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US 2026/0266228 A1Published application
Ratio unit based system for filling a fuel manifold of a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorLouis Duranleau-Hendrickx
Life of this patent
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Abstract
A method includes flowing a fuel to a primary fuel manifold of a gas turbine engine, flowing the fuel to a secondary fuel manifold of the gas turbine engine at a fuel flow rate, monitoring a compressor discharge pressure of the gas turbine engine, determining a ratio of the fuel flow rate of the secondary fuel manifold and the compressor discharge pressure, and adjusting the fuel flow rate of the fuel to the secondary fuel manifold based on the ratio.
Claims20
A method comprising:
- flowing a fuel to a primary fuel manifold of a gas turbine engine;
- flowing the fuel to a secondary fuel manifold of the gas turbine engine at a fuel flow rate;
- monitoring a compressor discharge pressure of the gas turbine engine;
- determining a ratio of the fuel flow rate of the secondary fuel manifold and the compressor discharge pressure;
- and
- adjusting the fuel flow rate of the fuel to the secondary fuel manifold based on the ratio while filling the secondary fuel manifold with the fuel in response to a change in the compressor discharge pressure.
3 more elements
A system comprising:
- a primary fuel manifold;
- a secondary fuel manifold;
- and
- a controller comprising at least one processor configured to cause the system to:
- flow a fuel to the primary fuel manifold;
- flow the fuel to the secondary fuel manifold at a fuel flow rate;
- monitor a compressor discharge pressure;
- determine a ratio of the fuel flow rate of the secondary fuel manifold and the compressor discharge pressure;
- and
- adjust the fuel flow rate of the fuel to the secondary fuel manifold based on the ratio while filling the secondary fuel manifold with the fuel in response to a change in the compressor discharge pressure.
7 more elements
An electronic device configured to fill a fuel manifold of a gas turbine engine, the electronic device comprising:
- at least one sensor configured to capture a compressor discharge pressure of the gas turbine engine;
- and
- at least one processor coupled to the at least one sensor, the at least one processor is configured to:
- flow a fuel to a primary fuel manifold of the gas turbine engine;
- flow the fuel to a secondary fuel manifold of the gas turbine engine at a fuel flow rate;
- monitor the compressor discharge pressure;
- determine a ratio of the fuel flow rate of the secondary fuel manifold and the compressor discharge pressure;
- and
- adjust the fuel flow rate of the fuel to the secondary fuel manifold based on the ratio while filling the secondary fuel manifold with the fuel in response to a change in the compressor discharge pressure.
6 more elements
Dependencies are inferred from the claim text.