scholarly journals Tailored Fuel Injection for Pulsed Detonation Engines via Feedback Control

2003 ◽  
Vol 19 (5) ◽  
pp. 917-921
Author(s):  
Alberto Aliseda ◽  
Kartik B. Ariyur ◽  
Olivier Sarrazin ◽  
Juan C. Lasheras ◽  
Miroslav Krstic
Keyword(s):  
Feedback Control ◽  
Fuel Injection ◽  
Pulsed Detonation ◽  
Pulsed Detonation Engines

Control of Fuel Injection Rate for Marine Diesel Engines Using a Direct Drive Volume Control System

2015 ◽  
Author(s):  
Kazushi Sanada
Keyword(s):  
Mathematical Model ◽  
Control System ◽  
Feedback Control ◽  
Fuel Injection ◽  
Hydraulic Cylinder ◽  
Injection System ◽  
Volume Control ◽  
Direct Drive ◽  
Crank Angle ◽  
Marine Diesel

A direct drive volume control (DDVC) is applied to fuel injection control for marine diesel engine. The DDVC consists of an AC servomotor, a fixed-displacement hydraulic pump, and a hydraulic cylinder. The hydraulic cylinder pushes a plunger pump and fuel is pressurized. When the fuel pressure becomes greater than injection pressure, fuel is injected to a combustion chamber. A brief introduction of the DDVC is described first in this paper referring to conventional fuel injection systems including a cam mechanism and a common rail system. A mathematical model of the DDVC for simulation is summarized. Experiments of fuel injection shows the control function of the DDVC fuel injection system. The topic of this paper is feedback control of the quantity of fuel injection (fuel mass per injection) of the DDVC. The feedback control system is simulated using the above mathematical model. Fuel injection is stopped by switching a drive signal of the AC servomotor and retracting a piston of the hydraulic cylinder. The timing to stop injection is adjusted based on crank angle. An algorithm of updating the crank angle to stop injection is proposed so that the quantity of fuel injection follows the target value. Simulation study shows that the update algorithm works successfully.

Effect of Supercritical Fuel Injection on Cycle Performance of Pulsed Detonation Engine

2007 ◽  
Vol 23 (4) ◽  
pp. 748-755 ◽  
Author(s):  
Timothy M. Helfrich ◽  
Paul I. King ◽  
John L. Hoke ◽  
Frederick R. Schauer
Keyword(s):  
Fuel Injection ◽  
Cycle Performance ◽  
Pulsed Detonation Engine ◽  
Pulsed Detonation ◽  
Detonation Engine

Aerothermodynamics of Pulsed Detonation Engines

2000 ◽  
Author(s):  
Shmuel Eidelman ◽  
Dmitri Sharov ◽  
David Book
Keyword(s):  
Pulsed Detonation ◽  
Pulsed Detonation Engines

Aerothermodynamics of pulsed detonation engines

2000 ◽  
Author(s):  
Shmuel Eidelman ◽  
Dmitri Sharov ◽  
David Book
Keyword(s):  
Pulsed Detonation ◽  
Pulsed Detonation Engines

Multilevel Analysis of Pulsed Detonation Engines

2002 ◽  
Vol 18 (2) ◽  
pp. 225-232 ◽  
Author(s):  
Houshang B. Ebrahimi ◽  
Rajendran Mohanraj ◽  
Charles L. Merkle
Keyword(s):  
Multilevel Analysis ◽  
Pulsed Detonation ◽  
Pulsed Detonation Engines

scholarly journals ОСОБЛИВОСТІ КОНСТРУКТИВНИХ СХЕМ ДВИГУНІВ З ІМПУЛЬСНИМИ ДЕТОНАЦІЙНИМИ КАМЕРАМИ

2020 ◽  
pp. 4-10
Author(s):  
Олександр Євгенович Золотько ◽  
Олена Василівна Золотько ◽  
Олександра Валеріївна Сосновська ◽  
Олександр Сергійович Аксьонов ◽  
Ірина Сергіївна Савченко
Keyword(s):  
Electric Power ◽  
Propulsion System ◽  
High Rate ◽  
Rocket Engines ◽  
Pulsation Frequency ◽  
Feed System ◽  
Jet Engine ◽  
Pulse Detonation ◽  
Pulsed Detonation ◽  
Pulsed Detonation Engines

The pressure of the products of chemical reactions in the chamber of a rocket engine increases significantly if the rocket fuel components burn in the detonation mode. In this case, it can get to a simpler and more reliable expulsion propellant feed system instead of a turbopump feed system. The value of heat release power (MW / liter) of detonation engines is several orders of magnitude larger than that of aircraft and rocket engines operating in the Brighton cycle. The high rate of energy released in the detonation mode can significantly reduce the mass, the inertia, and overall dimensions of the propulsion system. Due to these features, detonation chambers are advisable to be used as part of ejector pulsed detonation engines, together with a turbine – in electric power generators of spacecraft, in a hybrid design – together with turbofan or turboprop engines, etc. In the article are considered various design schemes of pulse detonation engines (PDE): single-chamber and multi-chamber pulsed detonation engines; an ejector PDE system; a hybrid PDE and an integrated detonation-turbine unit with a detonation chamber in the form of a spiral and with a multi-chamber detonation device. The possibility of pulsation frequency increase is realized in the multi-chamber pulsed detonation engine, and the possibility of thrust size increase is realized in PDE with ejector. Replacing traditional chambers with detonation chambers in the construction of gas turbine jet engine will allow providing a decrease in propellant flow rate value from 8 % to 10 % on some estimations. In the hybrid detonation propulsion plant advantages inherent to the detonation cycle combine with positive features of a turbo-compressor jet engine. A combination of PDE and turbine allows creating the cogeneration propulsion system in that a turbine is used for the production of electric power, and detonation chamber – for the creation of thrust impulse. Practical realization of hybrid pulse detonation turbo-engine and the integrated detonation-turbine device is possible if two key complex problems will be solved. These problems are the detonation waves weakening on input in a turbine and the bearing and shaft necessary work resource increasing into a detonation pulsating stream

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