Siemens Energy Global Gmbh & Co. Kg

Siemens Aktiengesellschaft

Patrik Jaerling

Magnus Persson

Anders Larsson

Olle Lindman

Mats Andersson

Rickard Heinefeldt

Atanu Kumar Kundu

A fuel nozzle for use in a combustion arrangement of a gas turbine includes a main body extending from a cold side to an opposite hot side and at least five air passages arranged next to each other extending from the cold side towards the hot side. A fuel distribution chamber is arranged within the main body next to the cold side, wherein the air passages cross the fuel distribution chamber separated by passage walls. To inject fuel into the air passages, fuel holes are arranged within the passage walls.

Fuel nozzle with multiple air passages

A gas turbine arrangement for dual fuel operation has a first manifold that delivers a first fuel or compressor bleed fluid and is connected to a bleed port and a first passage for ejecting fuel or fluid into a combustor space. A second manifold delivers a second fuel and is connected to a second passage for ejecting the second fuel into the combustor space. A control system, when operated with the second fuel, provides the second fuel to the second manifold and continuously opens the bleed valve to provide bleed fluid into the first manifold to replace the first fuel. The control system controls the bleed valve over time by throttling a mass flow of the bleed fluid provided to the first passage or by increasing a mass flow of the bleed fluid provided to the first passage to adapt to fuel properties of the second fuel.

Gas turbine arrangement with controlled bleed air injection into combustor, and method of operation

Growing community of inventors

Linköping, Sweden

Patrik Jaerling