US2962221A - Rocket nozzle construction with cooling means - Google Patents
Rocket nozzle construction with cooling means Download PDFInfo
- Publication number
- US2962221A US2962221A US812716A US81271659A US2962221A US 2962221 A US2962221 A US 2962221A US 812716 A US812716 A US 812716A US 81271659 A US81271659 A US 81271659A US 2962221 A US2962221 A US 2962221A
- Authority
- US
- United States
- Prior art keywords
- passage
- nozzle
- coolant
- ring
- nozzle construction
- 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
- 238000010276 construction Methods 0.000 title description 13
- 238000001816 cooling Methods 0.000 title description 7
- 239000000463 material Substances 0.000 description 22
- 239000002826 coolant Substances 0.000 description 13
- 239000012809 cooling fluid Substances 0.000 description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 3
- 229910052802 copper Inorganic materials 0.000 description 3
- 239000010949 copper Substances 0.000 description 3
- 239000011148 porous material Substances 0.000 description 3
- 239000011324 bead Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 210000004243 sweat Anatomy 0.000 description 2
- 230000005068 transpiration Effects 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000009969 flowable effect Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910017604 nitric acid Inorganic materials 0.000 description 1
- 235000002020 sage Nutrition 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 210000002268 wool Anatomy 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
- F02K9/97—Rocket nozzles
- F02K9/972—Fluid cooling arrangements for nozzles
-
- 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
- Y10S60/909—Reaction motor or component composed of specific material
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49346—Rocket or jet device making
Definitions
- the present invention relates to a nozzle arrangement for rockets and the like.
- One feature of the invention is an arrangement for cooling the nozzle especially at the throat by means of transpiration or sweat cooling and for supplying a cooling fluid to the nozzle passage.
- Another feature is a nozzle of porous material with coolant passages therein of greater porosity than the nozzle to assure a passage for coolant to all portions of the nozzle.
- Another feature is the reenforcement of the nozzle material so that it will stand the pressures thereon.
- Fig. l is a longitudinal sectional view through a nozzle embodying the invention.
- Fig. 2 is a fragmentary sectional view similar to Fig. 1 on a larger scale.
- the nozzle is made up of a sleeve 2 of high strength material which is attached to or integral with the body 4 of the combustion chamber of the rocket.
- This sleeve which is somewhat shorter than the nozzle structure itself may have a plurality of annular radially inwardly extending fins 6 on the inner wall which are axially spaced apart, as shown.
- the flow path through the nozzle is defined by an annulus of low porosity material which is in engagement with the inner surface of the sleeve 2 and which has an axial passage therein which forms the convergent portion 10, the throat 12 and divergent portion 14 of the flow passage through the nozzle.
- This low porosity mate rial may be of sintered aluminum or other metal or of other material as silicon carbide although other materials with the desired porosity may be equally satisfactory.
- a spiral passage 16 Formed within the annulus 8 and extending parallel to the inner wall of the annulus is a spiral passage 16, the successive convolutions of which are closely adjacent to each other.
- This passage is filled with a high porosity material such as metallic or plastic beads or steel wool or other equally suitable material preferably made up of discrete elements.
- Coolant is introduced to one end of the spiral passage as by the coolant inlet pipe 18 and any coolant not used within the nozzle may be discharged through a pipe 20.
- this coolant may be a liquid fuel and accordingly, the pipe 20 would be connected into the fuel system.
- the coolant As the coolant enters the spiral passage under pressure it will flow along the spiral passage losing coolant into the less porous material of the annulus 8 and this coolant passes through the material of the annulus and cools the surface of the nozzle passage thereby elfecting transpiration or sweat cooling.
- the pressure drop in the coolant passage will match approximately the pressure drop through the nozzle to assure an adequate and uniform flow of the coolant over the entire wall surface.
- the spiral passage 16 may be formed within the ring 8 by using a copper tube as a core for the passage and forming the material of the ring 8 around the copper tube, in a mold.
- the material of the ring 8 is then sintered at the necessary high temperature and the copper tube core is then removed by dissolving it as with nitric acid.
- the resulting passage 16 may then be blown or poured full with beads or other flowable high porosity material.
- the annulus 8 may be made up of a plurality of angular segments in which event the passages 16 may be formed in the individual segments to line up with each other. With this arrangement, it will be understood that the resulting passage 16 would be only approximately spiral since the portions of the passage in each segment would be straight. Other methods of construction will be apparent from the description of these two possible methods.
- a nozzle construction including a ring of a low porosity material and having an axial passage therein forming a nozzle throat, small circumferentially extending passages within said ring and positioned substantially concentric to said axial passage, and a material of higher porosity in said smaller passages.
- a nozzle construction including a ring of low porosity material having an axial passage therein for the flow of a propellant gas therethrough, a substantially spiral passage within said ring and extending in substantially parallel relation to the wall of the axial passage therein and means for delivering a coolant to said spiral passage to be discharged through the low porosity material to the surface of the axial passage.
- a nozzle construction including a ring of low porosity material having an axial passage therein for the flow of a propellant gas therethrough, a substantially spiral passage in said porous material and extending substantially parallel to the wall of the axial passage therein, and a material of higher porosity in said spiral passage.
- a nozzle construction including a ring of a low porosity material and having an axial passage therein forming a nozzle throat, smaller circumferentially extending passages within said ring and substantially concentric to said axial passage, a material of higher porosity in said smaller passages, and a metallic ring surrounding said first ring and in contact therewith for reenforcement of said first ring.
- a nozzle construction as in claim 4 in which the axial passage forms a convergent portion, a threat portion and a divergent portion and in which the smaller passages are adjacent to but substantially uniformly spaced from the surfaces of the axial passage.
- a nozzle construction as in claim 4 in which means are provided for delivering a cooling fluid to the smaller passages.
- a nozzle construction as in claim 4 in which the smaller passages form a continuous spiral passage and in which a cooling fluid is delivered to said spiral passage.
- a nozzle construction as in claim 4 in which the material of high porosity permits a substantial flow therearound through the small passages and in which the low porosity material permits a fiow from the small passages to the surface of the axial passage.
- a nozzle construction as in claim 4 in which the smaller passages form a continuous spiral passage and in which cooling fluid is delivered to the end of the spiral Patented Nov. 2 11 3 passage adjacent to th upstream and of the axial pas- 2,594,735 sage. 2,862,828
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Description
H. R. KUNZ Nov. 29, 1960 ROCKET NOZZLE CONSTRUCTION WITH COOLING MEANS Filed ma 12. 1959 INVENTOR T ZAROLD R. KUNZ BY ATTORNL') Unite States Patent ROCKET NOZZLE CONSTRUCTION WITH COOLING MEANS Harold R. Kuuz, Warehouse Point, Conn., assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware Filed May 12, 1959, Ser. No. 812,716
9 Claims. (Cl. 239-432) The present invention relates to a nozzle arrangement for rockets and the like.
One feature of the invention is an arrangement for cooling the nozzle especially at the throat by means of transpiration or sweat cooling and for supplying a cooling fluid to the nozzle passage. Another feature is a nozzle of porous material with coolant passages therein of greater porosity than the nozzle to assure a passage for coolant to all portions of the nozzle. Another feature is the reenforcement of the nozzle material so that it will stand the pressures thereon.
Other features and advantages will be apparent from the specification and claims, and from the accompanying drawings which illustrate an embodiment of the invention.
Fig. l is a longitudinal sectional view through a nozzle embodying the invention.
Fig. 2 is a fragmentary sectional view similar to Fig. 1 on a larger scale.
The nozzle, as shown, is made up of a sleeve 2 of high strength material which is attached to or integral with the body 4 of the combustion chamber of the rocket. This sleeve which is somewhat shorter than the nozzle structure itself may have a plurality of annular radially inwardly extending fins 6 on the inner wall which are axially spaced apart, as shown.
The flow path through the nozzle is defined by an annulus of low porosity material which is in engagement with the inner surface of the sleeve 2 and which has an axial passage therein which forms the convergent portion 10, the throat 12 and divergent portion 14 of the flow passage through the nozzle. This low porosity mate rial may be of sintered aluminum or other metal or of other material as silicon carbide although other materials with the desired porosity may be equally satisfactory.
Formed within the annulus 8 and extending parallel to the inner wall of the annulus is a spiral passage 16, the successive convolutions of which are closely adjacent to each other. This passage is filled with a high porosity material such as metallic or plastic beads or steel wool or other equally suitable material preferably made up of discrete elements.
Coolant is introduced to one end of the spiral passage as by the coolant inlet pipe 18 and any coolant not used within the nozzle may be discharged through a pipe 20. Obviously, this coolant may be a liquid fuel and accordingly, the pipe 20 would be connected into the fuel system. As the coolant enters the spiral passage under pressure it will flow along the spiral passage losing coolant into the less porous material of the annulus 8 and this coolant passes through the material of the annulus and cools the surface of the nozzle passage thereby elfecting transpiration or sweat cooling.
The pressure drop in the coolant passage will match approximately the pressure drop through the nozzle to assure an adequate and uniform flow of the coolant over the entire wall surface. With this arrangement, if the portion of the annulus 8 between the coolant passage and ice 2 the nozzle wall surface should become plugged to any extent, cooling would still be continued through the spiral passage.
The spiral passage 16 may be formed within the ring 8 by using a copper tube as a core for the passage and forming the material of the ring 8 around the copper tube, in a mold. The material of the ring 8 is then sintered at the necessary high temperature and the copper tube core is then removed by dissolving it as with nitric acid. The resulting passage 16 may then be blown or poured full with beads or other flowable high porosity material.
Alternatively, the annulus 8 may be made up of a plurality of angular segments in which event the passages 16 may be formed in the individual segments to line up with each other. With this arrangement, it will be understood that the resulting passage 16 would be only approximately spiral since the portions of the passage in each segment would be straight. Other methods of construction will be apparent from the description of these two possible methods.
It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described, but may beused in other ways without departure from its spirit as defined by the following claims.
I claim:
1. A nozzle construction including a ring of a low porosity material and having an axial passage therein forming a nozzle throat, small circumferentially extending passages within said ring and positioned substantially concentric to said axial passage, and a material of higher porosity in said smaller passages.
2. A nozzle construction including a ring of low porosity material having an axial passage therein for the flow of a propellant gas therethrough, a substantially spiral passage within said ring and extending in substantially parallel relation to the wall of the axial passage therein and means for delivering a coolant to said spiral passage to be discharged through the low porosity material to the surface of the axial passage.
3. A nozzle construction including a ring of low porosity material having an axial passage therein for the flow of a propellant gas therethrough, a substantially spiral passage in said porous material and extending substantially parallel to the wall of the axial passage therein, and a material of higher porosity in said spiral passage.
4. A nozzle construction including a ring of a low porosity material and having an axial passage therein forming a nozzle throat, smaller circumferentially extending passages within said ring and substantially concentric to said axial passage, a material of higher porosity in said smaller passages, and a metallic ring surrounding said first ring and in contact therewith for reenforcement of said first ring.
5. A nozzle construction as in claim 4 in which the axial passage forms a convergent portion, a threat portion and a divergent portion and in which the smaller passages are adjacent to but substantially uniformly spaced from the surfaces of the axial passage.
6. A nozzle construction as in claim 4 in which means are provided for delivering a cooling fluid to the smaller passages.
7. A nozzle construction as in claim 4 in which the smaller passages form a continuous spiral passage and in which a cooling fluid is delivered to said spiral passage.
8. A nozzle construction as in claim 4 in which the material of high porosity permits a substantial flow therearound through the small passages and in which the low porosity material permits a fiow from the small passages to the surface of the axial passage.
9. A nozzle construction as in claim 4 in which the smaller passages form a continuous spiral passage and in which cooling fluid is delivered to the end of the spiral Patented Nov. 2 11 3 passage adjacent to th upstream and of the axial pas- 2,594,735 sage. 2,862,828
References Cited in the file of this patent UNITED STATES PATENTS l 5 874,469
2,354,151 Skoglund Jlily 18, 1 924 4 Crumley Apr. 29, 1952 Glaser Dec. 2, 1958 FOREIGN PATENTS France May 4, 1942
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US812716A US2962221A (en) | 1959-05-12 | 1959-05-12 | Rocket nozzle construction with cooling means |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US812716A US2962221A (en) | 1959-05-12 | 1959-05-12 | Rocket nozzle construction with cooling means |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2962221A true US2962221A (en) | 1960-11-29 |
Family
ID=25210416
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US812716A Expired - Lifetime US2962221A (en) | 1959-05-12 | 1959-05-12 | Rocket nozzle construction with cooling means |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2962221A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3073683A (en) * | 1959-08-25 | 1963-01-15 | Collier Carbon & Chemical Co | Apparatus for submerged combustion heating of liquids |
| US3122883A (en) * | 1959-11-20 | 1964-03-03 | Thompson Ramo Wooldridge Inc | Heat resistant wall structure for rocket motor nozzles and the like |
| US3129560A (en) * | 1960-06-13 | 1964-04-21 | Stanley P Prosen | Convectively cooled rocket nozzle |
| US3188801A (en) * | 1961-09-29 | 1965-06-15 | Gen Motors Corp | Cooled nozzle construction |
| US3230705A (en) * | 1962-07-11 | 1966-01-25 | Trw Inc | Chemically cooled rocket |
| US3304008A (en) * | 1963-06-24 | 1967-02-14 | Gen Motors Corp | Temperature responsive rocket nozzle cooling system |
| US3373904A (en) * | 1966-05-05 | 1968-03-19 | Gillette Co | Heater for material dispensed from a container |
| US3378204A (en) * | 1966-01-14 | 1968-04-16 | Thiokol Chemical Corp | Nozzle |
| US5174368A (en) * | 1990-07-13 | 1992-12-29 | Societe Europeenne De Propulsion | Cooled refractory structure and manufacturing process therefor |
| US20060140780A1 (en) * | 2003-06-20 | 2006-06-29 | John Stark | Double cone for generation of a pressure difference |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR874469A (en) * | 1940-08-03 | 1942-08-07 | Bosch Gmbh Robert | Injector cooled, especially liquid controlled, for internal combustion engines |
| US2354151A (en) * | 1942-04-16 | 1944-07-18 | United Aircraft Corp | Fluid nozzle |
| US2594735A (en) * | 1949-04-12 | 1952-04-29 | Ernest W Crumley | Angle head abrasive blast nozzle |
| US2862828A (en) * | 1955-11-14 | 1958-12-02 | Borolite Corp | Hot strength corrosion resistant material and production thereof |
-
1959
- 1959-05-12 US US812716A patent/US2962221A/en not_active Expired - Lifetime
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR874469A (en) * | 1940-08-03 | 1942-08-07 | Bosch Gmbh Robert | Injector cooled, especially liquid controlled, for internal combustion engines |
| US2354151A (en) * | 1942-04-16 | 1944-07-18 | United Aircraft Corp | Fluid nozzle |
| US2594735A (en) * | 1949-04-12 | 1952-04-29 | Ernest W Crumley | Angle head abrasive blast nozzle |
| US2862828A (en) * | 1955-11-14 | 1958-12-02 | Borolite Corp | Hot strength corrosion resistant material and production thereof |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3073683A (en) * | 1959-08-25 | 1963-01-15 | Collier Carbon & Chemical Co | Apparatus for submerged combustion heating of liquids |
| US3122883A (en) * | 1959-11-20 | 1964-03-03 | Thompson Ramo Wooldridge Inc | Heat resistant wall structure for rocket motor nozzles and the like |
| US3129560A (en) * | 1960-06-13 | 1964-04-21 | Stanley P Prosen | Convectively cooled rocket nozzle |
| US3188801A (en) * | 1961-09-29 | 1965-06-15 | Gen Motors Corp | Cooled nozzle construction |
| US3230705A (en) * | 1962-07-11 | 1966-01-25 | Trw Inc | Chemically cooled rocket |
| US3304008A (en) * | 1963-06-24 | 1967-02-14 | Gen Motors Corp | Temperature responsive rocket nozzle cooling system |
| US3378204A (en) * | 1966-01-14 | 1968-04-16 | Thiokol Chemical Corp | Nozzle |
| US3373904A (en) * | 1966-05-05 | 1968-03-19 | Gillette Co | Heater for material dispensed from a container |
| US5174368A (en) * | 1990-07-13 | 1992-12-29 | Societe Europeenne De Propulsion | Cooled refractory structure and manufacturing process therefor |
| US20060140780A1 (en) * | 2003-06-20 | 2006-06-29 | John Stark | Double cone for generation of a pressure difference |
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