Title:
BOUNDARY LAYER CONTROLLER FOR AIRCRAFT
Document Type and Number:
Japanese Patent JP2016107958
Kind Code:
A
Abstract:
PROBLEM TO BE SOLVED: To provide a boundary layer controller configured to correspond to the intake side inner peripheral surface shape of a propulsion engine in an aircraft.SOLUTION: The boundary layer controller includes a venturi generator 10 configured such that when a communication path 9 is opened, a partition body 11 in the venturi generator is controlled by a control system to project from a housing part 12 formed into a recessed shape in an intake side inner peripheral surface, an airflow inlet 14 for capturing an airflow flowing in from the intake port front of a propulsion engine is formed toward the intake port front to be opened, a venturi passage 15 for increasing the speed of the airflow captured from the airflow inlet to reduce pressure is formed by a body bottom part 16, inner surfaces of both side parts and the intake side inner peripheral surface behind the airflow inlet, an airflow outlet for outputting the airflow lowered in pressure by increasing the flow speed is formed to be opened in the front of the intake side inner peripheral surface from the opening position of a discharge hole 7, when the communication path 9 is closed, the partition body is controlled by the control system to be housed in the housing part 12, and the bottom outer surface of the partition body and the intake aide inner peripheral surface constitute a continuous curve surface.SELECTED DRAWING: Figure 2
Inventors:
INOUE FUJIO
Application Number:
JP2014261230A
Publication Date:
June 20, 2016
Filing Date:
December 06, 2014
Export Citation:
Assignee:
INOUE FUJIO
International Classes:
B64C21/06; B64D33/02
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