Gasturbinenbrennkammer mit einem Übergangsstück mit einer Kühlstruktur

Details

Veröffentlichungs-Nr.

EP2863018

Aktenzeichen

EP13189106

Anmeldetag

17. Oktober 2013

Veröffentlichung

21. März 2018

Erteilung

21. März 2018

Rechtsraum

EP

IPC

F01D9/02F01D25/12F23M5/08F23R3/00

Abstract

The invention refers to a transition piece (100) of a combustor of a gas turbine, comprising an impingement cooling zone (200), a sequential disposed liner (300) having at least one cooling arrangement, a closing plate (500) with respect to the sequential disposed liner, wherein the sequential disposed liner having a cooling channel structure (400), wherein the cooling channel structure (400) forms a closed or quasi-closed loop cooling scheme. The proposed cooling channel structure (400) is realized by creating openings of near wall cooling channels to the outer combustor air plenum and openings to the space inside impingement chamber. The individual cooling channels run in a serpentine manner. The closing plate (500) may comprise an annular recess cavity for collecting dust particles, which may is connected to apertures for discharging the collected dust particles from the cavity to outside.

Anmelder

Firmen

Ansaldo Energia Switzerland AG
General Electric Technology GmbH
ALSTOM Technology Ltd

Land

🇨🇭 Schweiz

Fachgebiete