Back to results
US 10,208,672 B2Granted
Accumulator assisted gas turbine engine start system and methods therefor
AssigneeUnited Technologies Corporation
InventorDavid Lloyd Ripley
Life of this patent
Estimating the term…
Abstract
A gas turbine engine assembly is provided having a gas turbine engine and a fuel supply in flow communication with the gas turbine engine. An accumulator is positioned in flow communication between the fuel supply and the gas turbine engine to store fuel pressure in fuel flowing from the fuel supply to the gas turbine engine.
Claims14
An accumulator assisted gas turbine engine start system for a gas turbine engine including a fuel supply, the system comprising:
- an accumulator positioned in flow communication between the fuel supply and the gas turbine engine configured to store fuel pressure in fuel flowing from the fuel supply to the gas turbine engine;
- a gear pump positioned in flow communication between the fuel supply and the accumulator, wherein fuel is delivered from the fuel supply to the accumulator through the gear pump;
- and
- a check valve positioned in flow communication between the fuel supply and the accumulator, wherein the check valve limits a loss of pressure in the accumulator when the gas turbine engine and gear pump are inactive.
1 more element
A gas turbine engine assembly comprising:
- a gas turbine engine;
- a fuel supply in flow communication with the gas turbine engine;
- and
- an accumulator positioned in flow communication between the fuel supply and the gas turbine engine to store fuel pressure in fuel flowing from the fuel supply to the gas turbine engine;
- a gear pump positioned in flow communication between the fuel supply and the accumulator, wherein fuel is delivered from the fuel supply to the accumulator through the gear pump;
- and
- a check valve positioned in flow communication between the fuel supply and the accumulator, wherein the check valve limits a loss of pressure in the accumulator when the gas turbine engine and gear pump are inactive.
4 more elements
A method of controlling a pressure of fuel delivered from a fuel supply to a gas turbine engine comprising:
- storing fuel pressure in the fuel flowing from the fuel supply within an accumulator;
- charging the accumulator with high pressure fuel by running the gas turbine engine;
- supplying fuel to the gas turbine engine from the accumulator;
- and
- limiting a loss of pressure in the accumulator with a check valve positioned in flow communication between the fuel supply and the accumulator when the gas turbine engine is inactive.
2 more elements
Dependencies are inferred from the claim text.