US3570766A - Integral plug and strut nozzle - Google Patents

Integral plug and strut nozzle Download PDF

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Publication number
US3570766A
US3570766A US791528*A US3570766DA US3570766A US 3570766 A US3570766 A US 3570766A US 3570766D A US3570766D A US 3570766DA US 3570766 A US3570766 A US 3570766A
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nozzle
strut
exhaust
integral
gases
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US791528*A
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Albert W Johnson
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US Department of Navy
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US Department of Navy
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    • 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

Definitions

  • ABSTRACT A one-piece exhaust nozzle for rocket motors. It is substantially cylindrical with three funneled inlet holes at its forward end, blending into a single opening at the aft end. A center body, pyramid shaped, forms a contoured inner wall for the nozzle which has a constantly expanding exhaust area.
  • This invention relates to a plug exhaust nozzle for a rocket motor and more particularly to a nozzle where the exhaust gases are received through three inlets and are recombined in the downstream flow and discharged through a single aft opening.
  • annular exhaust nozzles have been formed of an outer body and a center body, with the center body supported by crossbars or tripodlike arms. These supports interfere with the flow of gases and form crosscurrents in the exhaust which reduce the efficiency of the motor.
  • the inner contour of the nozzle is formed by inserts which makes for leakage of exhaust gases and, by edge interference of these inserts, causes crosscurrents in the flow.
  • the integral molded nozzle is without the possibility of gas leakage, while the form of intersecting elliptical cones reduces the turbulence and provides greater efficiency.
  • An object of the present invention is to provide an exhaust nozzle formed in one piece.
  • Another object of the present invention is to provide an exhaust nozzle having a contoured inner and outer wall, integral, of substantially cylindrical form and so controlling the flow of gases as to prevent any leak path and provide a high thrust.
  • FIG. 1 is a perspective view of the plug and strut nozzle
  • FIG. 2 is a view looking at the aft end of the nozzle
  • FIG. 3 is a view looking at the forward end of the nozzle.
  • the integral plug and strut nozzle has a cylindrical outer wall 12, a forward rim 13 and an aft rim 14.
  • the forward end of the nozzle receives the exhaust gases from the motor and divides these gases to pass the gases through individual distinct throats 15, 16 and 17. Sloping sidewalls 18, 19 and 21, respectively, on the approach side of the throats funnel the gases into the throats.
  • the strut or center body 22 is shaped to recombine the exhaust gases coming through the different throats with the least turbulence. Gas flow from subsonic to supersonic is only disturbed to the extent of flow over an airfoil.
  • the shape of the entire body is that of elliptical cones intersecting and forming at their juncture, a strut or center body, the sides of which are shaped to provide an airfoil construction over which the gases flow.
  • he aft end of the nozzle 1s as though a plane was passed through the intersecting cones, together with the strut at a point beyond the apex of the strut.
  • the arcs of the side of the cones 23, 24 and 25 serve as the outer extremity of the outer wall of the nozzle, while the slopes of the strut or center body forms the inner wall of the nozzle and as these slopes terminate in the apex 26, the gases are progressively expanded in the shortest possible length of nozzle.
  • the integral plug and strut nozzle of the present invention has many advantages over the annular nozzle in use at present. It is less expensive to manufacture.
  • the thrust coefficient proves its high efficiency. There is the highest expansion ratio in the shortest length, the short length allowing a greater length of gain and a consequent greater or longer flight of missile. For low pressure and/or low temperature propellants, the entire nozzle could be molded out of good graphite or carbon molding compound.
  • An integral exhaust nozzle for a rocket motor having a cylindrical outer shape, three inlet openings formed in the forward end of said nozzle to receive exhaust gases from said rocket motor, three separate cone-shaped passages extending from said inlet openings and intersecting to form a single terminal outlet in the aft end of said nozzle where the exhaust gases are recombined, and a substantially pyramid-shaped center body formed by the intersection of said three coneshaped passages.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

A one-piece exhaust nozzle for rocket motors. It is substantially cylindrical with three funneled inlet holes at its forward end, blending into a single opening at the aft end. A center body, pyramid shaped, forms a contoured inner wall for the nozzle which has a constantly expanding exhaust area.

Description

United States Patent Albert W. Johnson Austin, Tex.
Jan. 15, 1969 Mar. 1 6, 1971 The United States of America as represented by the Secretary of the Navy [72] Inventor [21 1 Appl. No. [22] Filed [45 Patented [73] Assignee [54] INTEGRAL PLUG AND STRUT NOZZLE 2 Claims, 3 Drawing Figs.
[52] US. Cl ..239/265.1l,
239/601 [51] Int. Cl 864d 33/04 [50] Field of Search 60/263, 271; 239/265.1 1, 265.15, 422, 428, 433, 601
[5 6] References Cited UNITED STATES PATENTS 2,755,620 7/1956 Gillot 60/263X 2,875,577 3/1959 Odenkirchen 60/271X 3,245,620 4/1966 McEWen 239/265.15X
3,300,142 1/1967 Brown 239/265.l5
3,343,766 9/1967 Biehl et a1... 239/265.11X
3,292,865 12/1966 Short ct al. 239/265.25 FOREIGN PATENTS 636,026 1/1928 France 60/263 Primary Examiner-Lloyd L. King Assistant Examinerlohn J. Love Att0rneysE. J. Brower, Arthur L. Branning and T. 0.
Watson, Jr.
ABSTRACT: A one-piece exhaust nozzle for rocket motors. It is substantially cylindrical with three funneled inlet holes at its forward end, blending into a single opening at the aft end. A center body, pyramid shaped, forms a contoured inner wall for the nozzle which has a constantly expanding exhaust area.
PATENTEU MARI 6197i INVENTOR ALBERT W JOHNSON ATTORNEY I INTEGRAL PLUG AND STRUT NOZZLE STATEMENT OF GOVERNMENT INTEREST BACKGROUND OF THE INVENTION 1. Field of the invention This invention relates to a plug exhaust nozzle for a rocket motor and more particularly to a nozzle where the exhaust gases are received through three inlets and are recombined in the downstream flow and discharged through a single aft opening.
2. Description of Prior Art Heretofore annular exhaust nozzles have been formed of an outer body and a center body, with the center body supported by crossbars or tripodlike arms. These supports interfere with the flow of gases and form crosscurrents in the exhaust which reduce the efficiency of the motor. The inner contour of the nozzle is formed by inserts which makes for leakage of exhaust gases and, by edge interference of these inserts, causes crosscurrents in the flow.
SUMMARY OF THE INVENTION A nozzle made in one piece, where the expansion of the gases is controlled so that the explosion ratio to nozzle length is a forward step. The integral molded nozzle is without the possibility of gas leakage, while the form of intersecting elliptical cones reduces the turbulence and provides greater efficiency.
An object of the present invention is to provide an exhaust nozzle formed in one piece.
Another object of the present invention is to provide an exhaust nozzle having a contoured inner and outer wall, integral, of substantially cylindrical form and so controlling the flow of gases as to prevent any leak path and provide a high thrust.
It is another object of the present invention to provide an integral plug and strut nozzle, which for low temperature propellants, could be molded from a carbon molding compound.
It is still another object of the present invention to provide an integral plug and strut nozzle which may be manufactured at a comparatively low cost.
It is still another object of the present invention to provide an integral plug and strut nozzle which will provide the highest expansion ratios with the shortest length.
2 BRIEF DESCRIPTION OF THE DRAWINGS The invention is illustrated in the accompanying drawing in which: I
FIG. 1 is a perspective view of the plug and strut nozzle; FIG. 2 is a view looking at the aft end of the nozzle; and FIG. 3 is a view looking at the forward end of the nozzle.
DESCRIPTION OF THE PREFERRED EMBODIMENTS Referring to the drawings wherein like parts are designated by like numbers, the integral plug and strut nozzle has a cylindrical outer wall 12, a forward rim 13 and an aft rim 14.
The forward end of the nozzle receives the exhaust gases from the motor and divides these gases to pass the gases through individual distinct throats 15, 16 and 17. Sloping sidewalls 18, 19 and 21, respectively, on the approach side of the throats funnel the gases into the throats. The strut or center body 22 is shaped to recombine the exhaust gases coming through the different throats with the least turbulence. Gas flow from subsonic to supersonic is only disturbed to the extent of flow over an airfoil. The shape of the entire body is that of elliptical cones intersecting and forming at their juncture, a strut or center body, the sides of which are shaped to provide an airfoil construction over which the gases flow.
he aft end of the nozzle 1s as though a plane was passed through the intersecting cones, together with the strut at a point beyond the apex of the strut. The arcs of the side of the cones 23, 24 and 25 serve as the outer extremity of the outer wall of the nozzle, while the slopes of the strut or center body forms the inner wall of the nozzle and as these slopes terminate in the apex 26, the gases are progressively expanded in the shortest possible length of nozzle.
The integral plug and strut nozzle of the present invention has many advantages over the annular nozzle in use at present. It is less expensive to manufacture. The thrust coefficient proves its high efficiency. There is the highest expansion ratio in the shortest length, the short length allowing a greater length of gain and a consequent greater or longer flight of missile. For low pressure and/or low temperature propellants, the entire nozzle could be molded out of good graphite or carbon molding compound.
lclaim:
1. An integral exhaust nozzle for a rocket motor having a cylindrical outer shape, three inlet openings formed in the forward end of said nozzle to receive exhaust gases from said rocket motor, three separate cone-shaped passages extending from said inlet openings and intersecting to form a single terminal outlet in the aft end of said nozzle where the exhaust gases are recombined, and a substantially pyramid-shaped center body formed by the intersection of said three coneshaped passages.
2. An integral exhaust nozzle for a rocket motor according to claim 1 wherein the cones are elliptical.

Claims (2)

1. An integral exhaust nozzle for a rocket motor having a cylindrical outer shape, three inlet openings formed in the forward end of said nozzle to receive exhaust gases from said rocket motor, three separate cone-shaped passages extending from said inlet openings and intersecting to form a single terminal outlet in the aft end of said nozzle where the exhaust gases are recombined, and a substantially pyramid-shaped center body formed by the intersection of said three cone-shaped passages.
2. An integral exhaust nozzle for a rocket motor according to claim 1 wherein the cones are elliptical.
US791528*A 1969-01-15 1969-01-15 Integral plug and strut nozzle Expired - Lifetime US3570766A (en)

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4519423A (en) * 1983-07-08 1985-05-28 University Of Southern California Mixing apparatus using a noncircular jet of small aspect ratio
US5423483A (en) * 1993-11-12 1995-06-13 Schwade; Hans H. Sootblower
US5579999A (en) * 1993-07-19 1996-12-03 The United States Of America As Represented By The United States National Aeronautics And Space Administration Shock-free supersonic elliptic nozzles and method of forming same
US5920925A (en) * 1998-04-01 1999-07-13 B&S Plastics, Inc. Pulsating hydrotherapy jet system
US5931392A (en) * 1997-03-07 1999-08-03 Adams; Robert J. High-pressure cleaning spray nozzle
US8622715B1 (en) * 2011-12-21 2014-01-07 Compatible Components Corporation Twin turbine asymmetrical nozzle and jet pump incorporating such nozzle
FR3112170A1 (en) * 2020-07-06 2022-01-07 Arianegroup Sas Small propellant nozzle with several discharge sections

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR636026A (en) * 1927-06-15 1928-03-30 Turbo-compression thruster
US2755620A (en) * 1951-02-08 1956-07-24 Brandt Soc Nouv Ets Rocket motor
US2875577A (en) * 1957-09-06 1959-03-03 William W Odenkirchen Reaction propulsion device
US3245620A (en) * 1961-12-13 1966-04-12 Gen Motors Corp Missile steering control
US3292865A (en) * 1963-10-17 1966-12-20 Gen Motors Corp Thrust vector control with clustered nozzles
US3300142A (en) * 1963-06-25 1967-01-24 Whittaker Corp Rocket nozzle capable of inducing flow separation
US3343766A (en) * 1965-04-02 1967-09-26 Mb Assoc Nozzle insert

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR636026A (en) * 1927-06-15 1928-03-30 Turbo-compression thruster
US2755620A (en) * 1951-02-08 1956-07-24 Brandt Soc Nouv Ets Rocket motor
US2875577A (en) * 1957-09-06 1959-03-03 William W Odenkirchen Reaction propulsion device
US3245620A (en) * 1961-12-13 1966-04-12 Gen Motors Corp Missile steering control
US3300142A (en) * 1963-06-25 1967-01-24 Whittaker Corp Rocket nozzle capable of inducing flow separation
US3292865A (en) * 1963-10-17 1966-12-20 Gen Motors Corp Thrust vector control with clustered nozzles
US3343766A (en) * 1965-04-02 1967-09-26 Mb Assoc Nozzle insert

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4519423A (en) * 1983-07-08 1985-05-28 University Of Southern California Mixing apparatus using a noncircular jet of small aspect ratio
US5579999A (en) * 1993-07-19 1996-12-03 The United States Of America As Represented By The United States National Aeronautics And Space Administration Shock-free supersonic elliptic nozzles and method of forming same
US5423483A (en) * 1993-11-12 1995-06-13 Schwade; Hans H. Sootblower
US5931392A (en) * 1997-03-07 1999-08-03 Adams; Robert J. High-pressure cleaning spray nozzle
US5920925A (en) * 1998-04-01 1999-07-13 B&S Plastics, Inc. Pulsating hydrotherapy jet system
US8622715B1 (en) * 2011-12-21 2014-01-07 Compatible Components Corporation Twin turbine asymmetrical nozzle and jet pump incorporating such nozzle
FR3112170A1 (en) * 2020-07-06 2022-01-07 Arianegroup Sas Small propellant nozzle with several discharge sections

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