System and method for operating a thrust reverser for a turbofan propulsion system

A technology of thrust reverser and turbofan, applied in jet propulsion, high-efficiency propulsion technology, machine/engine, etc.

Active Publication Date: 2012-07-04
伍德沃德HRT公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

By including a second locking system between the first shroud and the second shroud, the thrust reverser assembly shown in the '713 patent may require flexible hoses and / or cables to bridge the gap between the fixed shroud and the first shroud during operation. gaps between enclosures, which can undesirably expose these components to adverse environmental conditions

Method used

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  • System and method for operating a thrust reverser for a turbofan propulsion system
  • System and method for operating a thrust reverser for a turbofan propulsion system
  • System and method for operating a thrust reverser for a turbofan propulsion system

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Embodiment Construction

[0022] The exemplary methods and systems described herein overcome at least some of the disadvantages of known turbofan propulsion systems by providing a thrust reverser assembly that facilitates regulating airflow discharged from a turbofan engine assembly. Additionally, the thrust reverser assembly includes a first translating cowl and a second translating cowl each positionable relative to the fixed cowl to adjust a discharge zone defined between the second translating cowl and the turbofan engine assembly. Additionally, the thrust reverser assembly includes an actuator operatively coupled to the second transcowl, and a positioning assembly configured to engage the actuator to selectively move the first transcowl. By selectively positioning the first transcowl and the second transcowl, the thrust reverser assembly helps regulate airflow exhausted through the turbofan propulsion system to improve the operating efficiency of the turbofan propulsion system.

[0023] figure 1 ...

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Abstract

The invention relates to a system and a method for operating a thrust reverser for a turbofan propulsion system. A thrust reverser assembly for use in a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine and a core cowl which circumscribes the core gas turbine engine. A nacelle is positioned radially outward from the core cowl to define a fan nozzle duct between the core cowl and a portion of the nacelle. The nacelle includes a stationary cowl. The thrust reverser assembly includes a first translating cowl that is slidably coupled to the nacelle. The first translating cowl is positionable with respect to the stationary cowl. A second translating cowl is slidably coupled to the nacelle such that the first translating cowl is positioned between the stationary cowl and the second translating cowl. The second translating cowl is positionable with respect to the first translating cowl. A positioning assembly is coupled to the first translating cowl. An actuator assembly is operatively coupled to the second translating cowl for selectively moving the second translating cowl. The actuator assembly is configured to engage the positioning assembly to selectively move the first translating cowl.

Description

technical field [0001] The field of the invention relates generally to aircraft gas turbine propulsion systems, and more specifically, to systems and methods for operating thrust reversers for turbofan propulsion systems. Background technique [0002] At least some known turbofan engines include a fan assembly, a core gas turbine engine enclosed in an annular core shroud, and a fan nacelle surrounding a portion of the core gas turbine engine. The fan nacelle is spaced radially on the outside with respect to the annular core shroud such that the core shroud and the fan nacelle form a fan nozzle duct with a discharge area. [0003] At least some known turbofan propulsion systems include thrust reverser assemblies. At least some known thrust reverser assemblies include a first stationary shroud, a second shroud axially translatable relative to the first shroud, and a third shroud axially translatable relative to the second shroud. More specifically, in some known thrust rever...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K1/76
CPCF02K1/72F02K1/763F02K1/766
Inventor J·T·科佩塞克P·W·沃克
Owner 伍德沃德HRT公司
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