| 摘要 |
PURPOSE: A gas turbine nozzle vane insert and methods of an installation are provided to easily dispose an insert inside a nozzle vane cavity, to form an impingement collection gap between an inner wall of the nozzle and the wall of the insert, to minimize or remove potential low cycle fatigues, and to be capable of installation. CONSTITUTION: A pair of hollow elongated insert bodies is disposed in one or more of the nozzle vane cavities of a nozzle stage of a gas turbine. Each insert body(80,82) has an outer wall portion(86) with apertures(94) for impingement-cooling of nozzle wall portions in registration with the outer wall portion. The insert bodies are separately installed on the cavity, and spreaders(100) flex the bodies toward and to engage standoffs(96) against wall portions of the nozzle. Therefore, a designed impingement gap between the outer wall portions of the insert bodies and the nozzle wall portions is achieved. The spreaders are secured to the inner wall portions(88) of the insert bodies and the bodies are secured to one another and to the nozzle vane by welding or brazing. |
