Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Jonathan May

Ghenadie Bulat

Timothy Hughes

Ian Wilkinson

Timothy Dolmansley

Herman Ruijsenaars

A burner for a gas turbine, having a combustion chamber, a first injector adapted to inject a first fuel into the combustion chamber and a second injector adapted to inject a second fuel being less reactive than the first fuel into the combustion chamber, wherein the burner is adapted to premix the fuels with an air flow before the fuel enter the reaction zone of the combustion chamber such that a first fuel flow of the first fuel has a first premixing stream line and a second fuel flow of the second fuel has a second premixing stream line, wherein each of the premixing stream lines begins with the beginning of the premixing with the air flow and ends at the location where the fuel enters the reaction zone and the length of the second premixing stream line is longer than the length of the first premixing stream line.

Burner for a gas turbine and method for operating the burner

A method for the combustion of ammonia, wherein a first combustion chamber receives ammonia and hydrogen in controlled proportions, and an oxygen-containing gas. Combustion of the ammonia and hydrogen produces NHions among other combustion products. A second combustion chamber receives the combustion products from the first combustion chamber and receives further ammonia and further hydrogen in controlled proportions, wherein combustion produces nitrogen oxides among other combustion products. A third combustion chamber receives the nitrogen oxides along with further ammonia and further hydrogen in further controlled proportions along with further oxygen-containing gas, such that the nitrogen oxides are combusted into nitrogen and water.

Method and equipment for combustion of ammonia

In a method and system for the combustion of ammonia, wherein a first combustion chamber receives ammonia and hydrogen in controlled proportions, and an oxygen-containing gas such as air. Combustion of the ammonia and hydrogen produces nitrogen oxides among other combustion products. A second combustion chamber receives the nitrogen oxides along with further ammonia and hydrogen in further controlled proportions along with further oxygen-containing gas such as air. The nitrogen oxides are combusted into nitrogen and water.

A gas turbine system has a source of ammonia and a source of an oxygen-containing gas, a first combustion chamber connected to receive ammonia, a hydrogen-rich gas stream and oxygen-containing gas, a turbine connected to receive an exhaust gas stream from the first combustion chamber; and a second combustion chamber connected to receive an exhaust gas from the turbine, ammonia and a hydrogen-rich gas stream.

Gas turbine system

A combustion system for a gas turbine includes a combustion chamber having an end section and a pre-combustion section extending from the end section, a swirler device, an optional pilot burner device and a light emitting arrangement. Main fuel is injectable by the swirler device into an inner volume of the pre-combustion section. The main flame using main fuel is producible inside the inner volume. The pilot burner device is mounted to the end section of the combustion chamber such that a pilot fuel is injectable by the pilot burner device into the inner volume of the pre-combustion section, wherein a pilot flame using the pilot fuel is producible inside the inner volume for stabilizing the main flame. The light emitting arrangement emits an electromagnetic radiation into the inner volume, such that an energy input is generatable by the electromagnetic radiation for stabilizing the pilot flame and/or the main flame.

Growing community of inventors

Lincoln, United Kingdom

Jonathan May