Material handling systems for the fluidized-bed combustion boiler at Rivesville, West Virginia

The 300,000 lbs/hr steam capacity multicell fluidized-bed boiler (MFB) utilizes complex material handling systems. The material handling systems can be divided into the following areas: (1) coal preparation; transfer and delivery, (2) limestone handling system, (3) fly-ash removal and (4) bed material handling system. Each of the above systems are described in detail and some of the potential problem areas are discussed. A major potential problem that exists is the coal drying system. The coal dryer is designed to use 600 F preheated combustion air as drying medium and the dryer effluent is designed to enter a hot electrostatic precipitator (730 F) after passage through a cyclone. Other problem areas to be discussed include the steam generator coal and limestone feed system which may have operating difficulties with wet coal and/or coal fines

Längenskalen bei der Strahlzerstäubung bei hohem Gegendruck

Dei Phänomene bei der Zerstäubung runder Flüssigkeitsstrahlen sind bis heute nicht vollständig geklärt. Für das Verständnis der Vorgänge sowie der Analyse der Einflussgrößen und eine Modellbildung sind detaillierte quantitative Messungen erforderlich, wie ´sie u.a. in (1,2), und (3) zu finden sind. Da es viele Anwendungen unter Hochdruckbedingungen gibt, wie z.B. Dieselmotor und Raketenbrennkammer, sind Untersuchungen unter thermodynamisch überkritischen Bedingungen anzustreben. Zur quantitativen Auswertung von Schattenaufnahmen wurde ein Programm entwickelt, das in der Lage ist, die Größe sichtbarer Strukturen im Strahl und in der Scherschicht sowie Wellenlängen und Amplituden auf der Strahloberfläche zu ermitteln. Die Einspritzung einer Flüssigkeit mit koaxialer Gasströmung in einem Ringspalt ermöglichte die unabhängige Untersuchung der Einflüsse der Einspritzgeschwindigkeit der Flüssigkeit, der Relativgeschwindigkeit zwischen Flüssigkeit und Gas, sowie des Messkammerdrucks. Damit war es möglich, die Einflüsse der aerodynamischen Kräfte und der turbulenten Vorgänge im Strahl getrennt voneinander zu untersuchen

Characterization of Cryogenic Injection at Supercritical Pressure

Understanding the Complex environment of the rocket chamber involves good knowledge of the injection phenomena. Understanding the injection phenomena allows the rocket designer to employ time and cost saving modeling tools to design a higher performance rocket engine. The rocket engine performance is highly dependent on the injection processes within the chamber. This project looked at injection processes in the supercritical regime of the injected fluid, cryogenic nitrogen, in order to better understand realistic conditions in the rocket engines of today. The investigation considered test conditions from 4.0 to 6.0 MPa at two different injection velocities and temperatures. Experimental data taken by Raman imaging and Shadowgraphy were compared to computational models for these various test conditions. The test data allows comparisons of density, length scales and jet spreading angles. The results validate the computational models fairly well and agree with classical theory.This agreement allows further use of the models to predict injection behavior under these operating conditions. Also, further comparisons were made between the various test cases using the computational models to consider the effects of pressure, velocity and temperature variations on the cryogenic jet

Raman Measurements of Cryogenic Injection at Supercritical Pressure

Understanding the complex environment of rocket chambers involves a good knowledge of injection phenomena and gives the designer the ability to employ time and cost saving modeling tools to design a higher performance engine. This project looked at injection processes in the supercritical regime using cryogenic nitrogen. Experimental data taken by 2-D Raman imaging allowed the comparison of density and divergence angels with computational models. These parameters provide much information about the jet development and mixing with the surrounding gas. The process used to derive divergence angles from Raman images proves difficult to compare directly with other techniques

Experimental and Numerical Investigation of Cryogenic Jet Atomization

Unerstanding the complex environment of the rocket combustion chamber involves a good unerstanding of the injection phenomena. This understanding allows the rocket designer to employ time and cost saving modeling tools to better design a higher performing rocket engine. The rocket engine performance is highly dependent on the injection processes within the chamber. This project looked at injection processes in the supercritical regime of the injected fluid, cryogenic nitrogen, in order to better understand realistic conditions in the rocket engines of today. The investigation considers test conditions from 4.0 to 6.0 MPa at two different injection velocities and temperatures. Experimental data taken by Raman imaging and shadowgraphy are compared to computational models for these various test conditions. The test data allow comparisons of density, potential core length, length scales and jet spread angle. The results validate the computational models fairly well. This agreement allows further research to use the models to predict injection behavior under these operating conditions. Further comparisons were made between the various test cases using the computational models considering the effects of pressure, Velocity and temperature variations on the cryogenic jet