Turbine blade platform cooling holes
Номер патента: CA3202636A1
Опубликовано: 23-06-2022
Автор(ы): Aaron J. Dick, Donald Joseph Bognatz, Estevan Daniel Negrete, Marius Dumitrascu, Nnawuihe Asonye OKPARA
Принадлежит: Solar Turbines Inc
Опубликовано: 23-06-2022
Автор(ы): Aaron J. Dick, Donald Joseph Bognatz, Estevan Daniel Negrete, Marius Dumitrascu, Nnawuihe Asonye OKPARA
Принадлежит: Solar Turbines Inc
Реферат: During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade.
Turbine blade platform cooling holes
Номер патента: EP4264015A1. Автор: Nnawuihe Asonye OKPARA,Aaron J. Dick,Donald Joseph Bognatz,Marius Dumitrascu,Estevan Daniel Negrete. Владелец: Solar Turbines Inc. Дата публикации: 2023-10-25.