| 摘要 |
PURPOSE: To elongate an effective life of a wall by forming a cooling passage in a wall of a structure in a gas turbine engine or the like to prevent the structure of a high temperature, said cooling passage having predetermined cross sections towards predetermined directions in respect to a principal stress applied to the wall. CONSTITUTION: A wall 22 of blades and vanes of a turbine, a combustor liner of a gas turbine engine or the like has a cooling passage 34. A first plane 28 of a principal stress defined by a first axis, i.e., X-axis 30 and a second axis, i.e., Y-axis 32 which is in the same plane of the X-axis 30 and perpendicular to the X-axis 30, is formed between spaced and parallel first and second surfaces 24, 26 of the wall 22. Then, a diagonal passage 34 forming an acute angle A on the first plane 28 and its X-axis 30 is formed through the wall 22. The diagonal passage 34 has a first cross section 44 which is perpendicular to its axis and in the shape of an ellipse having a longitudinal axis 46 and a latitudinal axis 48, and a second cross section 50 which is circular and in parallel with the first plane 28. |
