Side-initiated augmentor for engine applications

Patent metadata

Field	Value
Publication number	US-8991189-B2
Application number	US-91477610-A
Country	US
Kind code	B2
Filing date	Oct 28, 2010
Priority date	Oct 28, 2010
Publication date	Mar 31, 2015
Grant date	Mar 31, 2015

Abstract

A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.

First claim

What is claimed is:

1. A turbofan gas turbine engine comprising:
a core engine including in serial downstream flow communication a high-pressure compressor, a combustor, and a high-pressure turbine;
a fan section upstream of a core engine;
a low-pressure turbine downstream of the core engine;
an annular bypass duct containing a bypass flowpath circumscribing the core engine; and
a gas turbine engine augmentor downstream of the low pressure turbine, the gas turbine engine a…

Assignees

• Joshi Narendra Digamber
• Rasheed Adam
• Boespflug Matthew Patrick
• Saddoughi Seyed Gholamali
• Gen Electric

Inventors

• Joshi Narendra Digamber
• Rasheed Adam
• Boespflug Matthew Patrick
• Saddoughi Seyed Gholamali

Classifications

• F02K3/10 Primary

  Mechanical Engineering · mapped topic

• F23R3/20

  Mechanical Engineering · mapped topic