scholarly journals Comparison of thermodynamic efficiency and thrust characteristics of air-breathing jet engines with subsonic combustion and burning in stationary and nonstationary detonation waves

2018 ◽  
Author(s):  
A. N. Kraiko ◽  
A. D. Egoryan
Keyword(s):  
Detonation Waves ◽  
Thermodynamic Efficiency ◽  
Jet Engines ◽  
Air Breathing ◽  
Thrust Characteristics

Methodological Aspects of Determining Thrust of Irrotational Air-Breathing Jet Engines in Bench and Flight Tests

2019 ◽  
pp. 86-97
Author(s):  
V.L. Semenov ◽  
V.Yu. Aleksandrov ◽  
A.N. Prokhorov ◽  
K.Yu. Arefyev ◽  
S.V. Kruchkov
Keyword(s):  
Mathematical Models ◽  
High Speed ◽  
Specific Impulse ◽  
Jet Engines ◽  
Flight Tests ◽  
Air Breathing ◽  
Internal Parameters ◽  
Thrust Characteristics ◽  
Methodological Aspects ◽  
Further Development

This article examines methodological aspects of the indirect calculation of thrust characteristics of irrotational air-breathing jet engines using telemetry data that can be obtained during high-speed aircraft flight tests. Specific features of determining thrust characteristics during bench and flight tests are described. Mathematical models are developed for data analysis and calculation of the thrust and the specific impulse of an irrotational air-breathing jet engine by internal parameters, as well as its effective thrust in integration with a high-speed aircraft. The proposed approaches are tested, and the developed mathematical models are validated according to the results of experimental bench tests of the thrust characteristics of irrotational air-breathing jet engines in integration with a model fuselage of a high-speed aircraft. Satisfactory convergence of the results of indirect and direct (experimental) force measurements is shown. The data obtained can be used for further development of the method and analysis of bench and flight tests of aircraft with irrotational air-breathing jet engines.

scholarly journals Technological advancements in Pulse Detonation Engine Technology in the recent past: A Characterized Report

2019 ◽  
Vol 11 (4) ◽  
pp. 81-92
Author(s):  
Bharat Ankur DOGRA ◽  
Mehakveer SINGH ◽  
Tejinder Kumar JINDAL ◽  
Subhash CHANDER
Keyword(s):  
High Speed ◽  
Combustion Process ◽  
Detonation Waves ◽  
Status Report ◽  
Pulse Detonation Engine ◽  
Operating Cycle ◽  
Air Breathing ◽  
Pulse Detonation ◽  
Pulsed Detonation ◽  
Detonation Engine

Pulse Detonation Engine (PDE), is an emerging and promising propulsive technology all over the world in the past few decades. A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. Theoretically, a PDE can be operate from subsonic to hypersonic flight speeds. Pulsed detonation engines offer many advantages over conventional air-breathing engines and are regarded as potential replacements for air-breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long-range transportation, high-speed vehicles, space launchers to space vehicles. This article highlights the operating cycle of PDE, starting with the fuel-oxidizer mixture, combustion and Deflagration to detonation transition (DDT) followed by purging. PDE combustion process, a unique process, leads to consistent and repeatable detonation waves. This pulsed detonation combustion process causes rapid burning of the fuel-oxidizer mixture, which cannot be seen in any other combustion process as it is a thousand times faster than any other mode of combustion. PDE not only holds the capability of running effectively up to Mach 5 but it also changes the technicalities in space propulsion. The present paper is the extension of the previous study which is also a well characterized status report of PDE in different areas. The present study deals with the categorization of the design approach, computations & simulations, flow visualization, DDT & Thrust enhancement, PDRE’s, experimental detonation engines with some of the experience and research undertaken in Punjab Engineering College under the complete supervision and guidance of Prof. Tejinder Kumar Jindal followed by applications of PDE technology.

Numerical Study on Thermodynamic Efficiency and Stability of Oblique Detonation Waves

AIAA Journal ◽  
2018 ◽  
Vol 56 (8) ◽  
pp. 3112-3122 ◽  
Author(s):  
Shikun Miao ◽  
Jin Zhou ◽  
Zhiyong Lin ◽  
Xiaodong Cai ◽  
Shijie Liu
Keyword(s):  
Numerical Study ◽  
Detonation Waves ◽  
Thermodynamic Efficiency

scholarly journals АНАЛИЗ ХАРАКТЕРИСТИК ТУРБОРЕАКТИВНОГО ДВУХКОНТУРНОГО ДВИГАТЕЛЯ С ФОРСАЖНОЙ КАМЕРОЙ СГОРАНИЯ С ВПРЫСКОМ ВОДЫ ЗА ВХОДНЫМ УСТРОЙСТВОМ

2019 ◽  
pp. 29-38
Author(s):  
Юрий Александрович Улитенко
Keyword(s):  
High Speed ◽  
Power Plants ◽  
Specific Impulse ◽  
Water Injection ◽  
Range Extension ◽  
Thermodynamic Efficiency ◽  
Influence Of Water ◽  
Thrust Characteristics ◽  
New Generation ◽  
Turbojet Bypass Engine

Development of perspective high-speed aircraft inseparably depends on the level of aircraft propulsion engineering as engine performances to determine aircraft capabilities as a whole. The basic requirements to engines of high-speed aircraft are increase speed and flight height. The new generation of turbojet bypass engine with afterburner each their specific thrust and a specific impulse increases, also the application of high technologies raises leads to substantial growth of the engine cost too. At the same time, existing engines design has big reserves for modernization. The system of water injection to the input at the turbojet bypass engine with afterburner is one of the accessible ways for design improvement. Those advanced engines theoretically will allow to satisfy requirements from designers of high-speed aircraft concerning to thrust and other key parameters, at the same time to secure continuity of already existing types of power-plants. The possibility of range extension of turbojet bypass engine with classical scheme afterburner operation till Mach number 3 is considered in this article. The analysis of existing developments is carried out. Impact of water injection to the input at turbojet bypass engine with afterburner on its performance is investigated. Results of calculations for the influence of water injection to reaction mass parameters on the engine duct and its thrust characteristics are proved. Received results will allow to increase thermodynamic efficiency and to expand range extension of turbojet bypass engine with afterburner provided to use materials that applied in aviation manufacture, as well as to reduce terms of development competitive engines for high-speed aircraft at the expense of purposeful search of their rational thermodynamic and is constructive-geometrical architecture.

Rotating Detonation Instabilities in Hydrogen-Oxygen Mixture

2014 ◽  
Vol 709 ◽  
pp. 56-62 ◽  
Author(s):  
Yu Hui Wang ◽  
Jian Ping Wang
Keyword(s):  
High Speed ◽  
Specific Impulse ◽  
Pressure Sensors ◽  
Intermediate Frequency ◽  
Oxygen Mixture ◽  
Detonation Waves ◽  
Thermodynamic Efficiency ◽  
Detonation Pressure ◽  
Acoustic Oscillations ◽  
Rotating Detonation

Rotating detonation engines are studied more and more widely because of high thermodynamic efficiency and high specific impulse. Rotating detonation of hydrogen and oxygen was achieved in this study. Rotating detonation waves were observed by high speed cameras and detonation pressure traces were recorded by PCB pressure sensors. The velocity of rotating detonation waves is fluctuating during the run. Low frequency detonation instabilities, intermediate frequency detonation instabilities and high frequency detonation instabilities were discovered. They are relevant to unsteady heat release, acoustic oscillations and rotating detonation waves.

scholarly journals The Principal Aspects of Application of Detonation in Propulsion Systems

2013 ◽  
Vol 2013 ◽  
pp. 1-15 ◽  
Author(s):  
A. A. Vasil'ev
Keyword(s):  
Supersonic Flow ◽  
Combustible Mixture ◽  
Experimental Results ◽  
Detonation Waves ◽  
Propulsion Systems ◽  
Air Breathing ◽  
Deflagration To Detonation Transition ◽  
Detonation Engine ◽  
Detonation Process ◽  
Detonation Transition

The basic problems of application of detonation process in propulsion systems with impulse and continuous burning of combustible mixture are discussed. The results on propagation of detonation waves in supersonic flow are analyzed relatively to air-breathing engine. The experimental results are presented showing the basic possibility of creation of an engine with exterior detonation burning. The base results on optimization of initiation in impulse detonation engine are explained at the expense of spatial and temporal redistribution of an energy, entered into a mixture. The method and technique for construction of highly effective accelerators for deflagration to detonation transition are discussed also.

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