Miniaturized High Speed Controls for Turbine Engines (Fabrication and Test)
Abstract
This report summarizes the design and development of control components and high speed fuel pump technology for future drone, missile and RPV gas turbine engines. The hardware was designed for installation on an existing engine to provide a vehicle for control mode demonstration and evaluation testing. The developed hardware includes a fluidic/linear variable differential transformer delta P/P airflow sensor, a radiation pyrometer for sensing turbine blade temperature, three pressure transducers for sensing burner pressure (variable capacitance, strain gage, and potentiometric types), a 70,000 rpm centrifugal pump and proportional solenoid-operated fuel metering system, a magnetic clutch-driven 12,000 rpm gear pump for fuel metering and fuel pressurization, and an electronic unit for interfacing these components with an engine test cell digital computer.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1974
- Accession Number
- ADA006108
Entities
People
- A. H. White
- D. G. Burnell
- M. A. Cole
- R. D. Zagranski
- T. B. Morrison