Brennkammeranordnung für eine Gasturbineneinheit

Details

Veröffentlichungs-Nr.

EP4768787

Anmeldetag

30. Dezember 2024

Veröffentlichung

1. Juli 2026

Rechtsraum

EP

IPC

F23R3/28, F23R3/34

Abstract

A combustor assembly (3) for a gas turbine unit (1) comprises at least one combustor unit (7) provided with a liner (16) extending substantially along a combustor axis (B); the combustor unit (7) comprising a first-stage combustor (8) and a second-stage combustor (9), which is arranged downstream the first-stage combustor (8) along the gas flow direction (G); the first-stage combustor (8) comprising a first-stage burner (11), fed with first-stage fuel and first-stage air, and a first-stage combustion chamber (12), where the first-stage fuel is burned; wherein the second-stage combustor (9) comprises a second-stage burner (13) and a second-stage combustion chamber (14); the second-stage burner (13) being arranged downstream of the first-stage combustion chamber (12); the second-stage combustion chamber (14) being fed with hot gas leaving the first-stage combustion chamber (12) and passing through the second-stage burner (13), with dilution air and with a second-stage fuel; wherein the dilution air and the second-stage fuel are injected simultaneously within the second-stage burner (13).

Anmelder

Firma

Ansaldo Energia Switzerland AG

Land

🇨🇭 Schweiz

Fachgebiete