Transition duct for a gas turbine

A late lean injection system transition piece (12) includes a flowsleeve interface (38) extending circumferentially around a transition interior (18). Also included is an impingement sleeve mounting surface (52) extending circumferentially around the transition interior (18). Further included is a p...

Full description

Saved in:
Bibliographic Details
Main Authors STOIA, LUCAS JOHN, MELTON, PATRICK BENEDICT
Format Patent
LanguageEnglish
French
German
Published 10.07.2013
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION APPARATUS
COMBUSTION ENGINES
COMBUSTION PROCESSES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A late lean injection system transition piece (12) includes a flowsleeve interface (38) extending circumferentially around a transition interior (18). Also included is an impingement sleeve mounting surface (52) extending circumferentially around the transition interior (18). Further included is a plurality of fuel injectors (60) integrated substantially within the transition piece (12) and disposed between the flowsleeve interface (38) and the impingement sleeve mounting surface (52). Yet further included is an inner surface (25) extending circumferentially around the transition interior (18), wherein the inner surface (25) is spaced radially inward of the flowsleeve interface (38) and the impingement sleeve mounting surface (52).
Bibliography:Application Number: EP20130150559