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Novel Flame Monitoring Method by Differential Pressure between Burner Swirler Inlet and Combustor Secondary Zone

IP.com Disclosure Number: IPCOM000169174D
Original Publication Date: 2008-Apr-24
Included in the Prior Art Database: 2008-Apr-24
Document File: 3 page(s) / 247K

Publishing Venue

Siemens

Related People

Juergen Carstens: CONTACT

Abstract

Flame monitoring is extremely important in gas turbine (GT) operation. Legal requirements are generally in place to ensure that the flame in the combustor is continuously monitored during the engine is in operation since there are safety concerns when any of the burners in the turbine is flamed out. Once flame-out is detected, safety procedures has to be followed, usually immediately engine trip, to avoid unburned fuel causing serious explosion hazards because of the exhaust from the GT. A typical burner and combustor arrangement of a gas turbine is shown in figure 1. A novel real time flame monitoring method by continuously monitoring the differential pressure for individual burner between burner swirler inlet and combustor secondary zone is presented. The novel idea can apply to both can and annular combustor operating on both gas and liquid fuel.

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Novel Flame Monitoring Method by Differential Pressure between Burner Swirler Inlet and Combustor Secondary Zone

Idea: Dr. Kam-Lei Lam, GB-Lincoln

Flame monitoring is extremely important in gas turbine (GT) operation. Legal requirements are generally in place to ensure that the flame in the combustor is continuously monitored during the engine is in operation since there are safety concerns when any of the burners in the turbine is flamed out. Once flame-out is detected, safety procedures has to be followed, usually immediately engine trip, to avoid unburned fuel causing serious explosion hazards because of the exhaust from the GT. A typical burner and combustor arrangement of a gas turbine is shown in figure 1.

A novel real time flame monitoring method by continuously monitoring the differential pressure for individual burner between burner swirler inlet and combustor secondary zone is presented. The novel idea can apply to both can and annular combustor operating on both gas and liquid fuel.

Air and fuel enter the combustion system through a burner swirler and a fuel injector (premix or pilot injections), respectively. Fuel and air are then mixed in the burner and yielded to the combustor where the chemical reaction process takes place in the combustor primary zone. When the reaction occurs, thermal energy in fuel is released and the air is expanded. Expanding air posts blockage effect to the air flowing through the primary zone. As a result the pressure differential between the swirler inlet and the combustor secondary zone (downstream of primary zone) in the combusting burner is substantially higher than in the non-combusting (flame off) burner.

Based on the measuring air differential pressure for each burner between swirler inlet and secondary zone in combustor (i.e. individual ith burner ( i

  P
Δ )) as shown in figure 2, this idea suggests a novel

methodology for flame monitoring. The pressure differential correlates to flame temperature and flame mode (premix or pilot). Heightening the flame temperature results i...