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Computational Characterization of a CD Nozzle with Variable Geometry Translating Throat

  • S. Apoorva
  • Suresh Chandra Khandai
Conference paper
Part of the Lecture Notes in Mechanical Engineering book series (LNME)

Abstract

Nozzles constitute the exhaust system of jet engines. They are designed to regulate the flow properties to provide the required thrust force for all flight conditions. In the present work, the simulation of a de Laval nozzle outfitted with a throat shifting mechanism is compassed. The mechanism adds a variation in the throat geometry during the translation of the throat. A convergent–divergent (CD) nozzle is designed for Mach 2 initially. The geometry of the throat is varied by keeping the settling chamber pressure constant. The scope of the effort was to investigate the characteristics over the range of geometries (throat diameters, 10, 9.5, 9, and 8.5 mm) and operating conditions. The simulation of the nozzle flow is carried out using ANSYS CFX. Shear stress transport (SST) turbulence is used for the flow simulation. Grid-independent study is also performed for better mesh results. The simulation is carried out for chamber pressures of 8, 9.5, 11.5, and 14 bar. The Mach number, pressure, velocity, and temperature readings are taken along the nozzle axis and also the important cross sections of the nozzle for all cases. Thrust is calculated for all the cases and compared. Plot comparison of variations in the parameters was done, and optimum results were inferred.

Keywords

CD nozzle Pressure Temperature Variable geometry translating throat Grid SST 

List of Symbols

M

Mach number

V

Nozzle exit velocity (m/s)

Ae

Nozzle exit area (mm2)

A*

Nozzle throat area (mm2)

d*

Nozzle throat diameter (mm)

de

Nozzle exit diameter (mm)

Pamb

Ambient pressure (N/m2)

Po

Inlet pressure (N/m2)

Pe

Exit pressure (N/m2)

To

Inlet temperature (K)

Te

Exit temperature (K)

L

Nozzle length (mm)

X

Distance from nozzle inlet (mm)

References

  1. 1.
    Natta, P., Ranjith Kumar, V., Hanumantha Rao, Y.V.: Investigation of variation of flow parameters of a rocket nozzle. IJERA (2012). ISSN 2248–9622Google Scholar
  2. 2.
    Pandey, K.M., Singh, A.P.: CFD analysis of conical nozzle for mach 3 at various angles of divergence with fluent software. IJCEA 1(2) (2010). ISSN 2010–0221Google Scholar
  3. 3.
    Pandey, K.M., Yadav, S.K.: CFD analysis of a rocket nozzle with four inlets at Mach 2.1. IJCEA 1(4) (2010). ISSN: 2010–0221Google Scholar
  4. 4.
    Pansari, K, Jilani, S.A.K.: Analysis of performance of flow characteristics of convergent-divergent nozzles. IJAET (2013). ISSN: 22311961Google Scholar
  5. 5.
    Stark, R.H.: Flow Separation in Rocket Nozzles. AIAA, German Aerospace Center, Lampoldshausen, D-74239, Germany (2005)Google Scholar
  6. 6.
    Satyanarayana, G., Varun, C., Naidu, S.S.: CFD analysis of convergent-divergent nozzle. Acta Technica Corviniensis Bull. Eng. Fascicule 3 (2013). ISSN 2007–3809Google Scholar
  7. 7.
    Vinod Kumar, P., Kishore Kumar, B.: Design and CFD analysis of convergent-divergent nozzle. Int. J. Prof. Eng. Stud. 9(2) (2017)Google Scholar
  8. 8.
    Pandey, K.M., Kumar, V.: CFD analysis of twin jet flow at Mach 1.74 with fluent software. Int. J. Environ. Sci. Dev. 1(5) (2010). ISSN: 2010-0264Google Scholar
  9. 9.
    Lijo, V.: Numerical investigation of transient flows in an axisymmetric over-expanded thrust optimized contour nozzle. Int. J. Heat Fluid Flow 409–417 (2010)Google Scholar
  10. 10.
    Ali, A., Neely, A., Young, J., Blake, B., Lim, J.Y.: Numerical simulation of fluidic modulation of nozzle thrust. In: 17th Australian Fluid Mechanics Conference, 5–9 Dec 2010Google Scholar

Copyright information

© Springer Nature Singapore Pte Ltd. 2019

Authors and Affiliations

  1. 1.Department of Aeronautical EngineeringRajalakshmi Engineering CollegeChennaiIndia

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