US 8,408,233 B2Granted

Flow control system and method for controlling two positive displacement pumps

AssigneeHamilton Sundstrand Corporation

InventorsCharles E. Reuter, Aaron V. Price, Todd Haugsjaahabink, Yukinori Sato, John J. Wichowski

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Abstract

A fuel flow system for a gas turbine engine includes a first pump, a second pump, a bypass loop, an integrating bypass valve and a pilot valve. The first pump connects to an actuator and a metering valve. The second pump connects to the metering valve and is arranged in parallel with the first pump. The bypass loop recycles fuel flow from the first pump and the second pump to inlets of the first pump and second pump integrating bypass valve includes first and second windows. The first window regulates fuel from the first pump through the bypass loop and the second window that regulates fuel from the second pump through the bypass loop. The pilot valve controls the size of the first and second windows.

Claims17

Dependent claims

A fuel flow system for a gas turbine engine, the system comprising:

a first pump connected to a nozzle;
a second pump connected to the nozzle and arranged in parallel with the first pump;
a metering valve disposed downstream from the first pump and upstream from the nozzle:
an actuator disposed downstream from the first pump and upstream from the metering valve, the actuator receiving a high pressure fluid from the first pump and returning a low pressure fluid upstream to inlets of the first pump and the second pump;
a bypass loop that recycles fuel flow from the first pump and the second pump to the inlets of the first pump and second pump;
an integrating bypass valve having a first window that regulates fuel from the first pump through the bypass loop and a second window that regulates fuel from the second pump through the bypass loop;
and
a pilot valve that senses a pressure drop across the metering valve and in response either directs a portion of the high pressure fluid upstream from the actuator or directs a portion of the low pressure fluid downstream from the actuator to the integrating bypass valve to control a size of the first window and a size of the second window of the integrating bypass valve.

5 more elements

A method for controlling a fuel flow system for a gas turbine engine, the method comprising the steps:

dividing fuel flow from a source between an inlet of a first pump and an inlet of a second pump;
directing a first portion of the fuel flow from the first pump to an actuator, the actuator returning the first portion of the fuel flow upstream from the inlet of the first pump and the inlet of the second pump;
directing a second portion of the fuel flow from the first pump through a metering valve located downstream of the first pump;
controlling flow of a third portion of the fuel flow from the first pump through a bypass loop and back to the inlets of the first and second pumps with a first window of an integrating bypass valve, wherein the third portion of fuel flow from the first pump is in excess of flow requirements of the metering valve;
controlling the fuel flow from the second pump through the bypass loop and back to the inlets of the first and second pumps with a second window of an integrating bypass valve;
controlling the size of the first and second windows with a pilot valve;
and wherein controlling the size of the first and second windows with the pilot valve comprises:
sensing a pressure drop across the metering valve;
responding to the pressure drop by directing either a portion of the fuel flow upstream from the actuator and downstream from the first pump or a portion of the fuel flow downstream from the actuator to a single side of the integrating bypass valve until a regulated pressure setting is achieved.

6 more elements

Dependencies are inferred from the claim text.