Dynamic response testing of transient pressure transducers for liquid propellant rocket combustion chambers
dynamicresponset00bent.pdf (7.582Mb)Abstract
An investigation of the dynamic response of transient pressure
transducers intended for use in liquid propel lant rocket combustion
chambers was undertaken. Shock tube testing included optimization of
operating techniques especially the tailored interface and the effects
of ground shock and other mounting influences. The Kistler 60IA quartz
transducer was evaluated as a monitor for the Princeton Sinusoidal
Pressure Generator (SPG) and a number of water-cooled transient transducers
were evaluated for comparison with results from the SPG. An
investigation was conducted which satisfactorily demonstrated the
practical value of the SPG as a primary test device for transient
pressure transducer evaluations to 10,000 cps. During evaluations
special consideration was given to developing operating techniques
and improving SPG chamber design. The results from shock tube and
the SPG show close agreement up to 10,000 cps, the present limit of
usable SPG range. Transducers were then tested in experimental liquid
propellant rocket motors to compare laboratory measured characteristics
with actual transducer performance.
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