Multi-mode Thermoacoustic Actuator
AssigneeThe Government of the United States of America, as represented by the Secretary of the Navy
InventorSteven G. Tuttle
Life of this patent
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Abstract
A combustor including a first perforated layer including a first opening having a first diameter, wherein the first opening is configured to receive a flow of fluid including a fuel and air mixture; and impart a first rotational instability to the flow of fluid that is dependent on the first diameter; and a second perforated layer surrounding a combustion area, wherein the second perforated later includes a second opening having a second diameter, and wherein the second layer is located between the first layer and the combustion area.
Claims18
A combustor comprising:
- a first perforated layer comprising a first opening having a first diameter, wherein the first opening is configured to:
- receive a flow of fluid comprising a fuel and air mixture;
- and
- impart a first rotational instability to the flow of fluid that is dependent on the first diameter;
- and
- a second perforated layer surrounding a combustion area, wherein the second perforated later comprises a second opening having a second diameter, and wherein the second layer is located between the first layer and the combustion area.
A method for increasing an efficiency of an engine, the method comprising:
- receiving a flow of fluid comprising a fuel and air mixture through a first opening in a first perforated layer of a combustor of the engine;
- imparting a first rotational instability to the flow of fluid, wherein the first rotational instability is dependent on a first diameter of the first opening;
- and
- positioning a second perforated layer between the first layer and a combustion area of the combustor, wherein the second layer comprises a second opening.
A combustor comprising:
- a plurality of perforated surrounding layers, comprising:
- a first perforated surrounding layer comprising a first opening, wherein the first opening is configured to:
- receive a flow of fuel and air mixture;
- and
- impart a first rotational instability to the flow, wherein the first rotational instability is dependent on a first diameter of the first opening;
- and
- a second perforated surrounding layer comprising a second opening, wherein the second layer is located between the first layer and a combustion area;
- and
- a plurality of intermediate perforated surrounding layers, located between the first and second layers, wherein each of the intermediate layers comprise a corresponding intermediate plurality of openings configured to pass the flow and impart a plurality of intermediate rotational instabilities to the flow.
Dependencies are inferred from the claim text.