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Vafn systems with improved drive coupling assemblies and brakes

a technology of drive coupling and assembly, which is applied in the direction of liquid fuel engines, machines/engines, reaction engines, etc., can solve the problems of reducing fuel efficiency and undesirably increasing the overall engine weigh

Inactive Publication Date: 2013-03-28
HONEYWELL INT INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent describes an actuation system for a variable area fan nozzle assembly of an aircraft. The system includes a motor, a nozzle, and a drive coupling assembly. The drive coupling assembly has two positions: a first position in which torque is transferred to the nozzle to move it, and a second position in which torque is not transferred. The assembly has two end portions that mate in the first position and disengage in the second position. The technical effect of this system is that it enables precise control over the nozzle's movement, allowing for better performance and efficiency of the aircraft's fan.

Problems solved by technology

However, existing variable area fan nozzles typically utilize relatively complex mechanisms that undesirably increase overall engine weight and decrease fuel efficiency.

Method used

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  • Vafn systems with improved drive coupling assemblies and brakes
  • Vafn systems with improved drive coupling assemblies and brakes
  • Vafn systems with improved drive coupling assemblies and brakes

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Embodiment Construction

[0023]The following detailed description is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. As used herein, the word “exemplary” means “serving as an example, instance, or illustration.” Thus, any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments. All of the embodiments described herein are exemplary embodiments provided to enable persons skilled in the art to make or use the invention and not to limit the scope of the invention which is defined by the claims. Furthermore, there is no intention to be bound by any expressed or implied theory presented in the preceding technical field, background, brief summary, or the following detailed description.

[0024]FIG. 1 is a perspective view of portions of an aircraft jet engine system 100 with a fan case 102. Typically, the fan case 102 encloses a turbofan engine, as described below, and mounts t...

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Abstract

An actuation system is provided for a variable area fan nozzle assembly of an aircraft. The actuation system includes a motor configured to generate a torque; a nozzle; and a drive coupling assembly coupled to the motor and the nozzle. The drive coupling assembly includes a first position in which the torque from the motor is transferred to the nozzle to translate the nozzle and a second position in which the torque from the motor is not transferred to the nozzle. The drive coupling assembly includes a first end portion and a second end portion, the first and second end portions mating with one another in the first position and disengaged from one another in the second position.

Description

CROSS-REFERENCE TO RELATED APPLICATION[0001]This application claims the benefit of U.S. Provisional Application No. 61 / 540,325, filed Sep. 28, 2011 and U.S. Provisional Application No. 61 / 540,318, filed Sep. 28, 2011, the entirety of each being hereby incorporated by reference.TECHNICAL FIELD[0002]The present invention relates to variable area fan nozzle assemblies and more particularly to actuation systems for variable area fan nozzle assemblies of jet engines.BACKGROUND[0003]Conventional gas turbine engines generally include a fan section and a core engine with one or more compressors, a combustion section, and one or more turbines. The fan section and the core engine are disposed about a longitudinal axis and are enclosed within a case assembly. During operation, the fan section induces a first portion of air into the core engine and a second portion of air into a bypass flow path.[0004]In the core engine, air is compressed, mixed with fuel, combusted, expanded through the turbin...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D17/10F01D17/00
CPCF02K1/64F02K1/68Y02T50/671F02K1/763F02K1/766F02K1/70Y02T50/60
Inventor CHAKKERA, KEVIN K.VAUGHAN, RONMCGILL, MICHAELBIRN, STEPHEN
Owner HONEYWELL INT INC