A fuel divider included in a fuel supply device of a gas turbine engine includes a movable member which is movable according to a fuel pressure at a fuel entrance, opens only a pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and opens both of the pilot port and
A fuel divider included in a fuel supply device of a gas turbine engine includes a movable member which is movable according to a fuel pressure at a fuel entrance, opens only a pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and opens both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure. In addition, the fuel divider includes an adjusting means which adjusts a value of the first pressure in such a manner that it applies to the movable member a counter force in a direction opposite to a direction in which the movable member moves according to the fuel pressure at the fuel entrance, and adjusts the counter force.
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1. A fuel supply device of a gas turbine engine, which supplies a fuel to a combustor including a pilot burner and a main burner; the fuel supply device comprising: a pilot fuel passage through which the fuel is supplied to the pilot burner;a main fuel passage through which the fuel is supplied to t
1. A fuel supply device of a gas turbine engine, which supplies a fuel to a combustor including a pilot burner and a main burner; the fuel supply device comprising: a pilot fuel passage through which the fuel is supplied to the pilot burner;a main fuel passage through which the fuel is supplied to the main burner;a collecting fuel passage through which the fuel is supplied to the pilot fuel passage and to the main fuel passage; anda fuel divider which divides the fuel supplied from the collecting fuel passage to feed the fuel to the pilot fuel passage and to the main fuel passage;wherein the fuel divider includes:a fuel entrance into which the fuel supplied from the collecting fuel passage is introduced;a pilot port connected to the pilot fuel passage;a main port connected to the main fuel passage;a movable member which is movable according to a fuel pressure at the fuel entrance, the movable member being configured to open only the pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and to open both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure; andan adjusting means for adjusting a value of the first pressure in such a manner that the adjusting means applies to the movable member a counter force in a direction opposite to a direction in which the movable member moves according to the fuel pressure at the fuel entrance, and adjusts the counter force,wherein the fuel divider further includes a pilot port needle valve element, and a main port needle valve element;wherein the movable member closes the main port via the main port needle valve element when the fuel pressure at the fuel entrance is lower than the first pressure;wherein the movable member gradually decreases an opening degree of the pilot port via the pilot port needle valve element, and gradually increases an opening degree of the main port via the main port needle valve element, with an increase in the fuel pressure at the fuel entrance, when the fuel pressure at the fuel entrance is higher than the first pressure and lower than a second pressure; andwherein the movable member maintains the opening degree of the pilot port at a constant value via the pilot port needle valve element, and maintains the opening degree of the main port at a constant value via the main port needle valve element, irrespective of an increase in the fuel pressure at the fuel entrance, when the fuel pressure at the fuel entrance is higher than the second pressure. 2. The fuel supply device of the gas turbine engine according to claim 1, wherein the adjusting means is actuated based on an entrance temperature of the combustor. 3. The fuel supply device of the gas turbine engine according to claim 2, wherein the adjusting means includes a spring element for applying the counter force to the movable member. 4. The fuel supply device of the gas turbine engine according to claim 3, wherein the adjusting means includes a drive device constituted by a hydraulic cylinder, a stepping motor, or a servo motor; andwherein the drive device is configured to change a length of the spring element to adjust the counter force. 5. The fuel supply device of the gas turbine engine according to claim 1, wherein the adjusting means is actuated based on an entrance pressure of the combustor. 6. The fuel supply device of the gas turbine engine according to claim 5, wherein the adjusting means includes:a spring element for applying the counter force to the movable member; anda drive member which is displaceable according to the entrance pressure of the combustor applied to the drive member and coupled to the spring element; andthe driver member is displaced and a length of the spring element changes to adjust the counter force. 7. A fuel supply device of a gas turbine engine, which supplies a fuel to a combustor including a pilot burner and a main burner; the fuel supply device comprising: a pilot fuel passage through which the fuel is supplied to the pilot burner;a main fuel passage through which the fuel is supplied to the main burner;a collecting fuel passage through which the fuel is supplied to the pilot fuel passage and to the main fuel passage; anda fuel divider which divides the fuel supplied from the collecting fuel passage to feed the fuel to the pilot fuel passage and to the main fuel passage;wherein the fuel divider includes:a fuel entrance into which the fuel supplied from the collecting fuel passage is introduced;a pilot port connected to the pilot fuel passage;a main port connected to the main fuel passage;a movable member which is movable according to a fuel pressure at the fuel entrance, the movable member being configured to open only the pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and to open both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure; anda movable support member that adjusts a value of the first pressure in such a manner that the movable support member applies to the movable member a counter force in a direction opposite to a direction in which the movable member moves according to the fuel pressure at the fuel entrance, and adjusts the counter force,wherein the fuel divider further includes a pilot port needle valve element, and a main port needle valve element;wherein the movable member closes the main port via the main port needle valve element when the fuel pressure at the fuel entrance is lower than the first pressure;wherein the movable member gradually decreases an opening degree of the pilot port via the pilot port needle valve element, and gradually increases an opening degree of the main port via the main port needle valve element, with an increase in the fuel pressure at the fuel entrance, when the fuel pressure at the fuel entrance is higher than the first pressure and lower than a second pressure; andwherein the movable member maintains the opening degree of the pilot port at a constant value via the pilot port needle valve element, and maintains the opening degree of the main port at a constant value via the main port needle valve element, irrespective of an increase in the fuel pressure at the fuel entrance, when the fuel pressure at the fuel entrance is higher than the second pressure. 8. The fuel supply device of the gas turbine engine according to claim 7, wherein the movable support member is actuated based on an entrance temperature of the combustor. 9. The fuel supply device of the gas turbine engine according to claim 8, wherein the movable support member includes a spring element for applying the counter force to the movable member. 10. The fuel supply device of the gas turbine engine according to claim 9, wherein the movable support member includes a drive device constituted by a hydraulic cylinder, a stepping motor, or a servo motor; andwherein the drive device is configured to change a length of the spring element to adjust the counter force. 11. The fuel supply device of the gas turbine engine according to claim 7, wherein the movable support member is actuated based on an entrance pressure of the combustor. 12. The fuel supply device of the gas turbine engine according to claim 11, wherein the movable support member includes:a spring element for applying the counter force to the movable member; anda drive member which is displaceable according to the entrance pressure of the combustor applied to the drive member and coupled to the spring element; andthe driver member is displaced and a length of the spring element changes to adjust the counter force.
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이 특허에 인용된 특허 (4)
Becker Bernard (Mlheim an der Ruhr DEX), Fitting for joining at least one hybrid burner to apparatus for supplying a fluid fuel.
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