SYSTEMS AND METHODS FOR HIGH VOLUMETRIC OXIDANT FLOW IN GAS TURBINE ENGINE WITH EXHAUST GAS RECIRCULATION

A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover a...

Full description

Saved in:
Bibliographic Details
Main Authors SLOBODYANSKIY, Ilya Aleksandrovich, TROUT, Jesse Edwin, VALEEV, Almaz, BORCHERT, Bradford David, SIDKO, Igor Petrovich, GINESIN, Leonid Yul'evich, SIMMONS, Scott Robert
Format Patent
LanguageEnglish
French
German
Published 13.12.2017
Subjects
AIR
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
METHODSOR APPARATUS FOR COMBUSTION USING FLUID FUELOR SOLID FUEL SUSPENDED IN
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.
Bibliography:Application Number: EP20160706097