Wide Range Flow Control Program
Abstract
The objective of the Wide Range Flow Control Program was to establish propellant flow control valve technology including techniques for mixture ratio control for deep throttling of liquid fluorine-liquid hydrogen rocket engine systems for rated thrust levels between 15 and 45K. The effort described in this supplemental report met the specific objective of proving the technique of controlling the flow of liquid hydrogen by means of a cavitating venturi control valve. Typical inlet conditions for the hydrogen during the tests were a pressure of 465 plus or minus 10 psia and a temperature of 40 deg to 45 deg R. The design mass flow rate at the 100 percent throttle setting was 2.88 lb/sec. Although the hydrogen flow stream was at a super-critical pressure it was demonstrated to act as a subcritical cavitating liquid at the low static pressures prevailing in the valve throat. The feasibility of control was demonstrated over a flow range in excess of 50 to 1 with valve overall differential pressures from 20 to 400 psid. A recovery of 92 percent on the cavitation line at full throttle position was observed. A discharge coefficient of 0.9 from 2 to 10 percent and 0.875 from 20 percent through 110 percent was calculated from the data.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1969
- Accession Number
- AD0854595
Entities
People
- F. Merritt
- L. Dumont
Organizations
- TRW Inc.