Patent ID: 8205453

Claim:
A method of assembling a first part and a second part in a subassembly of a gas turbine, the first and second parts being assembled together end to end via respective substantially annular edge portions, the first and second parts being made of respective materials having different coefficients of thermal expansion, the first part being made of the material having the greater coefficient of thermal expansion and presenting capacity for elastic deformation, the method comprising the following steps: conferring a thickness to an edge portion of the first part that is smaller than the thickness of the remainder of the first part; forming a succession of flexible tongues in the smaller-thickness edge portion of the first part, the tongues being separated from one another by slots obtained directly by cutting or machining; engaging the edge portions of the first and second parts one in the other over a distance that is not less than a total length of the slots; and assembling the first and second parts together by means of fastener elements, each connecting a tongue of the edge portion of the first part to the edge portion of the second part; the edge portions of the first and second parts being engaged one in the other in such a manner that the edge portions are substantially in mutual contact at the high temperatures normally encountered in operation of the gas turbine.