Two stage V-gutter fuel injection mixer

In a gas turbine combustor for mixing and combusting fuel and an oxidant comprising:

• an enclosure for the introduction and mixing of the fuel and oxidant in an upstream end region thereof, and for combustion of the mixture of said fuel and oxidant in a downstream end region thereof;
• two or more rows of convex-shaped members in the upstream end of said enclosure extending transverse to the mixture flow from the upstream end to the downstream end regions;
• said convex-shaped members each including an apex connecting a pair of trailing edges;
• the apex of each of said convex-shaped members being pointed toward the upstream end of said enclosure, and said trailing edges of said convex-shaped members extending outwardly from said apex toward the downstream end of said enclosure;
• means to inject the oxidant into said upstream end region to cause an oxidant flow toward the downstream combustion end region;
• and
• means to inject said fuel into said upstream end region for mixing with said oxidant flow;
• said convex-shaped members being interposed in, and extending transverse to, the path of said mixture flow;
• a first row of said convex-shaped members located to assist in said mixing of said fuel and said oxidant, and a second row of said convex-shaped members located to assist in separating an area of mixing from said combustion end region;
• wherein a first manifold extends along the apexes of one or more of said convex-shaped members to connect a first group of openings spaced along the one or more of said convex-shaped members, a first inlet adapted to be connected to a source of gas fuel to flow through said first manifold to the first group of spaced openings and a second manifold extending adjacent said first manifold to connect a second group of openings spaced along the one or more of said convex-shaped members, and a second inlet adapted to be connected to a source of liquid fuel to flow through said second manifold to the second group of spaced openings.

In a gas turbine combustor for mixing and combusting fuel and an oxidant comprising:

• a combustor enclosure having an upstream mixing region adjacent one end region thereof, and a downstream combustion zone adjacent a remote end region thereof;
• means for introducing an oxidant under pressure to said upstream mixing region to establish an oxidant flow toward said downstream combustion zone;
• and
• means for injecting a fuel in the upstream mixing region between said oxidant introducing means and said combustion zone;
• said fuel injecting means including an upstream array of convex-shaped members and a downstream array of convex-shaped members extending substantially across said enclosure in planes transverse to said flow;
• said convex-shaped members each including an apex connecting a pair of trailing edges, with the apexes of said convex-shaped members pointing toward the upstream end of said enclosure, and with the trailing edges of said convex-shaped members extending outward from said apexes toward said combustion zone;
• the apexes of at least some of the downstream array of convex-shaped members being located behind said upstream array of convex-shaped members and pointed toward and proximate to spaces between adjacent trailing edges of adjacent convex-shaped members in said upstream array;
• said fuel injecting means further including openings spaced along one or more of said convex-shaped members in a direction transverse to said flow;
• whereby said upstream and downstream arrays of convex-shaped members are positioned to provide flow disturbance and prevent flame propagation to said mixing region from said combustion zone.

In a gas turbine combustor for mixing and combusting fuel and an oxidant comprising:

• a combustor enclosure having an upstream mixing region adjacent one end region thereof, and a downstream combustion zone adjacent a remote end region thereof;
• means for introducing an oxidant under pressure to said upstream mixing region to establish an oxidant flow toward said downstream combustion zone;
• and
• means for injecting a fuel in the upstream mixing region between said oxidant introducing means and said combustion zone;
• said fuel injecting means including an upstream array and a downstream array of convex members extending substantially across said enclosure in planes transverse to said flow;
• said convex members each including an apex connecting a pair of trailing edges, with the apexes of said convex members pointing toward the upstream end of said enclosure, and with the trailing edges of said convex members extending outward from said apexes toward said combustion zone;
• the apexes of at least some of the downstream array of convex members being pointed toward and proximate to spaces between adjacent trailing edges of adjacent convex members in said upstream array;
• said fuel injecting means further including openings spaced along one or more of said convex members in a direction transverse to said flow;
• whereby said arrays of convex members are positioned to provide flow disturbance and prevent flame propagation to said mixing region from said combustion zone;
• and
• wherein a first manifold extends along the apexes of one or more of said convex members to connect a first manifold with a first fuel inlet adapted to be connected to a source of gas fuel which flows through said first manifold to the first group of spaced openings, and a second manifold extending adjacent said first manifold to connect a second group of openings spaced along said second manifold with a second fuel inlet adapted to be connected to a source of liquid fuel.