Fuel delivery system for a turbine engine

A combustion turbine engine that includes: a compressor (26); a combustor (30) that receives fuel from a fuel line (50); a turbine (28); a heat exchange portion (52) comprising a portion of the fuel line (50) in heat transfer relationship with a heat source (71, 87, 91, 94) for heating the fuel; a r...

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Bibliographic Details
Main Authors Gallagher, Brian M, Rendo, Korey F, Hains, John V, Erickson, Dean M, Bilton, Timothy R
Format Patent
LanguageEnglish
French
German
Published 31.07.2019
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:A combustion turbine engine that includes: a compressor (26); a combustor (30) that receives fuel from a fuel line (50); a turbine (28); a heat exchange portion (52) comprising a portion of the fuel line (50) in heat transfer relationship with a heat source (71, 87, 91, 94) for heating the fuel; a rapid heating value meter (74) disposed to test the heating value of the fuel that is configured to provide heating value test results within approximately 1 minute; a cold leg bypass (76) comprising a fuel line (50) that bypasses the heat exchange portion (52), the cold leg bypass (76) being connected to the fuel line (50) at an upstream fork (62) and at a fuel mixing junction (64); and valves for controlling the fuel being directed through the heat exchange portion (52) and the fuel being direct through the cold leg bypass (76); wherein the length of fuel line (50) between the fuel mixing junction (64) and the combustor (30) is less than 20 meters.
Bibliography:Application Number: EP20100164820