A simplified fuel control approach for low-cost aircraft gas turbinesA hydromechanical approach to the problem of reducing the compexity and cost of turbine fuel controls without impairing performance and reliability is described and analyzed. The study applies to the modification of long-range high-performance turbine engines to meet short-range missile requirements. The generalized acceleration and deceleration control parameters are studied, and variable-orifice relations for acceleration and deceleration limits are derived. The hydromechanical speed-sensing and multiplying circuit and the fuel control schematic diagram are discussed.
Document ID
19740028052
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gold, H. (NASA Lewis Research Center Cleveland, Ohio, United States)