Gas turbine engine fuel injectors
Number of patents in Portfolio can not be more than 2000
United States of America Patent
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-
Aug 3, 1982
Grant Date -
N/A
app pub date -
Jul 16, 1980
filing date -
Aug 1, 1979
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A gas turbine engine fuel injector has distinct and separate flow paths for liquid and gaseous fuel which each terminate in outlets of decreasing cross-sectional area in order to prevent combustion products from the flame tube or tubes of the engine from flowing back into the injector, the separate fuel flow paths preventing fuel from migrating from one path to the other. Compressor delivery air is also arranged to flow through the fuel outlets and some mixing of fuel and air takes in the outlets before the fuel enters the flame tube. The fuel injector is formed in two separate and co-operating parts, a fuel feed arm attached to the engine casing and readily removable through a relatively small access aperture in the casing and a fuel and air inlet means which is attached to the head of the flame tube and defines the fuel and air inlets into the flame tube. The fuel injector is designed to operate on a wide calorific value range of both liquid and gaseous fuels and water injection means are also incorporated to reduce NO.sub.x emissions.
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