Burner for gas turbine

F - Mech Eng,Light,Heat,Weapons – 23 – C

Patent

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Details

F23C 7/00 (2006.01) F23D 11/24 (2006.01) F23D 11/38 (2006.01) F23R 3/34 (2006.01)

Patent

CA 2584270

Disclosed is a premix burner, e.g. for a gas turbine, comprising a vortex generator (1), a cylindrical mixing section (2) that is located downstream thereof in the direction of flow, and a high-pressure spray nozzle (10) which is provided with one or several fuel supply ducts. The high-pressure spray nozzle (10) is equipped with at least two discharge ducts through which liquid fuel penetrates into the vortex generator (1). The ducts are disposed in a decentralized manner relative to the longitudinal axis of the nozzle while being configured such that the spray cone (11) of the fuel is oriented at an angle (~) relative to the longitudinal axis of the vortex generator (1) which is smaller than the cone half-angle (a) of the vortex generator (1). The discharge ports are provided especially with an inner geometry that encompasses a conical constriction.

L'invention concerne un brûleur à prémélange, par exemple pour une turbine à gaz, pourvu d'un générateur de tourbillons (1) conique et d'une section de mélange (2) cylindrique située en aval de celui-ci dans le sens d'écoulement, ce brûleur présentant une buse de pulvérisation haute pression (10) comprenant un ou plusieurs canaux d'amenée du combustible. Cette buse de pulvérisation haute pression (10) présente au moins deux canaux de sortie par lesquels le combustible liquide pénètre dans le générateur de tourbillons (1), ces canaux étant disposés de façon décentrée par rapport à l'axe longitudinal de la buse et étant conçus de telle sorte que le cône de projection (11) du combustible soit orienté selon un angle (.beta.) par rapport à l'axe longitudinal du générateur de tourbillons (1) inférieur au demi-angle (.alpha.) du cône du générateur de tourbillons (1). La géométrie intérieure des canaux de sortie présente en particulier un rétrécissement conique.

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