ARRANGEMENT OF INJECTION SYSTEM AT END WALL OF AIRCRAFT ENGINE COMBUSTION CHAMBER

摘要

PROBLEM TO BE SOLVED: To provide an injection system arranged at the end wall of an aircraft engine combustion chamber to which such an arrangement is introduced that no geometric interference exists in a continuous region where the injection system of new generation is installed, and capable of maintaining operating performance. SOLUTION: By protruding at the side of the injection system (2), an injecting (2) part (202) and stationary (3) parts (31 and 32) extending around a hole (10) are shaped thin and long having a split straight line, and the longest dimension of the thin and long shape extends in the radial direction with respect to the combustion chamber end wall (1) having the split straight line. Sizes of the injecting (2) part and the stationary (3) parts are decreased by cutting off one part of the diameter using flat portions (2020, 310, and 320) extending in the radial direction and locating the flat portions adjoining parallel with one another, and the hole 10 with a thin and long section having a straight line of a tangent and an injecting part 203 passing a hole having a cylindrical shape are arranged having a working gap jrin the radial direction greater than the working gap jtof the tangent. COPYRIGHT: (C)2009,JPO&INPIT