US3170289A - Lightweight refractory metal structure - Google Patents
Lightweight refractory metal structure Download PDFInfo
- Publication number
- US3170289A US3170289A US207829A US20782962A US3170289A US 3170289 A US3170289 A US 3170289A US 207829 A US207829 A US 207829A US 20782962 A US20782962 A US 20782962A US 3170289 A US3170289 A US 3170289A
- Authority
- US
- United States
- Prior art keywords
- liner
- refractory metal
- tungsten
- strips
- nozzle
- 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
- 239000003870 refractory metal Substances 0.000 title claims description 12
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- 230000003628 erosive effect Effects 0.000 claims description 6
- 229910052721 tungsten Inorganic materials 0.000 description 19
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 18
- 239000010937 tungsten Substances 0.000 description 18
- 239000000463 material Substances 0.000 description 11
- 229910052715 tantalum Inorganic materials 0.000 description 10
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 10
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 150000002739 metals Chemical class 0.000 description 5
- 238000002844 melting Methods 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- NFFIWVVINABMKP-UHFFFAOYSA-N methylidynetantalum Chemical compound [Ta]#C NFFIWVVINABMKP-UHFFFAOYSA-N 0.000 description 3
- 229910003468 tantalcarbide Inorganic materials 0.000 description 3
- 238000013459 approach Methods 0.000 description 2
- WHJFNYXPKGDKBB-UHFFFAOYSA-N hafnium;methane Chemical compound C.[Hf] WHJFNYXPKGDKBB-UHFFFAOYSA-N 0.000 description 2
- 239000000155 melt Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 229920003023 plastic Polymers 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-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
- 239000000919 ceramic Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000003779 heat-resistant material Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000011819 refractory material Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000010959 steel Substances 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
- F02K9/974—Nozzle- linings; Ablative coatings
-
- 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 high temperature structural'materials and methodsof fabricating articles therefrom. More particularly, the invention relates to rocket nozzles formed entirely from refractory metal materials. With the adyent'of solid propellant rocket engines, the extremely high-temperatures and gas yelocities generated resistant, high-strength, lightweight nozzle. 7
- FIG. 2 illustrates more clearlythe construction of the I nozzle wherein a plurality of fstrips 9 of tungsten .or tantalum are joined'by tantalum rivets 10 or arc sprayed tungsten. to the interior lands of. the corrugations 6 to form the inner shell 4.
- the inside liner is then coated with arc sprayed tungsten,
- a further object is to provide a nozzle that will resist the eroding forces of the high velocity gas stream.
- a further object is to provide a method of constructinghafnium carbide or tantalum carbide which forms a coating of erosion resistant material and also joins together.
- the strips of sheet metal may optionally bevacuum sintered.
- the outside corrugations may be filled with suitable ceramicv or plastic to stiffen and provide insulation.
- Theouter shell is attached to the corrugations and the inside diameter may then if desired ;be ground toa smoother surface.
- the apparatus by which the above steps may beper- .formed is not critical nor part of the present invention.
- the corrugator can be any one ofthose commonly available in the art such as one similar to the one disclosed by Pappelendam in U.S. Patent No. 2,746,139.
- the arc sprayed tungsten can be accomplished by electric arc furnaces commonly known or by a' plasma stream apparatus such as that disclosed by Giannini in US. Patent No. 2,922,869. As is Well known, tungsten melts at 6200 F. Though tantalum melts at 5400 F., 800 F; lower, it is more workable at room temperature and is thus easier to construct a nozzle out of this material; Of
- tungsten has proven' most satisfactory and a 0.150, inch coating which was utilized in a solid propellant rocket engine did not come near 7 its melting point.
- the liner is formed of 0.060 tungsten a nozzle that is simple, reliable and relatively inexpensive. 1
- FIG. 1 shows a sectional view of a ment of the invention
- i FIG. 2 illustrates a section of the device taken on the preferred embodi line 2-2 of FIG. 1 looking in the direction of the arrows.
- FIG. 1 a nozzle 3 constructed of an interior shell 4 composed of 'a series of longitudinal strips 4a of tungsten or tantalum.
- corrugated backup liner shown as corrugations 6 on FIG. 2.
- the corrugations can be joinedto an outer liner 7 of suitable material and the spaces between the corrugation and the outside liner can be filled or. tantalum sheet, but the corrugated sheet can be thinner. It should be understood that since the coeflicients of expansion and melting points of these 'two metals are so similar that the liner or-oorrugated backing may be made of either interchangeably, tantalum being preferred for 'uses below 5400 F. and tungsten being required for heats above 5400 F. 7
- the nozzle is constructed completely out of refractory materials of ex tremely high melting point and erosion resistance.
- the mismatch of coeflicientof expansion is obviated since the materials have similar co'efiicients of expansion. 7
- the joining materials are refractory metals, i.e. tantalum rivets or are sprayed tungsten. The are sprayed tungsten can also be used to coat the innersurface of the liner and concomitantly thiscoating will weld the seams between the strips as it formsthe smooth inner surface.
- a refractory metal rocket nozzle capable of withstanding temperatures and gas velocities generated during ignition comprising in combination a plurality of strips of refractory. metals arranged longitudinally to form an inner liner, coating means on said strips of refractory metal to provide erosion resistance and to form a continuous. inner surface, an outer liner; corrugated means supporting said inner liner in spaced relation With-said outer liner, insulating means between said inner and outer liners, and means-attaching said inner liner to said corrugated supporting means.
- a rocket nozzle constructed substantially from re-' fractory metals such as tantalum and tungsten comprising in combination an inner liner composed of a plurality of longitudinal strips of one of said metals, a sprayed coat ing of a material selected from the group consisting of tungsten, hafnium carbide and tantalum carbide on said inner liner, corrugated refractory metal means supporting and insulating said inner liner and means attaching said inner liner to said corrugated support means.
- re-' fractory metals such as tantalum and tungsten comprising in combination an inner liner composed of a plurality of longitudinal strips of one of said metals, a sprayed coat ing of a material selected from the group consisting of tungsten, hafnium carbide and tantalum carbide on said inner liner, corrugated refractory metal means supporting and insulating said inner liner and means attaching said inner liner to said corrugated support means.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Coating By Spraying Or Casting (AREA)
Description
Feb. 23, 1965 B. KRAMER LIGHTWEIGHT REFRACTORY METAL STRUCTURE Filed July 5, 1962 FIG. I
INVENTOR BRUCE E. KRAMER BY 4% W ATTORNEY combustion products of the propellant reaction.
' of expansion.
LIGHTWEIGHT REFRACTORY METAL s STRUCTURE' Bruce E. Kramer, LovelamL-Ohio, assignor to the United States of America as represented by the Secretary of the Navy T Filed July 5, 1962,'Ser. No. 207,829 2 Claims. (Cl. 60.-.-35.6
I The present invention relates to high temperature structural'materials and methodsof fabricating articles therefrom. More particularly, the invention relates to rocket nozzles formed entirely from refractory metal materials. With the adyent'of solid propellant rocket engines, the extremely high-temperatures and gas yelocities generated resistant, high-strength, lightweight nozzle. 7
One of the prior art approaches to solve this problem have created a need fora temperature-resistant, erosionis to construct the nozzle out of standard metals 'such as steel or aluminum and to circulatevarious coolantsaround the external surface. However, this nozzle has not proven UnitedIS ates PatentOf ce 1 l f Patented Feb 23 1965 with suitable heat resistant material 8 such as ceramics.
and plastics.
FIG. 2, illustrates more clearlythe construction of the I nozzle wherein a plurality of fstrips 9 of tungsten .or tantalum are joined'by tantalum rivets 10 or arc sprayed tungsten. to the interior lands of. the corrugations 6 to form the inner shell 4.
The following describes the fabrication; process. Tungsten or. tantalum sheet is hot rolled -througha set of parallel gearswith tapered teeth to providea corrugated sheet which is then formed to the nozzle shape; the corrugations running in a'longitudinal direction. Thesheet.
is then joined by arc'sprayed tungsten or by tantalum rivets, for example. Strips of sheet tungsten ortantalum are then joined to the interior lands of the corrugations;
By longitudinally joining: together the interior lands of the corrugation the inside, liner of the nozzle is formed.
. The inside liner is then coated with arc sprayed tungsten,
' satisfactorysince it was too heavy, and demanded a'complex system to circulate the coolant. The usual approach was to fabricate the body of the rocket nozzle out of light weight insulative material such as graphite or ,plas
tic. Such insulativematerial wasthen coated on its inside surface with a high melting material such as tungsten to resist the temperatures and forces of the expelled A further object is to provide a nozzle that will resist the eroding forces of the high velocity gas stream.
A further object is to provide a method of constructinghafnium carbide or tantalum carbide which forms a coating of erosion resistant material and also joins together.
the strips of sheet metal. The sprayed coating may optionally bevacuum sintered. The outside corrugations may be filled with suitable ceramicv or plastic to stiffen and provide insulation. Theouter shell is attached to the corrugations and the inside diameter may then if desired ;be ground toa smoother surface. a
The apparatus by which the above steps may beper- .formed is not critical nor part of the present invention. The corrugator can be any one ofthose commonly available in the art such as one similar to the one disclosed by Pappelendam in U.S. Patent No. 2,746,139. The arc sprayed tungsten can be accomplished by electric arc furnaces commonly known or by a' plasma stream apparatus such as that disclosed by Giannini in US. Patent No. 2,922,869. As is Well known, tungsten melts at 6200 F. Though tantalum melts at 5400 F., 800 F; lower, it is more workable at room temperature and is thus easier to construct a nozzle out of this material; Of
the spray coated materials, tungsten has proven' most satisfactory and a 0.150, inch coating which was utilized in a solid propellant rocket engine did not come near 7 its melting point. The liner is formed of 0.060 tungsten a nozzle that is simple, reliable and relatively inexpensive. 1
Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the followingdetailed description when considered in connection with the accompanying drawings in which like reference numerals designate like .partsthroughout the figures thereof and wherein: g
FIG. 1 shows a sectional view of a ment of the invention; and i FIG. 2 illustrates a section of the device taken on the preferred embodi line 2-2 of FIG. 1 looking in the direction of the arrows.
Referring now to the drawings there is shown in FIG. 1 a nozzle 3 constructed of an interior shell 4 composed of 'a series of longitudinal strips 4a of tungsten or tantalum.
Since the circumference of the nozzle 3 is considerably reduced at the throat section, the width of longitudinal strips 4a must be correspondingly reduced atthat point, as shown by Dalgleish in US. Patent N0. 2,976,679. Said shell is covered with acoating 5 of erosion resistant material such as tungsten, tantalum carbide and hafnium carbide. The shell is supported by, surrounded by, and
attached to a corrugated backup liner shown as corrugations 6 on FIG. 2. The corrugations can be joinedto an outer liner 7 of suitable material and the spaces between the corrugation and the outside liner can be filled or. tantalum sheet, but the corrugated sheet can be thinner. It should be understood that since the coeflicients of expansion and melting points of these 'two metals are so similar that the liner or-oorrugated backing may be made of either interchangeably, tantalum being preferred for 'uses below 5400 F. and tungsten being required for heats above 5400 F. 7
Thus, it is readily obvious that the nozzle is constructed completely out of refractory materials of ex tremely high melting point and erosion resistance. The mismatch of coeflicientof expansion is obviated since the materials have similar co'efiicients of expansion. 7 Even the joining materialsare refractory metals, i.e. tantalum rivets or are sprayed tungsten. The are sprayed tungsten can also be used to coat the innersurface of the liner and concomitantly thiscoating will weld the seams between the strips as it formsthe smooth inner surface. It should be understood that although the corrugations have been shown to run longitudinally,-it is also permissible to have the corrugations run horizontally and then join the longitudinal strips of refractory metal thereto. 7 p 'Obviously many modifications and variations of the I present invention are possible in light of the above teachings. 'It is, therefore, to be understood that within the scopeof the appended claims, the invention may be practiced otherwise than as specifically described.
What is claimed is: 1. A refractory metal rocket nozzle capable of withstanding temperatures and gas velocities generated during ignition comprising in combination a plurality of strips of refractory. metals arranged longitudinally to form an inner liner, coating means on said strips of refractory metal to provide erosion resistance and to form a continuous. inner surface, an outer liner; corrugated means supporting said inner liner in spaced relation With-said outer liner, insulating means between said inner and outer liners, and means-attaching said inner liner to said corrugated supporting means.
2. A rocket nozzle constructed substantially from re-' fractory metals such as tantalum and tungsten comprising in combination an inner liner composed of a plurality of longitudinal strips of one of said metals, a sprayed coat ing of a material selected from the group consisting of tungsten, hafnium carbide and tantalum carbide on said inner liner, corrugated refractory metal means supporting and insulating said inner liner and means attaching said inner liner to said corrugated support means.
10/40 11/43 4/51 10/52 11/53 l/SS 6/56 9/58 3/61 3/63 Aronson 29157 Egger et al. 29-157 Lubock 6039.69 .Fuller 6035.6 Nicholson 6035.6 Nicholson 60- 356 Rath 6039.69 Lowe 6035.6 Dalgleis-h 6035.6 Witt 6039.69
OTHER REFERENCES SAMUEL LEVINE, Primary Examiner.
ABRAM BLUM, Examiner.
Claims (1)
1. A REFRACTORY METAL ROCKET NOZZLE CAPABLE OF WITHSTANDING TEMPERATURES AND GAS VELOCITIES GENERATED DURING IGNITION COMPRISING IN COMBINATION A PLURALITY OF STRIPS OF REFRACTORY METALS ARRANGED LONGITUDINALLY TO FORM AN INNER LINER, COATING MEANS ON SAID STRIPS OF REFRACTORY METAL TO PROVIDE EROSION RESISTANCE AND TO FORM A CONTINUOUS INNER SURFACE, AN OUTER LINER, CORRUGATED MEANS SUPPORTING SAID INNER LINER IN SPACED RELATION WITH SAID OUTER LINER, INSULATING MEANS BETWEEN SAID INNER AND OUTER LINERS, AND MEANS ATTACHING SAID INNER LINER TO SAID CORRUGATED SUPPORTING MEANS.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US207829A US3170289A (en) | 1962-07-05 | 1962-07-05 | Lightweight refractory metal structure |
| US281853A US3229359A (en) | 1962-07-05 | 1963-04-30 | Method of forming a refractory metal rocket nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US207829A US3170289A (en) | 1962-07-05 | 1962-07-05 | Lightweight refractory metal structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3170289A true US3170289A (en) | 1965-02-23 |
Family
ID=22772153
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US207829A Expired - Lifetime US3170289A (en) | 1962-07-05 | 1962-07-05 | Lightweight refractory metal structure |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3170289A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3321922A (en) * | 1964-10-29 | 1967-05-30 | Jr William T Latto | Small rocket engine |
| US4061162A (en) * | 1976-12-27 | 1977-12-06 | Texaco Inc. | High temperature and shock resistant insulated pipe |
| US4414181A (en) * | 1981-11-02 | 1983-11-08 | The United States Of America As Represented By The Secretary Of The Navy | Gas generator outlet having controlled temperature transition |
| US4644974A (en) * | 1980-09-08 | 1987-02-24 | Dowell Schlumberger Incorporated | Choke flow bean |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2217193A (en) * | 1937-08-12 | 1940-10-08 | Oxweld Acetylene Co | Method of swaging blowpipe nozzles |
| US2334257A (en) * | 1939-01-14 | 1943-11-16 | Linde Air Prod Co | Method of making blowpipe nozzles |
| US2548485A (en) * | 1946-01-09 | 1951-04-10 | Shell Dev | Combustion chamber lining |
| US2614619A (en) * | 1947-10-22 | 1952-10-21 | Selas Corp Of America | Burner and nozzle tip for projecting hot products of combustion |
| US2658332A (en) * | 1951-03-21 | 1953-11-10 | Carborundum Co | Fluid cooled, refractory, ceramic lined rocket structure |
| US2699036A (en) * | 1950-12-09 | 1955-01-11 | Carborundum Co | Ceramic lined, lightweight rocket motor structure and like device |
| US2751188A (en) * | 1950-02-25 | 1956-06-19 | Maschf Augsburg Nuernberg Ag | Ceramic product |
| US2849860A (en) * | 1955-10-17 | 1958-09-02 | Norton Co | Rocket motor with recrystallized silicon carbide throat insert |
| US2976679A (en) * | 1956-12-10 | 1961-03-28 | Robert C Veit | Tubular rocket combustion chamber |
| US3082601A (en) * | 1958-05-08 | 1963-03-26 | Daimler Benz Ag | Rocket combustion chamber |
-
1962
- 1962-07-05 US US207829A patent/US3170289A/en not_active Expired - Lifetime
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2217193A (en) * | 1937-08-12 | 1940-10-08 | Oxweld Acetylene Co | Method of swaging blowpipe nozzles |
| US2334257A (en) * | 1939-01-14 | 1943-11-16 | Linde Air Prod Co | Method of making blowpipe nozzles |
| US2548485A (en) * | 1946-01-09 | 1951-04-10 | Shell Dev | Combustion chamber lining |
| US2614619A (en) * | 1947-10-22 | 1952-10-21 | Selas Corp Of America | Burner and nozzle tip for projecting hot products of combustion |
| US2751188A (en) * | 1950-02-25 | 1956-06-19 | Maschf Augsburg Nuernberg Ag | Ceramic product |
| US2699036A (en) * | 1950-12-09 | 1955-01-11 | Carborundum Co | Ceramic lined, lightweight rocket motor structure and like device |
| US2658332A (en) * | 1951-03-21 | 1953-11-10 | Carborundum Co | Fluid cooled, refractory, ceramic lined rocket structure |
| US2849860A (en) * | 1955-10-17 | 1958-09-02 | Norton Co | Rocket motor with recrystallized silicon carbide throat insert |
| US2976679A (en) * | 1956-12-10 | 1961-03-28 | Robert C Veit | Tubular rocket combustion chamber |
| US3082601A (en) * | 1958-05-08 | 1963-03-26 | Daimler Benz Ag | Rocket combustion chamber |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3321922A (en) * | 1964-10-29 | 1967-05-30 | Jr William T Latto | Small rocket engine |
| US4061162A (en) * | 1976-12-27 | 1977-12-06 | Texaco Inc. | High temperature and shock resistant insulated pipe |
| US4644974A (en) * | 1980-09-08 | 1987-02-24 | Dowell Schlumberger Incorporated | Choke flow bean |
| US4414181A (en) * | 1981-11-02 | 1983-11-08 | The United States Of America As Represented By The Secretary Of The Navy | Gas generator outlet having controlled temperature transition |
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