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Fluidic traverse actuator

An actuator, a fluid dynamic technique applied in the direction of passing through a cylindrical rotating member, affecting the flow of air over the surface of an aircraft, reducing drag, etc.

Active Publication Date: 2014-05-14
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, adding a separate air compressor also results in additional weight

Method used

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Examples

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Embodiment Construction

[0032] The following detailed description is exemplary in nature and not intended to limit the disclosure and application, and uses embodiments of the disclosure. Descriptions of specific devices, techniques, and applications are provided as examples only. Modifications to the examples described herein will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other examples and applications without departing from the spirit and scope of the present disclosure. The present disclosure should be accorded scope consistent with the claims and not limited to the examples described and shown herein.

[0033] Embodiments of the disclosure may be described in terms of functional and / or logical block components and various processing steps. It should be appreciated that such logical block components may be realized by any number of hardware, software, and / or firmware components configured to perform the specified functions. For t...

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Abstract

A system and method for a self-rotating fluidic traverse actuator are provided. A turbine rotates in response to a fluid flow, and an outer cylinder with a longitudinal slot that ejects the fluid flow. An inner cylinder rotates inside the outer cylinder in response to a rotation of the turbine and at least one helical slot of the inner cylinder ejects the fluid flow into the longitudinal slot.

Description

technical field [0001] Embodiments of the present disclosure relate generally to fluid dynamic design. More specifically, embodiments of the present disclosure relate to the design of fluid actuators. Background technique [0002] Flow control can be used to enhance lift performance using a fluid source, such as bleed air from an engine or a dedicated compressor. The airflow from the fluid source is ejected from the aircraft in the general direction of airflow across the top of the wing or flap. The jet of air imparts momentum to the air flow over the wing or flap. This momentum causes the airflow to better follow the surface of the wing or flap. Thus, the circulating flow is increased around the entire airfoil including the wing or flaps and a higher lift is obtained. [0003] However, current airflow control methods require a significant amount of injected airflow to achieve meaningful design goals. Aircraft engines can be used to supply air to be actuated by "exhaust...

Claims

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Application Information

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IPC IPC(8): B64C23/02
CPCB64C2230/04Y10T29/4932B64C21/04Y02T50/10
Inventor A·施米勒维驰S·R·肯特
Owner THE BOEING CO
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