US3052090A - Heat shield and nozzle seal for rocket nozzles - Google Patents
Heat shield and nozzle seal for rocket nozzles Download PDFInfo
- Publication number
- US3052090A US3052090A US775325A US77532558A US3052090A US 3052090 A US3052090 A US 3052090A US 775325 A US775325 A US 775325A US 77532558 A US77532558 A US 77532558A US 3052090 A US3052090 A US 3052090A
- Authority
- US
- United States
- Prior art keywords
- plate
- heat shield
- inserts
- nozzle seal
- wells
- 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
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
-
- 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
Definitions
- This invention is directed to rocket motors; more specifically it relates to improvements in discharge nozzles.
- FIG. 1 is a plan view of a nozzle plate
- FIG. 2 is a cross-sectional elevational view of the nozzle plate taken along line 22 of FIG. 1.
- FIGS. 1 and 2 there is shown in FIGS. 1 and 2 a plate 11 having an annular skirt portion, a centrally positioned threaded hole, and a plurality of wells 16 depending from the side having the skirt portion.
- exit ports corresponding to the wells 16 and centrally positioned with respect thereto, each exit port having a beveled surface 12.
- tubular erosion-resistant inserts 13 Positioned inside the wells 16 and contacting the surfaces thereof are tubular erosion-resistant inserts 13 having beveled surfaces 14 and 15; inserts 13 are secured inside the wells by shims 17.
- Surfaces 12 and 14 are beveled so as to form a smooth continuous diverging conduit.
- a heat shield 18 having apertures corresponding to the apertures of plate 11 is securely positioned inside the skirt portion and in contact with the face of plate 11.
- the apertures of shield 18 corresponding to the openings in the erosion-resistant inserts may be beveled if desired to form a smooth continuous surface with beveled surface 15 of the insert, but if not done, has no appreciable eifect.
- the heat shield 18 is made of a thermosetting resin, preferably a phenol-formaldehyde resin having a low degree of polymerization which incorporates up to 70% of a filler.
- the filler is preferably chopped glass or asbestos fibers although other suitable materials may be used.
- Inserts 13 are made of graphite, a refractory metal, or certain metal oxides, all well known for their resistance to erosion.
- Plate 11 is conventional and made of steel, as are shims 17 which are integral therewith.
- the nozzle plate is made by first machining plate 11, then inserting the inserts 13 and staking them down by the use of shims 17. Then the shield 18 is simply pressed in position; it can be bonded to the face of plate 11 if desired. Shield 18 is bonded by merely coating it with some of the uncured resin, placing it in position and heating until the resin is cured. Rupture diaphragms which seal the discharge ports hermetically are molded in place similarly.
- the nozzle plate is simply screwed into position at the end of the combustion chamber.
- a nozzle plate assembly for rocket motors comprising a metal plate having an annular skirt portion and a plurality of wells in the side of the plate having the skirt portion, said plate having exit ports on the unskirted side of the plate corresponding to said wells, an insert positioned within each of said wells and secured therein by a shim, a heat shield having apertures corresponding to the wells and ports of said plate, said heat shield being pressed into position inside the skirt portion of the plate against said plate and inserts and covering the junction therebetween, whereby the shield protects the junction between the inserts and the plate from the combustion products of the rocket motor.
- a rocket nozzle plate comprising a metal plate having a plurality of exit ports and an annular skirt portion, said skirt portion having a plurality of wells therein corresponding to and in alignment with said ports, and a tubular erosion-resistant insert secured within each of said wells; the improvement which comprises a thermosetting resin heat shield coving the upstream ends of said inserts and the junctions between the inserts and said plates; said plate having a plurality of openings corresponding to the upstream openings of said inserts and bonded to said plate within the skirt portion.
Description
Sept. 4, 1962 s. H. HERZOG 3,052,090
HEAT SHIELD AND NOZZLE SEAL FOR ROCKET NOZZLES Filed. Nov. 20, 1958 INVENTOR. STEPHEN H. HERZOG ATTORN EYS.
3,052,090 HEAT S @l t 1.1) AND NQZZLE SEAL FOR ROCKET NOZZLES Stephen H. Herzog, China Lake, Calif., assignor to the United States of America as represented by the Secretary of the Navy Filed Nov. 20, 1958, Ser. No. 775,325 2 Claims. (Cl. 60-356) (Granted under Title 35, US. Code (1952), sec. 266) The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
This invention is directed to rocket motors; more specifically it relates to improvements in discharge nozzles.
Steel nozzles have been used successfully in the past with the propellants then in use. At present, it is common to place an insert of erosion-resistant material in the constricted or throat portion of the nozzle where the most erosion occurs. However, some of the propellants in use today are so energetic that the steel surrounding the insert is eroded away by the hot exhaust gases and the insert is expelled during the burning of the propellant.
It is therefore an object of this invention to provide a nozzle plate with an insert which will not be expelled during the operation of the motor.
With this and further objects in view, as will hereinafter more fully appear, and which will be more particularly pointed out in the appended claims, reference is now made to the following description taken in connection with the accompanying drawings in which:
FIG. 1 is a plan view of a nozzle plate, and
FIG. 2 is a cross-sectional elevational view of the nozzle plate taken along line 22 of FIG. 1.
Referring now to the drawing wherein like reference numerals designate like or corresponding parts throughout the several views, there is shown in FIGS. 1 and 2 a plate 11 having an annular skirt portion, a centrally positioned threaded hole, and a plurality of wells 16 depending from the side having the skirt portion. On the opposite side of plate 11 are exit ports corresponding to the wells 16 and centrally positioned with respect thereto, each exit port having a beveled surface 12. Positioned inside the wells 16 and contacting the surfaces thereof are tubular erosion-resistant inserts 13 having beveled surfaces 14 and 15; inserts 13 are secured inside the wells by shims 17. Surfaces 12 and 14 are beveled so as to form a smooth continuous diverging conduit. A heat shield 18 having apertures corresponding to the apertures of plate 11 is securely positioned inside the skirt portion and in contact with the face of plate 11.
The apertures of shield 18 corresponding to the openings in the erosion-resistant inserts may be beveled if desired to form a smooth continuous surface with beveled surface 15 of the insert, but if not done, has no appreciable eifect.
The heat shield 18 is made of a thermosetting resin, preferably a phenol-formaldehyde resin having a low degree of polymerization which incorporates up to 70% of a filler. The filler is preferably chopped glass or asbestos fibers although other suitable materials may be used.
3,852,090 Patented Sept. 4, 1962 Inserts 13 are made of graphite, a refractory metal, or certain metal oxides, all well known for their resistance to erosion.
Plate 11 is conventional and made of steel, as are shims 17 which are integral therewith. The nozzle plate is made by first machining plate 11, then inserting the inserts 13 and staking them down by the use of shims 17. Then the shield 18 is simply pressed in position; it can be bonded to the face of plate 11 if desired. Shield 18 is bonded by merely coating it with some of the uncured resin, placing it in position and heating until the resin is cured. Rupture diaphragms which seal the discharge ports hermetically are molded in place similarly.
After assembly, the nozzle plate is simply screwed into position at the end of the combustion chamber.
A number of the instant nozzle plates have been tested under the same conditions which caused conventional steel nozzle plates to expel their erosion-resistant inserts and no such expulsion occured.
Obviously, many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.
What is claimed is:
l. A nozzle plate assembly for rocket motors, comprising a metal plate having an annular skirt portion and a plurality of wells in the side of the plate having the skirt portion, said plate having exit ports on the unskirted side of the plate corresponding to said wells, an insert positioned within each of said wells and secured therein by a shim, a heat shield having apertures corresponding to the wells and ports of said plate, said heat shield being pressed into position inside the skirt portion of the plate against said plate and inserts and covering the junction therebetween, whereby the shield protects the junction between the inserts and the plate from the combustion products of the rocket motor.
2. In a rocket nozzle plate comprising a metal plate having a plurality of exit ports and an annular skirt portion, said skirt portion having a plurality of wells therein corresponding to and in alignment with said ports, and a tubular erosion-resistant insert secured within each of said wells; the improvement which comprises a thermosetting resin heat shield coving the upstream ends of said inserts and the junctions between the inserts and said plates; said plate having a plurality of openings corresponding to the upstream openings of said inserts and bonded to said plate within the skirt portion.
References Cited in the file of this patent UNITED STATES PATENTS 2,755,620 Gillot July 24, 1956 2,759,326 Brandt Aug. 21, 1956 2,762,193 Johnson Sept. 11, 1956 2,816,418 Loedding Dec. 17, 1957 2,835,107 Ward May 20, 1958 2,849,860 Lowe Sept. 2, 1958 2,958,184 Sanders Nov. 1, 1960 2,968,919 Hughes et al J an. 24, 1961 2,987,874 Nicholson June 13, 1961
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US775325A US3052090A (en) | 1958-11-20 | 1958-11-20 | Heat shield and nozzle seal for rocket nozzles |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US775325A US3052090A (en) | 1958-11-20 | 1958-11-20 | Heat shield and nozzle seal for rocket nozzles |
Publications (1)
Publication Number | Publication Date |
---|---|
US3052090A true US3052090A (en) | 1962-09-04 |
Family
ID=25104050
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US775325A Expired - Lifetime US3052090A (en) | 1958-11-20 | 1958-11-20 | Heat shield and nozzle seal for rocket nozzles |
Country Status (1)
Country | Link |
---|---|
US (1) | US3052090A (en) |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3237402A (en) * | 1963-11-14 | 1966-03-01 | Steverding Bernard | Variable thrust nozzle |
US3372548A (en) * | 1965-06-17 | 1968-03-12 | Thiokol Chemical Corp | Rocket nozzle |
US3459701A (en) * | 1964-01-07 | 1969-08-05 | Martin Marietta Corp | Ceramic filled plastic system |
US4091709A (en) * | 1976-07-26 | 1978-05-30 | The United States Of America As Represented By The Secretary Of The Army | Recoilless rifle nozzle |
US4150540A (en) * | 1977-04-14 | 1979-04-24 | The United States Of America As Represented By The Secretary Of The Air Force | Rocket nozzle system |
DE3246540A1 (en) * | 1982-12-16 | 1984-06-20 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | PUSH-NOZZLE ARRANGEMENT FOR ADJUSTING THE PUSH-NOZZLE CROSS-SECTION OF RECOMBUSED POWER PLANTS FOR AIRCRAFT |
US4793426A (en) * | 1986-11-26 | 1988-12-27 | Millsapps Jr Stuart C | Drill bit with covered ring nozzle retainer |
US20040084566A1 (en) * | 2002-11-06 | 2004-05-06 | Daniel Chasman | Multi-nozzle grid missile propulsion system |
US20050011989A1 (en) * | 2002-11-07 | 2005-01-20 | Daniel Chasman | Missile control system and method |
US20060284006A1 (en) * | 2005-04-25 | 2006-12-21 | Chasman Daniel B | Missile control system and method |
US20090229241A1 (en) * | 2008-03-07 | 2009-09-17 | Haight Stephen D | Hybrid missile propulsion system with reconfigurable multinozzle grid |
US20100313544A1 (en) * | 2006-11-06 | 2010-12-16 | Daniel Chasman | Propulsion system with canted multinozzle grid |
US20120233979A1 (en) * | 2011-03-16 | 2012-09-20 | Raytheon Company | Rocket multi-nozzle grid assembly and methods for maintaining pressure and thrust profiles with the same |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2755620A (en) * | 1951-02-08 | 1956-07-24 | Brandt Soc Nouv Ets | Rocket motor |
US2759326A (en) * | 1953-03-14 | 1956-08-21 | Energa | Powder reactor including a perforated conical grid |
US2762193A (en) * | 1953-02-03 | 1956-09-11 | Scaife Company | Welded end closure means for rocket motors |
US2816418A (en) * | 1954-08-18 | 1957-12-17 | Unexcelled Chemical Corp | Shaped propellant charges for solidfuel rocket type motors |
US2835107A (en) * | 1956-12-21 | 1958-05-20 | Haveg Industries Inc | Resins and use thereof |
US2849860A (en) * | 1955-10-17 | 1958-09-02 | Norton Co | Rocket motor with recrystallized silicon carbide throat insert |
US2958184A (en) * | 1950-10-17 | 1960-11-01 | Aerojet General Co | Jet propulsion motor with safety pressure relief means |
US2968919A (en) * | 1957-03-25 | 1961-01-24 | Hughes Aircraft Co | Variable area nozzle |
US2987874A (en) * | 1954-03-15 | 1961-06-13 | Carborundum Co | Ceramic lined, light weight rocket motor nozzles and like devices |
-
1958
- 1958-11-20 US US775325A patent/US3052090A/en not_active Expired - Lifetime
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2958184A (en) * | 1950-10-17 | 1960-11-01 | Aerojet General Co | Jet propulsion motor with safety pressure relief means |
US2755620A (en) * | 1951-02-08 | 1956-07-24 | Brandt Soc Nouv Ets | Rocket motor |
US2762193A (en) * | 1953-02-03 | 1956-09-11 | Scaife Company | Welded end closure means for rocket motors |
US2759326A (en) * | 1953-03-14 | 1956-08-21 | Energa | Powder reactor including a perforated conical grid |
US2987874A (en) * | 1954-03-15 | 1961-06-13 | Carborundum Co | Ceramic lined, light weight rocket motor nozzles and like devices |
US2816418A (en) * | 1954-08-18 | 1957-12-17 | Unexcelled Chemical Corp | Shaped propellant charges for solidfuel rocket type motors |
US2849860A (en) * | 1955-10-17 | 1958-09-02 | Norton Co | Rocket motor with recrystallized silicon carbide throat insert |
US2835107A (en) * | 1956-12-21 | 1958-05-20 | Haveg Industries Inc | Resins and use thereof |
US2968919A (en) * | 1957-03-25 | 1961-01-24 | Hughes Aircraft Co | Variable area nozzle |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3237402A (en) * | 1963-11-14 | 1966-03-01 | Steverding Bernard | Variable thrust nozzle |
US3459701A (en) * | 1964-01-07 | 1969-08-05 | Martin Marietta Corp | Ceramic filled plastic system |
US3372548A (en) * | 1965-06-17 | 1968-03-12 | Thiokol Chemical Corp | Rocket nozzle |
US4091709A (en) * | 1976-07-26 | 1978-05-30 | The United States Of America As Represented By The Secretary Of The Army | Recoilless rifle nozzle |
US4150540A (en) * | 1977-04-14 | 1979-04-24 | The United States Of America As Represented By The Secretary Of The Air Force | Rocket nozzle system |
DE3246540A1 (en) * | 1982-12-16 | 1984-06-20 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | PUSH-NOZZLE ARRANGEMENT FOR ADJUSTING THE PUSH-NOZZLE CROSS-SECTION OF RECOMBUSED POWER PLANTS FOR AIRCRAFT |
US4793426A (en) * | 1986-11-26 | 1988-12-27 | Millsapps Jr Stuart C | Drill bit with covered ring nozzle retainer |
US20040084566A1 (en) * | 2002-11-06 | 2004-05-06 | Daniel Chasman | Multi-nozzle grid missile propulsion system |
US20050011989A1 (en) * | 2002-11-07 | 2005-01-20 | Daniel Chasman | Missile control system and method |
US7108223B2 (en) | 2002-11-07 | 2006-09-19 | Raytheon Company | Missile control system and method |
US20060284006A1 (en) * | 2005-04-25 | 2006-12-21 | Chasman Daniel B | Missile control system and method |
US7287725B2 (en) | 2005-04-25 | 2007-10-30 | Raytheon Company | Missile control system and method |
US20100313544A1 (en) * | 2006-11-06 | 2010-12-16 | Daniel Chasman | Propulsion system with canted multinozzle grid |
US7856806B1 (en) | 2006-11-06 | 2010-12-28 | Raytheon Company | Propulsion system with canted multinozzle grid |
US20090229241A1 (en) * | 2008-03-07 | 2009-09-17 | Haight Stephen D | Hybrid missile propulsion system with reconfigurable multinozzle grid |
US8117847B2 (en) | 2008-03-07 | 2012-02-21 | Raytheon Company | Hybrid missile propulsion system with reconfigurable multinozzle grid |
US20120233979A1 (en) * | 2011-03-16 | 2012-09-20 | Raytheon Company | Rocket multi-nozzle grid assembly and methods for maintaining pressure and thrust profiles with the same |
US8596040B2 (en) * | 2011-03-16 | 2013-12-03 | Raytheon Company | Rocket multi-nozzle grid assembly and methods for maintaining pressure and thrust profiles with the same |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3052090A (en) | Heat shield and nozzle seal for rocket nozzles | |
US2968919A (en) | Variable area nozzle | |
US3765297A (en) | Non-eroding, lightweight cartridge cases | |
US3038303A (en) | Thrust termination in solid propellant rockets | |
US2912820A (en) | Combined ram jet and rocket engine | |
US3052091A (en) | Apparatus for cutting off thrust of a rocket motor | |
CA1079078A (en) | Rocket nozzle assembly | |
US3768255A (en) | Inlet port covers for reaction vehicle | |
Green Jr | Erosive burning of some composite solid propellants | |
US3048970A (en) | Plastic nozzle plate for missile motors | |
US4150540A (en) | Rocket nozzle system | |
US3304865A (en) | Self-sealing, unbonded, rocket motor nozzle closure | |
US3132475A (en) | Hybrid rocket propulsion system | |
US2949009A (en) | Variable thrust solid propellant rocket motor | |
US3296799A (en) | Thrust vector control system | |
US4154141A (en) | Ultrafast, linearly-deflagration ignition system | |
US3786993A (en) | Control systems for rocket motors | |
US2897649A (en) | Igniter | |
US3394549A (en) | Step nozzle | |
US3691955A (en) | Stress relieved grains | |
US5419119A (en) | High pressure slab motor | |
US3004734A (en) | Hydraulic power supply | |
US2963975A (en) | Cloud seeding carbon dioxide bullet | |
US3434419A (en) | Rocket assisted projectile with movable piston base plate | |
US2995009A (en) | Closure for rocket case |