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Test firing of Space Shuttle main engine (whose engine nozzle is very close in shape to optimal)

The bell-shaped or contour nozzle is probably the most commonly used shaped rocket engine nozzle. It has a high angle expansion section (20 to 50 degrees) right behind the nozzle throat; this is followed by a gradual reversal of nozzle contour slope so that at the nozzle exit the divergence angle is small, usually less than a 10 degree half angle.

An ideal nozzle would direct all of the gases generated in the combustion chamber straight out the nozzle. That would mean the momentum of the gases would be axial, imparting the maximum thrust to the rocket. In fact, there are some non-axial components to the momentum. In terms of a momentum vector, there is an angle between the axis of the rocket engine and the gas flow. As a result, the thrust is lowered by varying amounts.

The bell or contour shape is designed to impart a large angle expansion for the gases right after the throat. The nozzle is then curved back in to give a nearly straight flow of gas out the nozzle opening. The contour used is rather complex. The large expansion section near the throat causes expansion shock waves. The reversal of the slope to bring the exit to near zero degrees causes compression shock waves. A properly designed nozzle will have these two sets of shock waves coincide and cancel each other out. In this way, the bell is a compromise between the two extremes of the conical nozzle since it minimizes weight while maximizing performance.[1]

The most important design issue is to contour the nozzle to avoid oblique shocks and maximize performance.

In his classic textbook,[2] George P. Sutton credits Dr. G. V. R. Rao with working out the mathematics of the optimal bell nozzle design in 1955, while working at Rocketdyne.[3][4][5][6]

References

  1. ^ Williams, James C. (1970). A STUDY OF NACA AND NASA PUBLISHED INFORMATION OF PERTINENCE IN THE DESIGN OF LIGHT AIRCRAFT (1st ed.). Springfield, Virginia: DEPARTMENT OF MECHANICAL AND AEROSPACE ENGINEERING NORTH CAROLINA STATE UNIVERSITY Raleigh, N.C. p. 708.
  2. ^ George P. Sutton (1992). Rocket Propulsion Elements: An Introduction to the Engineering of Rockets (6th ed.). Wiley-Interscience. p. 636. ISBN 0-471-52938-9.
  3. ^ G.V.R. Rao Contoured Rocket Nozzles. Ninth annual congress of the International Astronautical Federation 1958. Library of Congress call number TL 787.I44
  4. ^ G.V.R. Rao, "Recent development in rocket nozzle configurations". Journal American Rocket Society Vol. 31 Number 11 November 1961. Library of Congress call number TL 780.A613
  5. ^ G.V.R. Rao, "Approximation of optimum thrust nozzle contours". Journal American Rocket Society Vol. 30 Number 6 June 1960. Library of Congress call number TL 780.A613
  6. ^ G.V.R. Rao, "Exhaust nozzle contour for optimum flight". Jet Propulsion Vol. 28 number 6 1958. Library of Congress call number TL 780.A613

See also

Category