Jan Kindracki

A Three-Dimensional Numerical Study of Rotational Detonation in an Annular Chamber

Detonation waves successively rotating in an annular chamber are numerically investigated to understand an overall ∞owfleld structure in the combustion chamber of an engine and its basic operation with a continuous fuel injection. This study leads to further investigation into continuously rotating detonation wave, which is the backbone in developing a rotating detonation-based propulsion system. A computational code developed is based on multi-dimensional Euler equations with source terms due to chemical reactions. Spatial terms in governing equations are discretized with a flnite volume method and a MUSCLbased Roe scheme, while temporal terms are discretized with a second-order, three-step Runge-Kutta method. Source terms are treated with a time-operator splitting method in order to isolate stifiness. The detonation is modeled with the one-step chemical reaction of a hydrogen and air mixture. A detailed ∞owfleld structure including detonation properties is presented in two- and three-dimensional annular chamber. The propulsive parameters of a rotational detonation engine are evaluated and its comparison of one- and two-waved detonation engine is performed in a three-dimensional chamber.

Rocket rotating detonation engine flight demonstrator

Purpose Today’s modern liquid propellant rocket engines have a very complicated structure. They cannot be arbitrarily downsized, ensuring efficient propellants’ mixing and combustion. Moreover, the thermodynamic cycle’s efficiency is relatively low. Utilizing detonation instead of deflagration could lead to a significant reduction of engine chamber dimensions and mass. Nowadays, laboratory research is conducted in the field of rotating detonation engine (RDE) testing worldwide. The aim of this paper is to cover the design of a flight demonstrator utilizing rocket RDE technology. Design/methodology/approach It presents the key project iterations made during the design of the gaseous oxygen and methane-propelled rocket. One of the main goals was to develop a rocket that could be fully recoverable. The recovery module uses a parachute assembly. The paper describes the rocket’s main subsystems. Moreover, vehicle visualizations are presented. Simple performance estimations are also shown. Findings This paper shows that the development of a small, open-structure, rocket RDE-powered vehicle is feasible. Research limitations/implications Flight propulsion system experimentation is on-going. However, first tests were conducted with lower propellant feeding pressures than required for the first launch. Practical implications Importantly, the vehicle can be a test platform for a variety of technologies. The rocket’s possible further development, including educational use, is proposed. Originality/value Up-to-date, no information about any flying vehicles using RDE propulsion systems can be found. If successful in-flight experimentation was conducted, it would be a major milestone in the development of next-generation propulsion systems.

RECENT RESEARCH ON THE ROTATING DETONATION AT WARSAW UNIVERSITY OF TECHNOLOGY

The paper describes the recent experimental investigation of detonation in a heterogeneous mixture of kerosene and oxidizer. research was carried out in two different stands. For research on detonation limits, a number of short test tubes of differing inner diameter were used. Various mixtures of oxygen and nitrogen were used as an oxidant, from pure oxygen to the composition of air. The main goal of the study was to determine the minimum tube diameter required for direct initiation of detonation. From measurements, the pressure courses were obtained for three cases: direct initiation, initiation behind reflected wave and without initiation. The second part of the paper describes experimental research into the initiation and propagation of rotating detonation for heterogeneous kerosene and air mixtures. The research facility with main subsystems and exemplary results are shown and described.

Report on the implementation of the POIG project „turbine engine with a detonation combustion chamber”

This article contains a description of the work carried out under the UDA-POIG 01.03.01-14-071/09-10 project titled “A turbine engine with a detonation chamber”. The work carried out during the project involved 14 construction, research and calculation tasks. Various research stands designed to analyse the process of mixture formation, initiation of detonation and research of rotating detonation in combustion chambers were constructed. Test stand for examining a turboshaft engine with detonation combustion chamber was built. Those test stands allowed powering the combustion chambers and the engine with both liquid and gaseous fuels, simultaneously or separately. At the same time, REFLOPS software, which could calculate the propagation of a detonation wave was created, and used in the design of further versions of combustion chambers. Data from the experiments was used to verify the calculations and models created in the mentioned software. GTD-350 engine was used as the base; the structure of which (combustion chamber situated outside the turbine-compressor unit) facilitated modifying the shape of the detonation combustion chamber. During the research, great emphasis was placed on the safety of researchers. Working with hydrogen in high temperatures and JET-A1 fuel, which was additionally heated, and the usage of the oxy-acetylene detonators forced extreme caution, and full compliance with developed procedures. The project was divided into 14 tasks that were often conducted simultaneously in a 20-person team implementing the project. The work was completed by performing comparative studies between conventional engine with deflagration combustion chamber, and modified engine with a detonation combustion chamber. During the completion of the project, it was the first working demonstrator engine with detonation combustion chamber in the world.

Innovative Resistojet Propulsion System—Use in Robotic Space Platforms

This paper addresses the problem of precise satellite manoeuvres and possibility of using resistojet as an effective element of a positioning system. The high demands of precision and reliability make the simplicity of any such system one of its most important features. In many missions, electrothermal propulsion is considered to be a good solution, but high power levels are required to improve the working gas parameters. Resistojet, designed and built in Warsaw University of Technology, with power supplied by supercapacitors can fulfil those requirements. The Simulation Tool for Space Robotics developed at the Space Research Centre of the Polish Academy of Sciences demonstrates the possibility of predicting satellite movement after a thruster pulse. It will enable precise adjustments to be made to resistojet performance to meet the demands of particular mission and tasks. Cooperation between the Space Research Centre of the Polish Academy of Sciences and Warsaw University of Technology in research on use of the resistojet in space robotics, and common experimentation using an air-bearing table is planned for the near future.