scholarly journals Applications of the continuously rotating detonation to combustion engines at the Łukasiewicz - Institute of Aviation

2022 ◽  
Author(s):  
Michał Kawalec ◽  
Witold Perkowski ◽  
Borys Łukasik ◽  
Adam Bilar ◽  
Piotr Wolański
Keyword(s):  
Rocket Engines ◽  
Combustion Engines ◽  
Liquid Propellant ◽  
Propulsion Systems ◽  
Combine Cycle ◽  
Pulsed Detonation ◽  
Detonation Combustion ◽  
Detonation Engine ◽  
Rotating Detonation Engines ◽  
Rotating Detonation

In the paper short information about advantages of introduction of detonation combustion to propulsion systems is briefly discussed and then research conducted at the Łukasiewicz-Institute of Aviation on development of the rotating detonation engines (RDE) is presented. Special attention is focused on continuously rotating detonation (CRD), since it offers significant advantages over pulsed detonation (PD). Basic aspects of initiation and stability of the CRD are discussed. Examples of applications of the CRD to gas turbine and rocket engines are presented and a combine cycle engine utilizing CRD are also evaluated. The world's first rocket flight powered by liquid propellant detonation engine is also described.

Numerical Modeling of the RDE

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Michal Folusiak ◽  
Karol Swiderski ◽  
Piotr Wolański
Keyword(s):  
Combustion Chamber ◽  
Turbine Engine ◽  
Rotating Detonation Engine ◽  
University Of Technology ◽  
Detonation Combustion ◽  
Detonation Engine ◽  
Innovative Economy ◽  
Turboshaft Engine ◽  
The University ◽  
Rotating Detonation

AbstractThe idea of using the phenomenon of rotating detonation to propulsion has its roots in fifties of the last century in works of Adamson et al. and Nicholls et al. at the University of Michigan. The idea was recently reinvented and experimental research and numerical simulations on the Rotating Detonation Engine (RDE) are carried in numerous institutions worldwide, in Poland at Warsaw University of Technology (WUT) since 2004. Over the period 2010-2014 WUT and Institute of Aviation (IOA) jointly implemented the project under the Innovative Economy Operational Programme entitled ‘Turbine engine with detonation combustion chamber’. The goal of the project was to replace the combustion chamber of turboshaft engine GTD-350 with the annular detonation chamber.This paper is focused on investigation of the influence of a geometry and flow conditions on the structure and propagation stability of the rotating detonation wave. Presented results are in majority an outcome of the aforementioned programme, in particular authors’ works on the development of the in-house code REFLOPS USG and its application to simulation of the rotating detonation propagation in the RDE.

scholarly journals Combustion Characteristics in Rotating Detonation Engines

2021 ◽  
Vol 2021 ◽  
pp. 1-17
Author(s):  
Yuhui Wang ◽  
Wenyou Qiao ◽  
JialingLe
Keyword(s):  
Detonation Wave ◽  
Flow Rate ◽  
Detonation Waves ◽  
Outer Diameter ◽  
Combustion Mode ◽  
Hydrogen Flow ◽  
Pulsed Detonation ◽  
Rotating Detonation Engine ◽  
Rotating Detonation Engines ◽  
Rotating Detonation

A lot of studies on rotating detonation engines have been carried out due to the higher thermal efficiency. However, the number, rotating directions, and intensities of rotating detonation waves are changeful when the flow rate, equivalence ratio, inflow conditions, and engine schemes vary. The present experimental results showed that the combustion mode of a rotating detonation engine was influenced by the combustor scheme. The annular detonation channel had an outer diameter of 100 mm and an inner diameter of 80 mm. Air and hydrogen were injected into the combustor from 60 cylindrical orifices in a diameter of 2 mm and a circular channel with a width of 2 mm, respectively. When the air mass flow rate was increased by keeping hydrogen flow rate constant, the combustion mode varied. Deflagration and diffusive combustion, multiple counterrotating detonation waves, longitudinal pulsed detonation, and a single rotating detonation wave occurred. Both longitudinal pulsed detonation and a single rotating detonation wave occurred at different times in the same operation. They could change between each other, and the evolution direction depended on the air flow rate. The operations with a single rotating detonation wave occurred at equivalence ratios lower than 0.60, which was helpful for the engine cooling and infrared stealth. The generation mechanism of longitudinal pulsed detonation is developed.

scholarly journals Detonation Gas Turbines

2013 ◽  
Vol 135 (12) ◽  
pp. 50-54
Author(s):  
Lee S. Langston
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Wave System ◽  
Pulse Detonation ◽  
Functional Aspects ◽  
Detonation Combustion ◽  
Continuous Detonation ◽  
Improved Performance ◽  
Rotating Detonation Engines ◽  
Rotating Detonation

This article focuses on various technical and functional aspects of detonation gas turbines. Detonation combustion involves a supersonic flow, with the chemical reaction front accelerating, driving a shock wave system in its advancement. In the 1990s, detonation-based power concepts began with pulse detonation engines (PDEs), and have now moved into the continuous detonation mode, termed rotating detonation engines (RDEs). Modern gas turbine combustors are compact, robust, tolerant of a wide variety of fuels, and provide the highest combustion intensities. The single-spool RDE gas turbine is represented by a detonation cycle, which accounts for the supersonic features of the heat addition, starting at station 2.5′. Continued research and development by the RDE technical community is needed to see if the promise of improved performance and downsized turbomachinery for a detonation cycle is real.

Propulsive Performane of Cylindrical Rotating Detonation Engine with Propellant Injection Cooing

2021 ◽  
Author(s):  
Keisuke Goto ◽  
Kosei Ota ◽  
Akira Kawasaki ◽  
Hiroaki Watanabe ◽  
Nobotu Itouyama ◽  
...  
Keyword(s):  
Rotating Detonation Engine ◽  
Detonation Engine ◽  
Rotating Detonation

Flow Visualization inside a Rotating Detonation Engine near Injection Nozzles Using Point-Diffraction Interferometry

2021 ◽  
Author(s):  
Toshiharu Mizukaki ◽  
Fumihiko Iwasaki ◽  
Makoto Kojima ◽  
Hideto Kawashima ◽  
Shingo Matsuyama ◽  
...  
Keyword(s):  
Flow Visualization ◽  
Rotating Detonation Engine ◽  
Detonation Engine ◽  
Rotating Detonation

RECENT STUDIES ON LIQUID-FUELED ROTATING DETONATION ENGINE

2019 ◽  
Author(s):  
A.K. HAYASHI ◽  
◽  
W. YOSHIDA ◽  
M. ASAHARAI ◽  
N. TSUBOI ◽  
...  
Keyword(s):  
Rotating Detonation Engine ◽  
Detonation Engine ◽  
Rotating Detonation

Investigation into the effective injector area of a rotating detonation engine with impact of backflow

Shock Waves ◽  
2021 ◽  
Author(s):  
K. Goto ◽  
R. Yokoo ◽  
A. Kawasaki ◽  
K. Matsuoka ◽  
J. Kasahara ◽  
...  
Keyword(s):  
Rotating Detonation Engine ◽  
Detonation Engine ◽  
Rotating Detonation

scholarly journals Adjoint-based optimisation of detonation initiation by a focusing shock wave

Shock Waves ◽  
2021 ◽  
Author(s):  
S. Bengoechea ◽  
J. Reiss ◽  
M. Lemke ◽  
J. Sesterhenn
Keyword(s):  
Shock Wave ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Detonation Initiation ◽  
Axisymmetric Nozzle ◽  
Exponential Factor ◽  
Pulsed Detonation Engine ◽  
Pulsed Detonation ◽  
Detonation Engine ◽  
Adjoint Approach

AbstractAn optimisation study of a shock-wave-focusing geometry is presented in this work. The configuration serves as a reliable and deterministic detonation initiator in a pulsed detonation engine. The combustion chamber consists of a circular pipe with one convergent–divergent axisymmetric nozzle, acting as a focusing device for an incoming shock wave. Geometrical changes are proposed to reduce the minimum shock wave strength necessary for a successful detonation initiation. For that purpose, the adjoint approach is applied. The sensitivity of the initiation to flow variations delivered by this method is used to reshape the obstacle’s form. The thermodynamics is described by a higher-order temperature-dependent polynomial, avoiding the large errors of the constant adiabatic exponent assumption. The chemical reaction of stoichiometric premixed hydrogen-air is modelled by means of a one-step kinetics with a variable pre-exponential factor. This factor is adapted to reproduce the induction time of a complex kinetics model. The optimisation results in a 5% decrease of the incident shock wave threshold for the successful detonation initiation.

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