초록 ▼

A gas-fuelled burner, especially for gas turbines powered by low calorific value fuel, is provided with restrictors to slow the incoming fuel from inlets to a similar mass mean velocity as the air provided through inlets, thereby reducing turbulence and improving combustion. The restrictors and outl

A gas-fuelled burner, especially for gas turbines powered by low calorific value fuel, is provided with restrictors to slow the incoming fuel from inlets to a similar mass mean velocity as the air provided through inlets, thereby reducing turbulence and improving combustion. The restrictors and outlet passages carrying the fuel to the combustion pre-chamber are located in vanes of a radial inlet swirler so as to alternate with the air inlets. The geometry is such that the respective flows emerge tangentially to a notional circle centered on the combustion pre-chamber of the turbine. The circle is preferably between 0.7 and 1.0 times the diameter of the actual pre-chamber. The ratio of the area of the restrictor to that of the outlet passage may lie between 1:1.1 and 1:1.7, preferably 1:1.4.

대표청구항 ▼

1. A gas turbine engine combustion system, comprising: a radial inflow swirler for mixing gaseous fuel and air, a combustion pre-chamber and a combustion main chamber, the swirler, the pre-chamber and the main chamber having a common longitudinal axis and being arranged in a flow sequence, the swirl

1. A gas turbine engine combustion system, comprising: a radial inflow swirler for mixing gaseous fuel and air, a combustion pre-chamber and a combustion main chamber, the swirler, the pre-chamber and the main chamber having a common longitudinal axis and being arranged in a flow sequence, the swirler comprising air and gas fuel passages angularly arrayed around the pre-chamber, the passages being oriented tangentially to a notional circle centered on the common longitudinal axis, thereby in operation to impart a common swirling motion to streams of fuel and air as they enter the pre-chamber from the passages, each gas fuel passage having an exit situated immediately downstream of an exit of an air supply passage with respect to a direction of swirl and being sized relative to the air supply passage such that at least at a predetermined power condition of the gas turbine engine, a mass mean velocity of the fuel and air streams at said notional circle are closely matched to each other. 2. The combustion system according to claim 1, wherein each gas fuel passage comprises means for restricting the flow of fuel. 3. The combustion system according to claim 2, wherein the restricting means comprises a reduced cross-section portion of the gas fuel passage. 4. The combustion system according to claim 3, wherein the reduced cross-section portion is located at an entrance to the gas fuel passage. 5. The combustion system according to claim 2, wherein a ratio of an area of the restricting means to a remainder of the passage is from 1:1.1 to 1:1.7. 6. The combustion system according to claim 5, wherein the ratio of the area of the restricting means to the remainder of the passage is 1:1.4. 7. The combustion system according to claim 2, wherein the restricting means comprises smoothing means extending across the passage to smooth the flow of the gas passing therealong. 8. The combustion system according to claim 7, wherein the smoothing means comprises a plate having a plurality of apertures therethrough. 9. The combustion system according to claim 8, wherein the plate has an array of circular holes therethrough. 10. The combustion system according to claim 9, wherein the plate has twelve holes therethrough. 11. The combustion system according to claim 1, wherein the notional circle has a diameter which lies between 0.7 and 1.0 times a diameter of the combustion pre-chamber. 12. The combustion system according to claim 1, wherein the fuel is a fuel gas of low calorific value. 13. A fuel/air mixing system for incorporation in a burner of a gas-fueled engine, the mixing system comprising: fuel passageways and air passageways for introducing fuel and air to a combustion chamber from a radially outer position to a radially inner position relative to an axis concentric with the combustion chamber, each fuel passageway having an exit situated immediately downstream of an exit of an air passageway with respect to a direction of swirl of the fuel and air in the combustion chamber, said passageways having radially inner ends which are substantially tangential to a notional circle centered on the same axis as said chamber, the fuel passageways being sized relative to the air passageways such that at least at a predetermined power condition of the engine, a mass mean velocity of the fuel and air at said notional circle are closely matched to each other. 14. The fuel/air mixing system according to claim 13, the fuel and air passageways alternate circumferentially around said axis. 15. The fuel/air mixing system according to claim 13, and further comprising a radial inflow swirler, wherein the fuel and air passageways are disposed at inclined angles relative to radii of said swirler. 16. The fuel/air mixing system according to claim 13, wherein the fuel is a fuel gas of low calorific value.