Actions for High Accuracy Fuel Flowmeter, Phase 1.

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High Accuracy Fuel Flowmeter, Phase 1.

Author
Chin, B.
Published
Mar 1, 1983.
Physical Description
1 electronic document
Additional Creators
Rose, L., Mayer, C., Gregory, W., and Chan, A.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
Technology related to aircraft fuel mass - flowmeters was reviewed to determine what flowmeter types could provide 0.25%-of-point accuracy over a 50 to one range in flowrates. Three types were selected and were further analyzed to determine what problem areas prevented them from meeting the high accuracy requirement, and what the further development needs were for each. A dual-turbine volumetric flowmeter with densi-viscometer and microprocessor compensation was selected for its relative simplicity and fast response time. An angular momentum type with a motor-driven, spring-restrained turbine and viscosity shroud was selected for its direct mass-flow output. This concept also employed a turbine for fast response and a microcomputer for accurate viscosity compensation. The third concept employed a vortex precession volumetric flowmeter and was selected for its unobtrusive design. Like the turbine flowmeter, it uses a densi-viscometer and microprocessor for density correction and accurate viscosity compensation.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19830013043.
Accession ID: 83N21314.
NASA-CR-167893.
NAS 1.26:167893.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15713089