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Gas turbine engine with fan variable area nozzle for low fan pressure ratio

A gas turbine and engine technology, applied in the direction of machines/engines, jet propulsion devices, etc., can solve the problems of increased overall weight

Inactive Publication Date: 2014-08-27
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing fan variable area nozzles typically employ relatively complex mechanisms that increase overall engine weight to the extent that the resulting increase in fuel efficiency may be offset

Method used

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  • Gas turbine engine with fan variable area nozzle for low fan pressure ratio
  • Gas turbine engine with fan variable area nozzle for low fan pressure ratio
  • Gas turbine engine with fan variable area nozzle for low fan pressure ratio

Examples

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Embodiment Construction

[0032] Figure 1A A general partial fragmentary schematic diagram of a gas turbofan engine 10 is shown suspended from an engine pylon P within an engine nacelle assembly N typical for an aircraft designed for subsonic operation of.

[0033] Turbofan engine 10 includes a core engine within a core nacelle 12 housing a lower rotor 14 and an upper rotor 24 . Lower rotor 14 includes a low pressure compressor 16 and a low pressure turbine 18 . The lower rotor 14 drives the fan section 20 through a gear train 22 . High rotor 24 includes a high pressure compressor 26 and a high pressure turbine 28 . A combustor 30 is arranged between the high pressure compressor 26 and the high pressure turbine 28 . The lower and upper rotors 14, 24 rotate about the axis A of rotation of the engine.

[0034] Engine 10 is preferably a high bypass geared aircraft engine. In one disclosed, non-limiting embodiment, the engine 10 has a bypass ratio greater than about six (6), with an example embodimen...

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PUM

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Abstract

A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a fan pressure ratio of the fan bypass airflow during engine operation, the fan pressure ratio less than about 1.45. In a further embodiment of any of the foregoing nacelle assembly for a gas turbine engine embodiment, the assembly further includes a controller operable to control the fan variable area nozzle.

Description

[0001] Cross References to Related Applications [0002] This application claims priority to US Application No. 13 / 340,771, filed December 30, 2011, which is a continuation-in-part of US Application No. 13 / 314,365, filed December 8, 2011. [0003] Invention background. the technical field [0004] The present invention relates to gas turbine engines, and more particularly to turbofan engines having a variable area fan nozzle (VAFN) that moves axially to vary its bypass flow path area. Background technique [0005] Conventional gas turbine engines typically include a fan section and a core engine, the fan section having a larger diameter than the core engine. The fan section and core motor are disposed about the longitudinal axis and enclosed within the nacelle assembly. [0006] Combustion gases are discharged from the core engine through core exhaust nozzles while an annular fan flow disposed radially outwardly of the main airflow path is discharged through annular fan e...

Claims

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Application Information

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IPC IPC(8): F02K1/06
CPCF02K3/06F02K3/075F02K1/06
Inventor G.A.科伦伯格S.P.扎莫拉F.M.施瓦斯
Owner UNITED TECH CORP
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