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Articulating slider track

a slider track and slider technology, applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of engine stall, different take-off and landing conditions, and more nois

Inactive Publication Date: 2013-08-08
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent describes an assembly and a method for adjusting the length of a fan nozzle in a vehicle. This is accomplished by using a mechanism that allows the position of the cowl member, which holds the fan nozzle, to be adjusted relative to the vehicle's support member. This results in the nozzle exit area being modified without changing its shape or size. The technical effect is an improved adjustability of the fan nozzle without affecting its shape or size.

Problems solved by technology

However, the requirements for take-off and landing conditions are different from requirements for the cruise condition.
For cruise conditions, it is desirable to have a smaller area or smaller diameter fan nozzle for increasing cruise performance and for maximizing fuel efficiency, whereas, for take-off and landing conditions, smaller diameter fan nozzles will create more noise and may cause an engine stall.
Therefore, in many conventional engines, the cruise performance and fuel efficiency are often compromised to ensure safety of the gas turbine engine at take-off and landing.
Further, known variable area nozzle mechanisms may add significant weight to the engine, which adversely affects performance.

Method used

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Examples

Experimental program
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Embodiment Construction

[0021]Exemplary embodiments disclosed herein provide thrust reverser assemblies that may be utilized to provide the desired variable area of fan exit nozzles.

[0022]FIG. 1 illustrates a schematic view of selected portion of an exemplary gas turbine engine 10 suspended from an engine pylon 12 of an associated aircraft. The gas turbine engine 10 is circumferentially disposed about an engine centerline, or axial centerline axis A. The gas turbine engine 10 includes a fan 14 and a core engine 16. An outer housing, nacelle 28 (or fan nacelle) extends circumferentially about the fan 14. A fan bypass passage 32 extends between the nacelle 28 and an inner housing, engine cowl 34, which generally surrounds a low pressure compressor, a high pressure compressor, a low pressure turbine, and a high pressure turbine (all not illustrated here for simplicity, but well known in the art).

[0023]In operation, the fan 14 draws air into the gas turbine engine 10 as a core flow, C, and into the bypass pass...

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PUM

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Abstract

A variable fan nozzle assembly includes a cowl member mounted on a slider track. The slider track may be articulated relative to a support member to slightly modify the position of the cowl member to vary the fan nozzle exit area. At least one 4-bar linkage may be utilized to allow articulation of the slider track responsive to an actuator. A method for varying a fan nozzle exit area includes mounting a first slider track in articulatable relationship with a support member; mounting a first cowl member in slidable relationship with a first slider track such that a fan nozzle is at least partially defined by a surface of the first cowl member; varying the operational position of the first cowl member by articulating the first slider track without sliding the first cowl member with respect to the first slider track to vary the fan nozzle exit area.

Description

CROSS REFERENCE TO RELATED APPLICATIONS[0001]This application claims priority and benefit of U.S. Provisional Patent Application Ser. No. 61 / 304,741 filed Feb. 15, 2010, entitled “Articulating Slider Track,” which is herein incorporated by reference in its entirety.BACKGROUND OF THE INVENTION[0002]Embodiments disclosed herein relate generally to an articulating slider track for a cowl member to provide a variable area fan nozzle for a gas turbine engine.[0003]Conventional gas turbine engines include a fan section and a core engine with the fan section having a larger outer diameter than that of the core engine. The fan section and the core engine are disposed sequentially about a longitudinal axis and are enclosed in a nacelle. An annular path of primary airflow passes through the fan section and the core engine to generate primary thrust. An annular path of duct or fan flow (bypass air), disposed radially outward of the primary airflow path, passes through the fan section and exits...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D25/28
CPCF02K1/08F02K1/09F01D25/28F02K1/763F02K1/80F02K1/10
Inventor STUART, ALAN ROYFEHRMANN, JOHN ROBERTCOX, MELANIE ZOE
Owner GENERAL ELECTRIC CO