Patent ID: 8499564
Filing Date: 2013-08-06
Classification: F23C,F23D,F23R

Abstract:
1. A pilot burner for a gas turbine engine comprising: an annular inner casing disposed within an annular outer casing, the inner casing defining an inner mixing passageway, and a space between the inner casing and outer casing defining an annular outer mixing passageway; an inlet to the outer casing in fluid communication with a compressed air source for admitting an outer fluid oxidant flow into the outer mixing passageway; a fluid-restricting inlet port in fluid communication with the compressed air source for admitting a restricted inner fluid oxidant flow into the inner mixing passageway, the fluid-restricting inlet port effective to limit the inner fluid oxidant flow to have an axial velocity through the inner mixing passageway that is less than an axial velocity of the outer fluid oxidant flow through the outer mixing passageway; a swirler element disposed in the outer mixing passageway effective to impart an annular swirl velocity to the outer fluid oxidant flow; an inner fuel outlet delivering an inner fuel flow into the inner fluid oxidant flow within the inner mixing passageway to provide a non-swirling inner fuel/oxidant mixture flow at an outlet end of the inner casing; an outer fuel outlet delivering an outer fuel flow into the outer fluid oxidant flow within the outer mixing passageway to provide a swirling outer fuel/oxidant mixture flow surrounding and concentric with the inner fuel/oxidant mixture flow at the outlet end of the inner casing; the outer casing extending in a downstream direction beyond the outlet end of the inner casing to define a straight section mixing zone, the straight section mixing zone receiving the concentric flows and effective to allow the swirling outer fuel/oxidant mixture flow to impart a degree of angular momentum to the inner fluid fuel/oxidant mixture flow as the concentric flows progress axially toward an open end of the straight section mixing zone; and a cone disposed at the open end of the straight section mixing zone for receiving and radially expanding the concentric flows; wherein the angular swirl velocity of the outer fuel/oxidant mixture flow cooperates with the cone to expand the concentric flows radially against the cone and to reduce an axial velocity of the inner fuel/oxidant mixture flow as it flows through the cone sufficiently to enable the concentric flows to burn without recirculation flow and without attachment to any structure of the pilot burner.