Multi-system thrust reverser for aircraft propulsion system
AssigneeRohr, Inc.
InventorTimothy Gormley
Life of this patent
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Abstract
A method is provided for accessing an engine core for an aircraft propulsion system. During this method, a first outer structure section of a nacelle is uncoupled from a second outer structure section of the nacelle. The second outer structure section is pivoted to an open position. A first inner structure section of the nacelle is uncoupled from a second inner structure section of the nacelle. The second inner structure section is pivoted to an open position. The first outer structure section and the first inner structure section are pivoted to an open position while the first inner structure section is structurally linked to the first outer structure section.
Claims16
An assembly for an aircraft propulsion system, comprising:
- a first thrust reverser system including a first thrust reverser passage, a first blocker door and a first door deployment linkage pivotally coupled to the first blocker door, the first thrust reverser system configured to move the first blocker door from a first door stowed position to a first door deployed position using the first door deployment linkage, the first blocker door located radially outboard of a bypass flowpath relative to an axis when the first blocker door is in the first door stowed position, and the first blocker door configured to redirect a first portion of air flowing in the bypass flowpath through the first thrust reverser passage when the first blocker door is in the first door deployed position;
- and
- a second thrust reverser system including a second thrust reverser passage, a second blocker door and a second door deployment linkage pivotally coupled to the second blocker door, the second thrust reverser system configured to move the second blocker door from a second door stowed position to a second door deployed position using the second door deployment linkage, the second blocker door located radially outboard of the bypass flowpath relative to the axis when the second blocker door is in the second door stowed position, the second blocker door configured to redirect a second portion of the air flowing in the bypass flowpath through the second thrust reverser passage when the second blocker door is in the second door deployed position, and the second door deployment linkage having a different configuration than the first door deployment linkage;
- wherein the second blocker door is circumferentially offset from the first blocker door about the axis;
- wherein the first blocker door forms a first outer peripheral boundary of a first portion of the bypass flowpath when the first blocker door is in the first door stowed position;
- and
- wherein the second blocker door forms a second outer peripheral boundary of a second portion of the bypass flowpath when the second blocker door is in the second door stowed position.
An assembly for an aircraft propulsion system, comprising:
- a stationary structure;
- a nacelle outer structure including a first outer structure section and a second outer structure section, the first outer structure section disposed to a first side of the stationary structure and pivotally coupled to the stationary structure, the first outer structure section configured with a first thrust reverser system, the second outer structure section disposed to a second side of the stationary structure and pivotally coupled to the stationary structure, and the second outer structure section configured with a second thrust reverser system;
- and
- a nacelle inner structure including a first inner structure section and a second inner structure section, the first inner structure section disposed to the first side of the stationary structure and pivotally coupled to the stationary structure, the first inner structure section linked to the first outer structure section by the first thrust reverser system, the second inner structure section disposed to the second side of the stationary structure and pivotally coupled to the stationary structure, and the second inner structure section decoupled from the second thrust reverser system.
Dependencies are inferred from the claim text.