Handbook of Turbomachinery Second Edition Revised - Ventech!

section is intended to place today’s capabilities (and shortcomings) in a
somewhat better perspective. Following this, sections are devoted to each of
several key components of rocket turbomachinery systems. Where it is
necessary or particularly insightful, various design issues are discussed as
they relate to the various rocket engine thermodynamic cycles in existence
today or in the recent past. Some cycles may be discussed together in
relation to a particular component when the cycles place similar demands or
restrictions on component design or performance.
Although this chapter is not intended to function as a design guide, I
have found it necessary to make certain assumptions as to the reader’s
familiarity with the subject. A knowledge of the fundamental concepts of
turbomachinery energy exchange will be needed, as well as a grasp of
velocity diagrams and their relationship to machinery performance. Topics
such as these are not specifically covered, but a certain familiarity with them
will make discussions regarding things like design tradeoffs much more
intuitive.
It is hoped that this chapter will serve as a starting point for readers
(both advanced students and practicing engineers at the BSE level) who wish
to efficiently learn some aspect of turbomachinery as it relates to rocket
propulsion systems. I attempt to present a collection of my own experiences
and the experiences of others as related to me, as well as a collection of the
references I have found most helpful.
The development of turbomachinery for use in rocket engines has
involved both the government of the United States and large portions of the
American industrial base. Examples of firms that are deeply involved
include the Aerojet General Corp., Pratt and Whitney Division of United
Technologies Corp., Rocketdyne Division of Rockwell International, and
the Turbomachinery Division of Sunstrand Corp., to name just a few. With
the help of firms such as these, the design, development, and production of
turbomachinery have reached quite a high state of refinement. For example,
the combined turbomachinery of a cluster of three Space Shuttle main
engines (SSMEs) moves nearly 1,600,000 lb of cryogenic propellant through
the engines in approximately 510–520 sec. In the process, head rises
approaching 200,000 ft are achieved in the engine’s fuel systems.
In more than 100 Space Shuttle flights to date, not a single
turbomachinery failure has occurred. Similar systems have been in
operation on several expendable launch vehicles for nearly 30 years with
comparable records of success. As a result of the talent brought to bear on
the turbomachinery problem, the record of reliability achieved thus far is
truly outstanding. Enormous quantities of propellant have been moved
against high pressures by marvelously compact machinery with rarely a
failure.
Copyright © 2003 Marcel Dekker, Inc.