Dual-mode plug nozzle

US20160123178A1Inactive Publication Date: 2016-05-05GENERAL ELECTRIC CO

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[0022]Reference now will be made in detail to embodiments provided, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation, not a limitation of the disclosed embodiments. The present embodiments apply to the gas turbine engine, for example aeronautical, power generation, industrial or marine, in which a combustor burns fuel and for which aircraft operation in the supersonic flight regime is intended. Embodiments herein utilize current plug nozzle technology to include the use of existing linear actuators. The embodiments provide the ability to further optimize nozzle performance over all flight conditions.

[0023]Present embodiments relate to engines for supersonic aircraft. In particular, engines intended for operation in supersonic flight require a large variability in nozzle throat area (A8), with associated dimensional units for area typically selected from a group of at least m2, in2 or ft2), nozzle exit area (A9), and area r...

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Abstract

A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a maximum diameter section. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle. An outer shroud surrounds the inner shroud and cooperates with the centerbody to define the exit area of the nozzle. Both shrouds are independently translatable to provide independent control of the nozzle throat area and the nozzle expansion ratio. Additional actuation of the inner shroud results in the throat being disposed upon a fully forward portion of the centerbody, said fully forward shroud disposition being more forward than over the maximum diameter section. The nozzle may further comprise independent translation of the centerbody with respect to the shrouds.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]This application is a national stage application under35 U.S.C. §371(c) of prior filed, co-pending PCT application serial number PCT / US2014 / 39914, filed on May 29, 2014 which claims priority to U.S. Patent Application Ser. No. 61 / 829,495, titled “Dual-Mode Plug Nozzle” and having filing date May 31, 2013, all of which is incorporated by reference herein.[0002]The US Government may have certain rights in this invention pursuant to Contract No. MDA972-01-3-0002 (DARPA) awarded by the US Department of Defense.BACKGROUND[0003]Embodiments of the present invention relates generally to nozzles for gas turbine engines and more particularly to a variable geometry nozzle which functions as a convergent nozzle, a divergent nozzle or a convergent-divergent nozzle.[0004]Variable geometry is required where exhaust systems for gas turbine engines operate over a wide range of pressure ratios (i.e. nozzle throat pressure / ambient pressure or P8 / Pamb) where...

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Application Information

Patent Timeline

05 May 2016

Publication

US20160123178A1

IPC: F01D17/14; F01D9/02

CPC: F01D17/14; F05D2240/128; F05D2220/32; F01D9/02; F02K1/08; F05D2250/41; F02K1/09; Y02T50/60

Inventors: TERSMETTE, TREVOR ANDREW; LEE, JASON ADAM