Method for manufacturing a two-component blade for a gas turbine engine and blade obtained by such a method

The invention relates to a method for manufacturing a two-component blade for a gas turbine engine, which comprises consecutively obtaining a blade profile (24) made of ceramic material comprising a hole passing through the blade profile from one side to the other in the lengthwise direction in order to form a longitudinal channel (28) opening into an upper recess (26a), positioning and holding a blade profile in a mould (30) so as to form a lower recess (26b) communicating with the channel (28) of the blade profile, pouring molten metal into the blade profile so as to fill the upper and lower recesses and the channel that connects same, and cooling the metal such that the contraction of the cooled metal in the upper and lower recesses causes compressive pre-stressing of the ceramic of the blade profile. 本发明涉及种制造用于燃气轮机的双部件叶片的方法，该方法连续地包括：获得由陶瓷材料制成的叶片型面(24)，该叶片型面包括从侧沿长度方向至另侧穿过叶片型面的孔，从而形成开口进入上凹部(26a)中的纵向通道(28)；将叶片型面定位并保持在模具(30)中，从而形成与叶片型面的通道(28)连通的下凹部(26b)；将熔融金属倒入叶片型面，从而充填上凹部和下凹部以及连接上凹部和下凹部的通道；以及使金属冷却，使得上凹部和下凹部中