FUEL SUPPLY SYSTEM FOR A COMBUSTOR

A gas turbine combustion system (400, 500) includes a combustor (18) having at least two injection stages (402, 414, 416, 418, 420, 502), each injection stage configured to inject fuel into a combustion chamber of the combustor (18). A fuel supply circuit (404, 504) is in fluid communication with th...

Full description

Saved in:
Bibliographic Details
Main Authors MIRANDA CARLOS, HUGHES MICHAEL JOHN
Format Patent
LanguageChinese
English
Published 19.09.2023
Subjects
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A gas turbine combustion system (400, 500) includes a combustor (18) having at least two injection stages (402, 414, 416, 418, 420, 502), each injection stage configured to inject fuel into a combustion chamber of the combustor (18). A fuel supply circuit (404, 504) is in fluid communication with the at least two injection stages (402, 414, 416, 418, 420, 502) for providing the fuel from a fuel supply (406, 506, 507) to the injection stages. The fuel supply circuit includes at least two branches (524, 526, 528), each branch fluidly coupled to a respective injection stage (402, 414, 416, 418, 420, 502). The gas turbine combustion system (400, 500) also includes at least one heat exchanger (410, 515, 517) fluidly coupled to the hot fluid supply (412). A respective heat exchanger (410, 515, 517) is disposed in thermal communication on at least one of the at least two branches for modifying the temperature of the fuel within the respective branch. 本发明公开了一种气体涡轮燃烧系统(400,500)，该气体涡轮燃烧系统包括具有至少两个喷射级(402,414,416,418,420
Bibliography:Application Number: CN202310218080