Experimental Investigation of Turbojet Thrust Augmentation Using an Ejector (Paperback) (ISBN-13: 9781249600787)

In recent years a significant number of commercially available small turbines have become available. At the same time unmanned aerial vehicles and smart munitions have decreased in size while their endurance needs have increased. With these new platform requirements comes the need for a propulsion system with reliability, good endurance and low acoustic signature. There has been much research accomplished in the area of steady cold flow primary sources, but little experimental work has been done using a gas turbine as a steady flow hot source. This investigation concerns the performance of an ejector driven by a small gas turbine. Aircraft applicability was a deciding factor in test geometry. Varying both engine throttle and the ejector's downstream distance resulted in peak augmentation values of nearly 1.4.

This work has been selected by scholars as being culturally important, and is part of the knowledge base of civilization as we know it. This work was reproduced from the original artifact, and remains as true to the original work as possible. Therefore, you will see the original copyright references, library stamps (as most of these works have been housed in our most important libraries around the world), and other notations in the work.

This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work.

As a reproduction of a historical artifact, this work may contain missing or blurred pages, poor pictures, errant marks, etc. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.