초록 ▼

A fuel and air mixing apparatus for a combustor and gas turbine generator. A primary portion of the fuel is injected into the mixing air at long distances from the combustor prechamber. The primary portion of the fuel is almost completely mixed with the mixing air. A secondary portion of fuel is inj

A fuel and air mixing apparatus for a combustor and gas turbine generator. A primary portion of the fuel is injected into the mixing air at long distances from the combustor prechamber. The primary portion of the fuel is almost completely mixed with the mixing air. A secondary portion of fuel is injected into the mixing air in the boundary layer at a short distance form the combustor prechamber. This minimally mixed second portion provides some rich portions of fuel-air in the prechamber to improve stability and reduce the chances of blowout.

대표청구항 ▼

An apparatus for mixing compressed air with a fuel, the apparatus comprising: a base plate, the base plate having a centrally located fuel-air chamber; a plurality of mixing channels for mixing compressed air and fuel, each mixing channel having an entrance for introduction of compressed air into th

An apparatus for mixing compressed air with a fuel, the apparatus comprising: a base plate, the base plate having a centrally located fuel-air chamber; a plurality of mixing channels for mixing compressed air and fuel, each mixing channel having an entrance for introduction of compressed air into the mixing channel, an exit in fluid communication with the fuel-air chamber, an interior peripheral surface, a first fuel inlet, the first fuel inlet including a fuel conduit extending from the mixing channel interior peripheral surface for introduction of fuel into the mixing channel, the fuel conduit having at least one fuel injector through which the fuel is introduced into the mixing channel, each mixing channel having a hydraulic diameter (D), the distance from the first fuel inlet to the mixing channel exit defining a first distance (L), the quantity (L×number of fuel injectors per mixing channel/D) being greater than 10, the mixing channels being oriented such that a swirling motion is imparted to the compressed air and fuel such that the compressed air and fuel exits the fuel-air chamber in a vortex configuration, each mixing channel being divided into two zones, a boundary layer zone adjacent the mixing channel peripheral surface and a free stream zone; and a second fuel inlet located in each mixing channel, the second fuel inlet introducing the fuel into the mixing channel boundary zone, the second fuel inlet being positioned a second distance (l) from the mixing channel exit, the ratio of l/D being less than 3.