Aircraft propulsion system inlet structure with variable airflow inlet area
AssigneeRohr, Inc.
InventorTimothy Gormley
Life of this patent
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Abstract
An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a nacelle inlet structure. The nacelle inlet structure includes an inner inlet opening, an outer inlet opening and a rotating structure. The rotating structure extends circumferentially about the inner inlet opening. The rotating structure is configured to rotate about an axis between a first position and a second position. The rotating structure at least partially closes the outer inlet opening in the first position. The rotating structure at least partially opens the outer inlet opening in the second position.
Claims12
An assembly for an aircraft propulsion system, comprising:
- a nacelle inlet structure including an inner inlet opening, an outer inlet opening and a rotating structure;
- the rotating structure extending circumferentially about the inner inlet opening;
- the rotating structure configured to rotate about an axis between a first position and a second position, wherein the rotating structure at least partially closes the outer inlet opening in the first position, and the rotating structure at least partially opens the outer inlet opening in the second position;
- the rotating structure forming an outer peripheral boundary of the inner inlet opening;
- and
- the rotating structure forming an inner peripheral boundary of the outer inlet opening.
An assembly for an aircraft propulsion system, comprising:
- a nacelle inlet structure including an inner inlet opening, an outer inlet opening and a rotating structure;
- the rotating structure extending circumferentially about the inner inlet opening;
- the rotating structure configured to rotate about an axis between a first position and a second position, wherein the rotating structure at least partially closes the outer inlet opening in the first position, and the rotating structure at least partially opens the outer inlet opening in the second position;
- and
- the rotating structure forming an inlet lip of the nacelle inlet structure.
An assembly for an aircraft propulsion system, comprising:
- a nacelle inlet structure including an inner inlet opening, an outer inlet opening and a rotating structure;
- the rotating structure extending circumferentially about the inner inlet opening;
- the rotating structure configured to rotate about an axis between a first position and a second position, wherein the rotating structure at least partially closes the outer inlet opening in the first position, and the rotating structure at least partially opens the outer inlet opening in the second position;
- the nacelle inlet structure further including a second outer inlet opening;
- the rotating structure at least partially closing the second outer inlet opening in the first position;
- and
- the rotating structure at least partially opening the second outer inlet opening in the second position.
An assembly for an aircraft propulsion system, comprising:
- a nacelle inlet structure including an inner inlet opening, an outer inlet opening and a rotating structure;
- the rotating structure extending circumferentially about the inner inlet opening;
- the rotating structure configured to rotate about an axis between a first position and a second position, wherein the rotating structure at least partially closes the outer inlet opening in the first position, and the rotating structure at least partially opens the outer inlet opening in the second position;
- the nacelle inlet structure further including a static structure that extends circumferentially about the rotating structure;
- and
- the outer inlet opening radially between the rotating structure and the static structure.
Dependencies are inferred from the claim text.