Indian Journal of Engineering & Materials Sciences

Open Access Open Access  Restricted Access Subscription Access

Analysis of Rotating Detonation Wave Engine


Affiliations
1 National Centre for Combustion Research and Development, IIT Madras, Chenna 600 036, India
 

Rotating Detonation Wave Engine (RDE) due to its promising potential as a propulsive and power generation device has been researched worldwide based on both numerical and experimental investigations. The thermodynamic analysis has been of importance prior to the commencement of the experimental investigations as the set conditions could be established with ease. The flow field behind the detonation wave has been quite complex due to oblique shock wave, contact surface between combustion products of detonation wave and shocked combustion products and the expansion waves. The simultaneous establishment of the flow parameters has been of importance to the success of understanding the RDE. The enthalpy values at different states have provided the energy conversion to kinetic energy as a result of expansion of the product gases in the RDE flow field. Stability of the oblique shock wave attached to the detonation wave has been crucial for obtaining optimum performance of RDE. The intersection of oblique shock polar and the Prandtl – Meyer expansion characteristics has given the conditions under which the oblique shock remains attached to the detonation wave and be a part of the triple point. Under all the set conditions, the stability of the oblique shock has been ascertained. In the present analysis, the specific thrust for the present configuration using H2–air is 1374 Ns/kg compared to a value of 1347 Ns/kg reported in the literature for a stoichiometric composition. The marginal difference has been due to the different input conditions ahead of the detonation wave. This has given credence to the results of the analytical work based on gas dynamic and thermodynamic relationships. The practical implications of this analytical work have been brought out.

Keywords

CJ Detonation, Deflection Angle, Rotating Detonation Wave Engine (RDE), Shock Polar, Shock Angle, Sonic State, Specific Thrust, Specific Impulse.
User
Notifications
Font Size

  • Journell C L, High speed diagnostics in a natural gas-air rotating detonation wave engine at elevated pressure, PhD thesis, Purdue University, 2019

  • Sooraj Ram, The impossible RDE actually works, Advancetec News, 26 May 2020

  • Subramaniam S, Novel approach for computational modelling of a non-premixed rotating detonation wave engine, MS thesis, Virginia Polytechnic Institute and State University, 2019

  • Ramanujachari V & Preethi A P, Transactions of the Indian National Academy of Engineering, 2021. https://doi.org/10.1007/s41403-021-00275-2.

  • Shepherd J E & Kasahara J, Analytical models for the thrust of a rotating detonation engine, GALCIT Report, CIT, CA, USA, 2017

  • Shah I J, Kildare J AC, Ivans M J, Cinnici A, Sparks C A M, Rubaiyat S N H Cin R C & Medwell P R, Detonation – A new era for Engines, Intech Open, 2019

  • Fotia M L, Hoka J & Schauer F, Performance of rotating detonation wave engine for air breathing applications, Chapter.1, in Detonation Control for Propulsion, Shock Waves and High Pressure Phenomena, Edited by Li, J.M. (Springer, 2018,Singapore)https://doi.org/10.1007/978-3-319-689067_1, (2018)

  • Escobar S, Suryanarayana RP, Ismail C, Donald Ferguson & Peter Strakey, Proceedings of ASME Turbo Expo, GT2013-94918, (2013).

  • Schwer, D & Kailasanath, K, 51st AIAA/ SAE/ASEE Joint Propulsion Conference, AIAA 2015-3782, 2015.

  • Sousa J, Braun J & Paniagua G, Applied Math Modelling, Vol 52 (2017) 42.

  • Fievisohn R, Development and Application of Theoretical Models for Rotating Detonation Wave Engines, PhD thesis, University of Maryland, USA, 2016

  • Mizener A R, Performance Modelling and Experimental Investigations of Rotating Detonation Engines, PhD thesis, University of Texas at Arlington, USA, 2018

  • Lu F K & Braun E M, Journal of Propulsion and Power, 30 (2014) 1125.

  • Han H S, Lee E S & Choi J Y, Energies,14,Paper-1381,2021

  • Koch J & Kutz N, Physics Fluids, 32(2020), 126102(1- 20).

  • Mendible A, Koch J, Lange H, Bruntor S L & Kutz N, Phys. Rev. Fluids, Paper 050507,6 (2021)

  • Bennewitz J W, Bigler B R, Hargus W A & Smith RD, Energies,14, Paper- 2037, 2021.

  • Suchocki J A, Operational space and characterisation of a rotating detonation engine using hydrogen and air, MS thesis, The Ohio State University, USA, 2012

  • Gordon S & McBride B, NASA Chemical Analysis Equilibrium Code, NASA Glenn Centre, 1996

  • Schwer D A & Kailasanath K, AIAA paper 2011-0581, 2011

  • Houim R W & Fievishon R T, Combustion & Flame, 179 (2017) 185


Abstract Views: 91

PDF Views: 81




  • Analysis of Rotating Detonation Wave Engine

Abstract Views: 91  |  PDF Views: 81

Authors

Ramanujachari V
National Centre for Combustion Research and Development, IIT Madras, Chenna 600 036, India
Amrutha Preethi P
National Centre for Combustion Research and Development, IIT Madras, Chenna 600 036, India

Abstract


Rotating Detonation Wave Engine (RDE) due to its promising potential as a propulsive and power generation device has been researched worldwide based on both numerical and experimental investigations. The thermodynamic analysis has been of importance prior to the commencement of the experimental investigations as the set conditions could be established with ease. The flow field behind the detonation wave has been quite complex due to oblique shock wave, contact surface between combustion products of detonation wave and shocked combustion products and the expansion waves. The simultaneous establishment of the flow parameters has been of importance to the success of understanding the RDE. The enthalpy values at different states have provided the energy conversion to kinetic energy as a result of expansion of the product gases in the RDE flow field. Stability of the oblique shock wave attached to the detonation wave has been crucial for obtaining optimum performance of RDE. The intersection of oblique shock polar and the Prandtl – Meyer expansion characteristics has given the conditions under which the oblique shock remains attached to the detonation wave and be a part of the triple point. Under all the set conditions, the stability of the oblique shock has been ascertained. In the present analysis, the specific thrust for the present configuration using H2–air is 1374 Ns/kg compared to a value of 1347 Ns/kg reported in the literature for a stoichiometric composition. The marginal difference has been due to the different input conditions ahead of the detonation wave. This has given credence to the results of the analytical work based on gas dynamic and thermodynamic relationships. The practical implications of this analytical work have been brought out.

Keywords


CJ Detonation, Deflection Angle, Rotating Detonation Wave Engine (RDE), Shock Polar, Shock Angle, Sonic State, Specific Thrust, Specific Impulse.

References