| 摘要 |
PROBLEM TO BE SOLVED: To provide a combustion chamber for an aircraft turbine engine, including a spark plug, a primary hole, and a dilution hole positioned on a downstream side from the primary hole in a direction of a longitudinal shaft.SOLUTION: A combustion chamber 10 for an aircraft turbine engine is an annular shape about a longitudinal axis A, defined by an outer side wall 12, an inner side wall 14, and an annular combustion chamber end wall 13 connecting one end of the outer side wall to one end of the inner side wall. The outer side wall 12 includes a spark plug, a primary hole 100, and a dilution hole 200 positioned on a downstream side from the primary hole 100 in the longitudinal axis A which are disposed on a periphery of the outer side wall 12. So as to differ air supply to an adjacent area from air supply to the outside of the adjacent area, the primary hole 100 positioned in each adjacent area adjacent to one of a spark plugs, has a different form from a form of the primary hole 100 positioned on the outside of the adjacent area.SELECTED DRAWING: Figure 2 |
