| 摘要 |
Disclosed is a method and device for cooling a turboengine rotor. The turboengine rotor comprises a rotor shaft (120) and at least one blade member (110), the blade member comprising a platform (111), wherein the platform comprises a hot gas side and a coolant side, an airfoil (112) being provided on the platform hot gas side and a blade foot section being provided on the platform coolant side, wherein the blade foot section comprises a blade shank (113) and a blade root (114), wherein the blade shank extends from the platform coolant side and is interposed between the blade root and the platform coolant side, the blade root comprising root fixation features being provided on the blade root and being received by a fixation feature of the rotor shaft, wherein the rotor shaft fixation feature extends from a rotor front face and is provided on posts (123) formed on the rotor shaft, an interconnection interface being formed between the fixation features being provided on the blade root and the rotor shaft, and extending to the rotor front face and forming an interface seam on the rotor front face, further a blade shank cavity (330) being provided adjacent the platform coolant side. The method comprises guiding a first fluid flow (306) along the rotor front face and into the blade shank cavity, a second fluid flow (305) being able to enter the blade shank cavity, wherein the method further comprises choosing the source (320) of the first fluid flow such that the first fluid flow is relatively colder than the second fluid flow, and admixing the second fluid flow with the first fluid flow inside the blade shank cavity such as to form a combined shank cavity fluid flow. |
