Control of low compressor vanes and fuel for a gas turbine engine

Patent · Tue Jul 28 04:00:00 EDT 1992

OSTI ID:7167029

Marcas, J A

This patent describes a gas turbine engine for powering aircraft having a pair of spools. It comprises: a high pressure compressor/turbine combination and a fan/low pressure compressor and turbine combination solely aerodynamically coupled, a burner for combusting fuel and air for powering the turbines, fuel regulating means for regulating the flow of fuel to the burner and variable area vanes for regulating the air flow to the fan/low pressure, means for controlling the engine to operate on a low pressure compressor steady state operating line. This patent describes improvement in control means and including means for generating a signal indicative of N[degrees]1 lock responsive to low pressure compressor speed and the position of the power lever to regulate rapid accelerations and decelerations in response to a preselected low pressure compressor airflow parameter for controlling the variable vanes and the fuel regulating means.

• Assignee: United Technologies Corp., Hartford, CT (United States)
• Patent Number(s): A; US 5133182
• Application Number: PPN: US 7-448391
• OSTI ID: 7167029
• Country of Publication: United States
• Language: English

Related Subjects

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
320201 -- Energy Conservation
Consumption
& Utilization-- Transportation-- Air & Aerospace
33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
330603 -- Vehicle Design Factors-- Engine System
AERODYNAMICS
AIRCRAFT COMPONENTS
COMPRESSORS
CONTROL EQUIPMENT
DESIGN
ENGINES
EQUIPMENT
FLOW REGULATORS
FLUID MECHANICS
FUEL SYSTEMS
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MECHANICS