which latter element is kept relatively cool by the cooling liquid in the jacket space S.

The corrugations in the refractory lining present a relatively large area on which surface combustion may take place and furthermore, the corrugations produce eddies and vortices and thus facilitate. mixing of the combustion elements.

The gradual increase in pitch of the corrugations 23 assists the combustion gases to achieve smooth flow into the axial grooves of the nozzle portion II.

A combustion chamber constructed as above described resists wear and oxidation and may be maintained in operation ,over relatively long periods of time. I

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 a combustion chamber having an elongated cylindrical body portion and having a nozzle portion, in combination, a refractory lining for said body portion which is provided on its inner surface with a continuous helical groove of relatively small pitch, and in its nozzle portion with longitudinally extending grooves into which said helical groove merges.

2. The combination in a combustion chamber as set forth in claim 1, in which the helical groove increases in pitch towards its lower end and merges gradually into the longitudinal grooves.

3. The combination in a combustion chamber as set forth in claim 1, in which the combustion chamber has an outer metal wall having helical and longitudinal grooves corresponding in section to the grooves of the refractory lining.

4. A combustion chamber comprising an elongated cylindrical metal body portion having a helically grooved inner surface provided with a similarly grooved refractory lining, and said chamber having a longitudinally grooved metal nozzle portion provided with a longitudinally grooved refractory lining.

5. The combination in a combustion chamber as set forth in claim 4-, in which the helical lining groove increases gradually in pitch as it approaches the longitudinal grooves of the nozzle lining.

6. In a combustion chamber having an elongated cylindrical body portion and having a noz- 35 2,417,445

4 for said body portion which is provided on its inner surface with a continuous helical groove of relatively small pitch, and in its nozzle portion with longitudinally extending grooves into which said helical groove merges, an outer jacket casing providing a Jacket space surrounding said body portion and nozne, and means to supply a cooling liquid to said jacket space.

7. In a combustion chamber having an elongated cylindrical body portion and having a nozzle portion, in combination, a refractory lining for said body portion which is provided on its inner surface with a continuous helical groove of relatively small pitch and in its nozzle portion with longitudinally extending grooves into which said helical groove merges, an outer Jacket casing providing a jacket space surrounding said body portion and nozzle,.means to supply a cooling liquid to said Jacket space, and means to discharge said liquid tangentially from said jacket space to said combustion chamber.

ESTHER C. GODDARD, Executnz: of the Last Will 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 1,888,749 Urquhart Nov. 22, 1932 2,115,769 Harris May 3, 1938 2,286,909 ,Goddard June 16, 1942 Pinkel Mar. 18, 1947

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1888749 *Sep 5, 1930Nov 22, 1932Urquhart Kenneth MReactive combustion engine
US2115769 *Aug 22, 1936May 3, 1938Harris Henry HRadiant heating tube
US2286909 *Dec 16, 1940Jun 16, 1942Robert H GoddardCombustion chamber
US2417445 *Sep 20, 1945Mar 18, 1947Benjamin PinkelCombustion chamber
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2658332 *Mar 21, 1951Nov 10, 1953Carborundum CoFluid cooled, refractory, ceramic lined rocket structure
US2696076 *Nov 28, 1949Dec 7, 1954Weeks Ivan FTurbulence and combustion-promoting device for ram jet motors
US2734578 *Feb 14, 1952Feb 14, 1956 Walter
US2749706 *Oct 29, 1953Jun 12, 1956Daniel And Florence GuggenheimMechanism for cooling a combustion chamber in propulsion apparatus and for feeding combustion liquids thereto
US2810382 *Nov 9, 1954Oct 22, 1957Koch Sons GeorgeDirect fired water heaters
US3021671 *Apr 3, 1958Feb 20, 1962George WallachRocket engines
US3024596 *Mar 16, 1955Mar 13, 1962Strato Missiles IncPropulsion system with automatic control of fuel and air
US3043103 *Oct 10, 1958Jul 10, 1962Gen Motors CorpLiquid cooled wall
US3095694 *Oct 28, 1959Jul 2, 1963Johanna Walter HermineReaction motors
US3151449 *Aug 25, 1961Oct 6, 1964Curtiss Wright CorpRocket nozzle cooling system
US3289943 *Aug 17, 1962Dec 6, 1966Westinghouse Electric CorpThermal barrier for thrust vehicle nozzle
US3321922 *Oct 29, 1964May 30, 1967Jr William T LattoSmall rocket engine
US3383862 *Feb 14, 1966May 21, 1968Thiokol Chemical CorpRocket thrust chamber
US3420061 *Nov 4, 1966Jan 7, 1969Thiokol Chemical CorpRocket combustion chamber and propellant injection apparatus
US4118925 *Feb 24, 1977Oct 10, 1978Carmel Energy, Inc.Hydrocarbon fuels, recovering underground petroleum
US4499946 *Mar 10, 1981Feb 19, 1985Mason & Hanger-Silas Mason Co., Inc.Enhanced oil recovery process and apparatus
US6047539 *Apr 30, 1998Apr 11, 2000General Electric CompanyMethod of protecting gas turbine combustor components against water erosion and hot corrosion
US7958719 *Mar 28, 2007Jun 14, 2011The Aerospace CorporationNoncircular transient fluid fuel injector control channels in propellant injector combustion systems
DE1142253B *Jan 29, 1960Jan 10, 1963Boelkow Entwicklungen KgBrennkammer fuer Fluessigtreibstoffe
EP1203879A2 *Oct 27, 2001May 8, 2002Astrium GmbHCooling for a combustion chamber for rockets
Classifications
U.S. Classification60/260, 60/265, 60/258, 60/915, 60/39.55
International ClassificationF02K9/62, F02K9/64
Cooperative ClassificationF02K9/62, Y10S60/915, F02K9/64
European ClassificationF02K9/64, F02K9/62