ULTRA LOW EMISSIONS GAS TURBINE COMBUSTOR Russian patent published in 2015 - IPC F23R3/46 F23R3/14 

FIELD: machine building.

SUBSTANCE: pipe combustion chamber for gas turbine engine running with gas fuel, contains cylindrical casing with internal cavity, axle and closed axle end, cylindrical insert of combustion chamber, mixer, impact cooling hose and channelling device. The cylindrical insert of the combustion chamber is located coaxially inside the casing cavity, and is made such that in combination with the casing sets limits of the radial external channel for combustion air flow. The cylindrical insert also sets the limits of the appropriate radial internal cavities for the combustion zone and diluent zone. The diluent zone is at distance along the axle from closed ends of the casing relatively to the combustion zone, and the combustion zone is located along direction of the axle at side of the closed end of the casing. The mixer is located at closed end of the casing connected by flow with channel for combustion air, includes multiple blades to mix gas fuel to be combusted with at least part of combustion air, and output hole of the mixer to ensure the obtained mixer fuel/air supply to the combustion zone. The impact cooling hose is coaxially located in the combustion air channel between the casing and insert, has multiple holes. Holes have such dimensions and are distributed such, that direct the combustion air to radial external surface of the insert section of the combustion chamber, setting limits of the combustion zone, for impact cooling of this insert section. The channelling device is located in the combustion air channel for the combustion air channelling from the output area of the imp[act cooling hose to the input hole of the mixer. The channelling device is made with possibility to prevent flow division, and includes section of diffuser with through cross-section of the input hole and through cross-section of output hole, at that ratio of through cross-section of output hole to with through cross-section of the input hole is in range 1.3-1.5.

EFFECT: invention ensures uniform air flow, stable burning, minimises temperature deviations in the combustion products directed to turbine, and increases cooling efficiency of the combustion chamber.

21 cl, 5 dwg