| 摘要 |
A fuel manifold staging valve is provided for use with aircraft engines. A first set of fuel nozzles is associated with a primary manifold, and a second set of fuel nozzles is associated with a secondary manifold. The valve opens on the basis of a constant ratio of fuel flow divided by compressor discharge pressure. The valve detects fuel flow by sensing the pressure drop across the fuel nozzles. This pressure drop is biased by a spring and compared to the compressor discharge pressure. When the ratio is correct for the geometry of the valve, the valve begins to open, allowing fuel to flow to the secondary manifold and associated fuel nozzles.
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