Gasturbineneinheit

Details

Veröffentlichungs-Nr.

EP4768786

Anmeldetag

30. Dezember 2024

Veröffentlichung

1. Juli 2026

Rechtsraum

EP

Abstract

Gas turbine unit comprising a compressor (2), a turbine (5) a combustor assembly (3) and a fuel supply assembly (4) configured to supply at least one first-stage fuel to the combustor assembly (3); the combustor assembly (3) comprising 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), which is fed with first-stage air coming from the compressor (2) and first-stage fuel coming from the fuel supply assembly (4), and a first-stage combustion chamber (12), where the first-stage fuel is burned; the first-stage fuel being an ammonia-based fuel; 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) and with dilution air; the fuel supply assembly (4) being configured to supply the at least one first-stage fuel to the first-stage burner (11) so as the combustion stoichiometry of the first-stage burner (11) is unbalanced and an excess of first-stage fuel is present in the first stage burner (11) to obtain unburned first-stage fuel reaching the second-stage burner (13).

Anmelder

Firma

Ansaldo Energia Switzerland AG

Land

🇨🇭 Schweiz