STAGED FUEL AND AIR INJECTION IN COMBUSTION SYSTEMS OF GAS TURBINES

A gas turbine 12 that includes: a combustor 13 coupled to a turbine that define a working fluid flowpath 37; a compressor discharge cavity; a staged injection system that includes the forward injector 21 and a staged injector 51; a stator blade positioned extending across the working fluid flowpath...

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Bibliographic Details
Main Authors BERRY, Jonathan Dwight, HUGHES, Michael John
Format Patent
LanguageEnglish
French
German
Published 27.01.2021
Subjects
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
ENGINE PLANTS IN GENERAL
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Summary:A gas turbine 12 that includes: a combustor 13 coupled to a turbine that define a working fluid flowpath 37; a compressor discharge cavity; a staged injection system that includes the forward injector 21 and a staged injector 51; a stator blade positioned extending across the working fluid flowpath between an inboard sidewall and an outboard sidewall. A one-way continuous coolant flowpath that includes: an intake section that comprises an upstream port connected to the compressor discharge cavity and a downstream port formed through one of the inboard and outboard sidewalls; an outtake section that comprises a downstream port connected to the staged injector and an upstream port formed through the same one of the inboard and outboard sidewalls; and a cooling circuit extending through an interior of the airfoil of the stator blade and connecting to the downstream port of the intake section and the upstream port of the outtake section.
Bibliography:Application Number: EP20160203418