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US 10,294,870 B2Granted
Distributed engine accessory drive
AssigneeUnited Technologies Corporation
InventorGary D. Roberge
Life of this patent
Estimating the term…
Abstract
An accessory drive system for an aircraft gas turbine engine is disclosed. The system may comprise an engine case including a core engine cowl and at least a first accessory drive gearbox disposed within the core engine cowl. The at least first accessory drive gearbox may be operatively connected to one or more accessories remotely located therefrom.
Claims11
A gas turbine engine, comprising:
- an accessory drive system;
- a core engine surrounded by a core engine cowl;
- a core engine envelope defined between the core engine and the core engine cowl, the accessory drive system including a first accessory drive gearbox disposed within the core engine envelope;
- a first accessory and a second accessory, operatively connected to the first accessory drive gearbox and disposed separately and away from the first accessory drive gearbox, thereby maximizing use of spatial storage limitations within the core engine envelope;
- and
- a separate second accessory drive gearbox operatively connected to a third accessory and a fourth accessory, wherein the first accessory is connected to the first accessory drive gearbox via a first flexible shaft, the first flexible shaft comprising a flexible outer sheath surrounding an inner shaft, the flexible outer sheath being fixed with respect to the inner shaft, and wherein the second accessory is connected to the first accessory drive gearbox via a second flexible shaft, the second flexible shaft comprising a flexible outer sheath surrounding an inner shaft, the flexible outer sheath being fixed with respect to the inner shaft, and wherein the third accessory is connected to the second accessory drive gearbox via a third flexible shaft, the third flexible shaft comprising a flexible outer sheath surrounding an inner shaft, the flexible outer sheath being fixed with respect to the inner shaft, and wherein the fourth accessory is connected to the second accessory drive gearbox via a fourth flexible shaft, the fourth flexible shaft comprising a flexible outer sheath surrounding an inner shaft, the flexible outer sheath being fixed with respect to the inner shaft, wherein the first accessory, the second accessory, the third accessory and the fourth accessory are used to operate the gas turbine engine.
3 more elements
A method of arranging gearboxes and accessories in a gas turbine engine, comprising:
- providing a first accessory drive gearbox within a core engine envelope;
- connecting the first accessory drive gearbox to a first accessory that is located separately and away from the first accessory drive gearbox and a second accessory that is located separately and away from the first accessory drive gearbox;
- providing a second accessory drive gearbox;
- and
- connecting the second accessory drive gearbox to a third accessory and a fourth accessory, wherein the first accessory is connected to the first accessory drive gearbox via a first flexible shaft, the first flexible shaft comprising a flexible outer sheath surrounding an inner shaft, the flexible outer sheath being fixed with respect to the inner shaft, and wherein the second accessory is connected to the first accessory drive gearbox via a second flexible shaft, the second flexible shaft comprising a flexible outer sheath surrounding an inner shaft, the flexible outer sheath being fixed with respect to the inner shaft, and wherein the third accessory is connected to the second accessory drive gearbox via a third flexible shaft, the third flexible shaft comprising a flexible outer sheath surrounding an inner shaft, the flexible outer sheath being fixed with respect to the inner shaft, and wherein the fourth accessory is connected to the second accessory drive gearbox via a fourth flexible shaft, the fourth flexible shaft comprising a flexible outer sheath surrounding an inner shaft, the flexible outer sheath being fixed with respect to the inner shaft, wherein the first accessory, the second accessory, the third accessory and the fourth accessory are used to operate the gas turbine engine.
2 more elements
Dependencies are inferred from the claim text.