US2487435A - Fuel and water feeding and steam discharge arrangement for combustion chambers - Google Patents
Fuel and water feeding and steam discharge arrangement for combustion chambers Download PDFInfo
- Publication number
- US2487435A US2487435A US7015A US701548A US2487435A US 2487435 A US2487435 A US 2487435A US 7015 A US7015 A US 7015A US 701548 A US701548 A US 701548A US 2487435 A US2487435 A US 2487435A
- Authority
- US
- United States
- Prior art keywords
- combustion
- chamber
- volute
- fuel
- combustion chambers
- Prior art date
- 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.)
- Expired - Lifetime
Links
- 238000002485 combustion reaction Methods 0.000 title description 28
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title description 8
- 239000000446 fuel Substances 0.000 title description 2
- 238000010276 construction Methods 0.000 description 9
- 229910052751 metal Inorganic materials 0.000 description 9
- 239000002184 metal Substances 0.000 description 9
- 239000007788 liquid Substances 0.000 description 6
- 239000007921 spray Substances 0.000 description 6
- 239000000463 material Substances 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000004326 stimulated echo acquisition mode for imaging Methods 0.000 description 2
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 2
- 229910052721 tungsten Inorganic materials 0.000 description 2
- 239000010937 tungsten Substances 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 208000033830 Hot Flashes Diseases 0.000 description 1
- 206010060800 Hot flush Diseases 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
Images
Classifications
-
- 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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- 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
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- 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
- Y10S165/00—Heat exchange
- Y10S165/907—Porous
Definitions
- This invention relates to combustion chambers as used in rockets and other propulsion apparatus.
- Fig. l is a sectional side elevation of a combustion chamber embodying this invention
- Fig. 2 is a detail sectional end elevation, taken along the line 2-2 in Fig. '1;
- Fig. 3 is a sectionalend elevation on a reduced scale and taken along the line 3-3 in Fig.1;
- Figs. 4 and 5 are enlarged sectional side elevations of certain portions of Fig. .1;- and Fig. 6 is a sectional side elevation of a modified construction.
- Figs. ber C is jshown, having opposed conical walls it and I and provided with a conical discharge nozzle N.
- the outer volute has a dis-' charge pipe through which steam may be devide jacket spaces sand 8' to'which combustion A liquids-maybe supplied'under pressure through feed pipes it and I1.
- Feed openingsor slots and 2i are provided in the adjacent-end portions' of theconical walls Ill and II.
- One combustion liquid, as gasoline, may
- a second combustion liquid as liquid oxygen, may be similarly supplied under pressure through the pipe ii to the space s' and will be sprayed through the openings 2i.
- These sprays intersect and are intimately intermingled as indicated in Fig. 1, andmay be ignited by an axially disposed igniter 23 which maybe of the hot flash or any other convenient type.
- An important feature of the-invention relates discharged through the pipe I0.
- porous metallic materials M and M which are of rigid construction but which also provide contimious filamentary ducts through which the combustion liquids can flow relatively freely.
- the walls It and Ii, casings i2 and I4, and filling materials M and M are all composed of the same metal or alloyand are so united that they form in effect single integral metallic structures.
- This unitary construction may be conveniently achieved by filling the spaces 8 and S with compressed and finely divided metal fragments or metal powder and by thereafter sintering or partially softening and melting the metal fragment to cause them-to adhere to each other and to the enclosing metal walls.
- the metal should have good heat conductivity.
- a mixture of silver and tungsten may be used to advantage, also a mixture of copper and tungsten
- the porous filling materials M and M are stopped off to provide clear spaces adjacent the feed pipes i6 and I1 and adjacent the feed opening or slots 20 and 2
- the adjacent ends of the conical chamber walls ill and II are spaced apart to admit a band 30 having a plurality of small feed openings 3! which communicate with an inner volute 32 (Figs. 1 and ,2) to which water under pressure is fed through a pipe 33.
- An outer volute 35 surrounds the inner volute 32 and is provided with a plurality of tubes 38- which connect into-the combustion chamber-C livered, to be used for any other useful purpose.
- FIG. 6 A slightly modified construction is shown in Fig. 6, in which the combustion chamber C has approximately semi-spherical end walls 50' and ii said volute, an outer volute having tubular connections through said first volute to steam ports in the wall 01' said combustion chamber, and means to discharge steam from said outer volute.
- jacket casings and metal filling materials will be as previously described in connection with Fig. l, and the use and advantages of this construction are the same.
- combustion chamber C gives maximum volume for a given weight of chamber wall and casing and also give exceptional strength.
- a combustion chamber having reversed conical end walls, means to spray two different combustion liquids to said chamber at points adjacent the greatest chamber diameter, a volute encircling said chamber at said greatest diameter and having spray opensteam in said outer volute.
- a combustion chamber having reversed jacketed conical end walls, means to feed two diiierent combustion liquids through said jacketed walls to said chamber at points adjacent the greatest chamber diameter, a volute interposed between said jacketed end walls and encircling said chamber at said greatings into said chamber, means to feed water to est diameter and having spray openings into said chamber, means to feed water to said volute, an outer volute having tubular connections extending through said first volute to steam ports in the wall or said combustion chamber between said water spray openings, and means to discharge steam from said outer volute.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Description
Nov. 8, 1949 R. H. GODDARD FUEL AND WATER FEEDING AND STEAM DISCHARGE ARRANGEMENT FOR COMBUSTION CHAMBERS Filed Feb. 7,' 1948 lGAl/Tfl? F/LAMENTARY METAL v i'lll'll"" INVENTOR.
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Patented Nov. 8, 1949 I 3,481,435 rum. AND WATER rannmc m STEAM DISCHARGE ARRANGEMENT FOR COM- BUSTION CHAMBERS Robert H. Goddard, deceased, late of Annapolis,
Md., by Esther C. 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 February 1, 1948, Serial No. 7,015 v 3 Claims. (01. 60-46) This invention relates to combustion chambers as used in rockets and other propulsion apparatus.
It is an important object of the invention to provide a combustion chamber wall'of improved construction and of increased strength, and one which is well adapted to be effectively cooled by the combustion elements introduced therethrough. 3
A more specific objectis to provide a combustion chamber wall of rigid metallic construction and having impervious inner and outer surface portions and an intermediate porous portion, I
and all preferably of a single metal or alloy.
1 'Another feature of the invention relates to improved means for producing steam in such a combustion chamber and for discharging steam therefrom.
The invention further relates to arrangements and combinations of parts which will be hereinafter set forth and more particularly pointed out inthe appended claims. Y
Preferred forms of the invention are shown in the drawing, in which Fig. l is a sectional side elevation of a combustion chamber embodying this invention;
Fig. 2 is a detail sectional end elevation, taken along the line 2-2 in Fig. '1;
Fig. 3 is a sectionalend elevation on a reduced scale and taken along the line 3-3 in Fig.1;
Figs. 4 and 5 are enlarged sectional side elevations of certain portions of Fig. .1;- and Fig. 6 is a sectional side elevation of a modified construction. I
Referring to Figs. ber C is jshown, having opposed conical walls it and I and provided with a conical discharge nozzle N. Outer walls or casings l2 and pro- 1 to .5, a combustion" chamthrough ports 31. The outer volute has a dis-' charge pipe through which steam may be devide jacket spaces sand 8' to'which combustion A liquids-maybe supplied'under pressure through feed pipes it and I1. Feed openingsor slots and 2i are provided in the adjacent-end portions' of theconical walls Ill and II. One combustion liquid, as gasoline, may
,supplied through the pipe It to the space 3 and will be projected intothe chamber C in the form of fiat. sprays. A second combustion liquid, as liquid oxygen, may be similarly supplied under pressure through the pipe ii to the space s' and will be sprayed through the openings 2i. These sprays intersect and are intimately intermingled as indicated in Fig. 1, andmay be ignited by an axially disposed igniter 23 which maybe of the hot flash or any other convenient type.
An important feature of the-invention relates discharged through the pipe I0.
to the filling of the-jacket spaces 8 and s' with porous metallic materials M and M which are of rigid construction but which also provide contimious filamentary ducts through which the combustion liquids can flow relatively freely.
Preferably the walls It and Ii, casings i2 and I4, and filling materials M and M are all composed of the same metal or alloyand are so united that they form in effect single integral metallic structures.
This unitary construction may be conveniently achieved by filling the spaces 8 and S with compressed and finely divided metal fragments or metal powder and by thereafter sintering or partially softening and melting the metal fragment to cause them-to adhere to each other and to the enclosing metal walls. The metal should have good heat conductivity. A mixture of silver and tungsten may be used to advantage, also a mixture of copper and tungsten The porous filling materials M and M are stopped off to provide clear spaces adjacent the feed pipes i6 and I1 and adjacent the feed opening or slots 20 and 2|. It is sometimes desirable to generate steam by a portion of the heat developed in the combustion chamber 0.
For this purpose,- the adjacent ends of the conical chamber walls ill and II are spaced apart to admit a band 30 having a plurality of small feed openings 3! which communicate with an inner volute 32 (Figs. 1 and ,2) to which water under pressure is fed through a pipe 33.
An outer volute 35 surrounds the inner volute 32 and is provided with a plurality of tubes 38- which connect into-the combustion chamber-C livered, to be used for any other useful purpose.
With this construction, water will-be sprayed into thecombustion chamber through the rela- I tively. small feed openings 3 I from the inner volute 32 and will bequickly changed into steam by the hot combustion gases in the chamber C. This steam, with-some small admixture of combustion gases, then escapes through the ports 31 and tubes 36 to 'the volute 35, and to be thereafter Effective provision is thus made for feeding the combustion liquids under pressure without requiring external power, which is of substantial im-. portance in the operation of rocket apparatus.
A slightly modified construction is shown in Fig. 6, in which the combustion chamber C has approximately semi-spherical end walls 50' and ii said volute, an outer volute having tubular connections through said first volute to steam ports in the wall 01' said combustion chamber, and means to discharge steam from said outer volute.
2. The combination in combustion apparatus as set forth in claim 1, in which the tubular connections are curved in a diametral plane of said chamber to induce rotational circulation of the at substantial angles as in the form previously described. Any usual igniter 85 may be provided for the chamber C.
The integral construction of the chamber walls,
jacket casings and metal filling materials will be as previously described in connection with Fig. l, and the use and advantages of this construction are the same.
It is noted, however, that the substantially spherical shape of the combustion chamber C gives maximum volume for a given weight of chamber wall and casing and also give exceptional strength.
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 combustion apparatus, a combustion chamber having reversed conical end walls, means to spray two different combustion liquids to said chamber at points adjacent the greatest chamber diameter, a volute encircling said chamber at said greatest diameter and having spray opensteam in said outer volute.
3. In combustion apparatus, a combustion chamber having reversed jacketed conical end walls, means to feed two diiierent combustion liquids through said jacketed walls to said chamber at points adjacent the greatest chamber diameter, a volute interposed between said jacketed end walls and encircling said chamber at said greatings into said chamber, means to feed water to est diameter and having spray openings into said chamber, means to feed water to said volute, an outer volute having tubular connections extending through said first volute to steam ports in the wall or said combustion chamber between said water spray openings, and means to discharge steam from said outer volute.
ESTHER C. GODDARD, Ezecutriz: of the Last Will and Testament of Robert H. Goddard, Deceased.
REFERENCES CITED v The following references are of record in the file of this patent:
UNITED STATES PATENTS
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US7015A US2487435A (en) | 1948-02-07 | 1948-02-07 | Fuel and water feeding and steam discharge arrangement for combustion chambers |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US7015A US2487435A (en) | 1948-02-07 | 1948-02-07 | Fuel and water feeding and steam discharge arrangement for combustion chambers |
Publications (1)
Publication Number | Publication Date |
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US2487435A true US2487435A (en) | 1949-11-08 |
Family
ID=21723733
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US7015A Expired - Lifetime US2487435A (en) | 1948-02-07 | 1948-02-07 | Fuel and water feeding and steam discharge arrangement for combustion chambers |
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US (1) | US2487435A (en) |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2776537A (en) * | 1953-04-20 | 1957-01-08 | Adolphe C Peterson | Fuel supply and control means for turbines and turbine jets |
US3134224A (en) * | 1961-05-26 | 1964-05-26 | United Aircraft Corp | Gas bleed from rocket chamber |
US3266241A (en) * | 1963-07-29 | 1966-08-16 | United Aircraft Corp | Propellant injector |
US3595023A (en) * | 1967-01-16 | 1971-07-27 | Bolkow Gmbh | Rocket engine combustion chamber cooling |
US4108241A (en) * | 1975-03-19 | 1978-08-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Heat exchanger and method of making |
EP0604279A1 (en) * | 1992-12-24 | 1994-06-29 | Societe Europeenne De Propulsion | Injector with porous wall for a rocket combustion chamber |
US6389814B2 (en) | 1995-06-07 | 2002-05-21 | Clean Energy Systems, Inc. | Hydrocarbon combustion power generation system with CO2 sequestration |
US6523349B2 (en) | 2000-03-22 | 2003-02-25 | Clean Energy Systems, Inc. | Clean air engines for transportation and other power applications |
US6622470B2 (en) | 2000-05-12 | 2003-09-23 | Clean Energy Systems, Inc. | Semi-closed brayton cycle gas turbine power systems |
US6868677B2 (en) | 2001-05-24 | 2005-03-22 | Clean Energy Systems, Inc. | Combined fuel cell and fuel combustion power generation systems |
US6945029B2 (en) | 2002-11-15 | 2005-09-20 | Clean Energy Systems, Inc. | Low pollution power generation system with ion transfer membrane air separation |
US7021063B2 (en) | 2003-03-10 | 2006-04-04 | Clean Energy Systems, Inc. | Reheat heat exchanger power generation systems |
US20110000981A1 (en) * | 2006-06-20 | 2011-01-06 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. | Injection head, mixing space and power unit |
US7882692B2 (en) | 2004-04-16 | 2011-02-08 | Clean Energy Systems, Inc. | Zero emissions closed rankine cycle power system |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2016921A (en) * | 1930-02-19 | 1935-10-08 | Robert H Goddard | Means for cooling combustion chambers |
US2405785A (en) * | 1944-03-14 | 1946-08-13 | Daniel And Florence Guggenheim | Combustion chamber |
-
1948
- 1948-02-07 US US7015A patent/US2487435A/en not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2016921A (en) * | 1930-02-19 | 1935-10-08 | Robert H Goddard | Means for cooling combustion chambers |
US2405785A (en) * | 1944-03-14 | 1946-08-13 | Daniel And Florence Guggenheim | Combustion chamber |
Cited By (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2776537A (en) * | 1953-04-20 | 1957-01-08 | Adolphe C Peterson | Fuel supply and control means for turbines and turbine jets |
US3134224A (en) * | 1961-05-26 | 1964-05-26 | United Aircraft Corp | Gas bleed from rocket chamber |
US3266241A (en) * | 1963-07-29 | 1966-08-16 | United Aircraft Corp | Propellant injector |
US3595023A (en) * | 1967-01-16 | 1971-07-27 | Bolkow Gmbh | Rocket engine combustion chamber cooling |
US4108241A (en) * | 1975-03-19 | 1978-08-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Heat exchanger and method of making |
EP0604279A1 (en) * | 1992-12-24 | 1994-06-29 | Societe Europeenne De Propulsion | Injector with porous wall for a rocket combustion chamber |
FR2699963A1 (en) * | 1992-12-24 | 1994-07-01 | Europ Propulsion | Close combustion gas generator. |
US5438834A (en) * | 1992-12-24 | 1995-08-08 | Societe Europeenne De Propulsion | Close combustion gas generator |
US6598398B2 (en) | 1995-06-07 | 2003-07-29 | Clean Energy Systems, Inc. | Hydrocarbon combustion power generation system with CO2 sequestration |
US6389814B2 (en) | 1995-06-07 | 2002-05-21 | Clean Energy Systems, Inc. | Hydrocarbon combustion power generation system with CO2 sequestration |
US7043920B2 (en) | 1995-06-07 | 2006-05-16 | Clean Energy Systems, Inc. | Hydrocarbon combustion power generation system with CO2 sequestration |
US6523349B2 (en) | 2000-03-22 | 2003-02-25 | Clean Energy Systems, Inc. | Clean air engines for transportation and other power applications |
US6622470B2 (en) | 2000-05-12 | 2003-09-23 | Clean Energy Systems, Inc. | Semi-closed brayton cycle gas turbine power systems |
US6637183B2 (en) | 2000-05-12 | 2003-10-28 | Clean Energy Systems, Inc. | Semi-closed brayton cycle gas turbine power systems |
US6824710B2 (en) | 2000-05-12 | 2004-11-30 | Clean Energy Systems, Inc. | Working fluid compositions for use in semi-closed brayton cycle gas turbine power systems |
US6910335B2 (en) | 2000-05-12 | 2005-06-28 | Clean Energy Systems, Inc. | Semi-closed Brayton cycle gas turbine power systems |
US6868677B2 (en) | 2001-05-24 | 2005-03-22 | Clean Energy Systems, Inc. | Combined fuel cell and fuel combustion power generation systems |
US6945029B2 (en) | 2002-11-15 | 2005-09-20 | Clean Energy Systems, Inc. | Low pollution power generation system with ion transfer membrane air separation |
US7021063B2 (en) | 2003-03-10 | 2006-04-04 | Clean Energy Systems, Inc. | Reheat heat exchanger power generation systems |
US7882692B2 (en) | 2004-04-16 | 2011-02-08 | Clean Energy Systems, Inc. | Zero emissions closed rankine cycle power system |
US20110000981A1 (en) * | 2006-06-20 | 2011-01-06 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. | Injection head, mixing space and power unit |
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