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Design and Validation of Diesel Engine Infrared Signature Suppression Devices for Naval Ships

  • Murty V. S. N. AnavillaEmail author
  • Subbaiah Venkata Kambagowni
  • Rao Bhujanga Vepakomma
Original Contribution
  • 56 Downloads

Abstract

Management of infrared (IR) signature forms a key component of naval stealth. Exhaust plume and exhaust duct metal surfaces are the major sources of IR signature in 3–5 µm wave band. The present study proposes methodology for design of passive eductor–diffuser-type diesel engine infrared signature suppression (IRSS) device comprising of mathematical modeling for dimensional design, commercial computational fluid dynamics (CFD) software-based thermal prediction and prototype testing for design validation. IRSS device for a hypothetical 1.2 MW diesel alternator fitted in the exhaust stack of generic naval corvette is designed using proposed methodology, based on which a 2.7-m-long prototype is fabricated and tested using hot air gas generator on a specially designed test bed at Naval Science and Technology Laboratory, Visakhapatnam. A good match is observed between CFD-predicted and measured values of key performance parameters, viz. diffuser ring metal temperatures, average plume temperature at exit and back-pressure. Reduction in missile lock-on range with and without diesel engine IRSS device in 3–5 µm range is estimated.

Keywords

Diesel engine IR signature suppression Eductor–diffuser IRSS device CFD Prototype testing Lock-on range 

List of Symbols

Amt

Area of mixing tube (m2)

An

Area of nozzle (m2)

b

Ring gap or slot size (mm)

Dmt

Diameter of mixing tube (mm)

Dn

Diameter of nozzle inlet (mm)

Lmt

Length of mixing tube (m)

M

ρambWamb/ρexhWexh (non-dimensional)

P

Static pressure (Pa)

Pr

Prandtl number = 0.7 (for air at 303 K)

Rec

Reynolds number based on coolant flow

Tc

Secondary air temperature (K)

Te

Temperature exhaust gas (K)

Texit

Temperature exhaust gas at device exit (K)

Tinlet

Temperature exhaust gas at nozzle inlet (K)

Tw

Wall temperature (K)

V

Velocity of fluid (m/s)

W

Mass flow rate (kg/s)

x

Ring length (mm)

Z

Potential height (m)

Greek Letters

β

Injection angle correction = 1.0 for tangential injection

ρ

Density of fluid (kg/m3)

μ

Viscosity of fluid (kg/ms)

μc

Dynamic viscosity of coolant air (kg/ms)

μm

Dynamic viscosity of main stream (kg/ms)

η

Film cooling efficiency of injection into tangential slots (non-dimensional)

γ

Specific heat of exhaust gas/specific heat of secondary air (non-dimensional)

Notes

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Copyright information

© The Institution of Engineers (India) 2019

Authors and Affiliations

  1. 1.Infrared DepartmentNaval Science and Technology LaboratoryVisakhapatnamIndia
  2. 2.Department of Mechanical EngineeringAndhra UniversityVisakhapatnamIndia
  3. 3.ISRO Chair ProfessorNational Institute of Advanced StudiesBangaloreIndia

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