Multi-mode thermoacoustic actuator
AssigneeThe 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.
Claims10
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 layer comprises a second opening having a second diameter, and wherein the second layer is located between the first layer and the combustion area;
- and
- wherein the second opening is configured to impart a second rotational instability to the flow that is dependent on:
- the second diameter of the second opening;
- an offset distance between a first axis of the first opening and a second axis of the second opening;
- and a distance between the first and second perforated layers.
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;
- positioning a second perforated layer between the first layer and a combustion area of the combustor, wherein the second layer comprises a second opening;
- and imparting, using the second opening, a second rotational instability to the flow of fluid that is dependent on:
- a second diameter of the second opening;
- an offset distance between a first axis of the first opening and a second axis of the second opening;
- and a distance between the first and second perforated layers.
Dependencies are inferred from the claim text.