Back to results
US 5,289,685 AGranted
Fuel supply system for a gas turbine engine
AssigneeGeneral Electric Company
InventorRobert J. Hoffa
Life of this patent
Estimating the term…
Abstract
In a gas turbine engine, fuel is supplied to a fuel metering valve which is connected to a shutoff valve. The shutoff valve supplies fuel to a manifold. Fuel flow between the manifold and main fuel nozzles is controlled by fuel staging valves while the pilot nozzle is connected directly to the manifold by a fuel line which may include an orifice. The orifice is designed to match the flow in the pilot nozzle with the flow in main nozzles when the fuel staging valve is on.
Claims3
A gas turbine engine fuel control comprising:
- a triple annular combustor comprising a central ring of pilot fuel nozzles and inner and outer rings of main fuel nozzles,
- a fuel manifold connecting said combustor to a fuel source;
- a fuel metering valve controlling the flow of fuel from said fuel source to said fuel manifold;
- a plurality of conduits connecting said pilot nozzles to said manifold;
- and
- a plurality of selectively controllable fuel staging valves controlling the flow of fuel from said manifold to said main nozzles.
3 more elements
Dependencies are inferred from the claim text.