Parallel-jets combustion chamber of a turbine engine

Parallel-jets combustion chamber of a turbine engine having a casing, wherein in a front part of the turbine engine, a compressor is disposed on a main shaft and in a rear part of the turbine engine, a turbine is disposed on the main shaft,

• wherein the combustion chamber with a lower wall is disposed within a casing and comprises a primary zone with an air inlet and an outer flame tube and an inner flame tube, both of which are provided with air inlet openings for air inlet,
• wherein the lower wall has a thermally exposed end part adjacent the air inlet openings,
• wherein into the chamber, oil supply is provided by a radial oil spray ring arranged on the shaft with inlet openings for spraying fuel into the combustion chamber,
• wherein the outer flame tube has conical shape and is continued at a front side by a front wall, which is perpendicular to an axial direction, wherein between a front end of the outer flame tube and an outer end of an end wall, a set of cooling air openings for air is arranged in the axial direction,
• wherein between an inner end of the front wall and the oil spray ring, an axial slot is provided for the supply of air,
• wherein the thermally exposed end part of the lower wall of the combustion chamber is connected to an end portion of the inner flame tube,
• wherein in radial direction, an annulus is formed at the end portion and below the annulus a series of inlet tube openings for the air is arranged,
• wherein the end portion extends over the thermally exposed end part,
• wherein a front end of the end portion of the inner flame tube is provided with an edge and between the edge and the oil spray ring, a gap is provided,
• wherein sets of the air inlet openings around the circumference of the outer flame tube in a radial direction, series of inlet tube openings, the annulus, the gap and the axial slot are formed to generate a stabilization vortex of toroidal shape in the primary zone,
• wherein air which is passing through the series of inlet tube openings strikes the thermally exposed end part of the lower wall of the combustion chamber, which is connected to the end portion of the inner flame tube, thereby locally producing an increase in the heat transfer coefficient on the bottom surface of the thermally exposed end part.