Главная    Ex Libris    Книги    Журналы    Статьи    Серии    Каталог    Wanted    Загрузка    ХудЛит    Справка    Поиск по индексам    Поиск    Форум   
blank
Авторизация

       
blank
Поиск по указателям

blank
blank
blank
Красота
blank
Nix A.C. — Effects of High Intensity, Large-Scale Freestream Combustor Turbulence On Heat Transfer in Transonic Turbine Blades
Nix A.C. — Effects of High Intensity, Large-Scale Freestream Combustor Turbulence On Heat Transfer in Transonic Turbine Blades

Читать книгу
бесплатно

Скачать книгу с нашего сайта нельзя

Обсудите книгу на научном форуме



Нашли опечатку?
Выделите ее мышкой и нажмите Ctrl+Enter


Название: Effects of High Intensity, Large-Scale Freestream Combustor Turbulence On Heat Transfer in Transonic Turbine Blades

Автор: Nix A.C.

Аннотация:

The influence of freestream turbulence representative of the flow downstream of a
modern gas turbine combustor and first stage vane on turbine blade heat transfer has been
measured and analytically modeled in a linear, transonic turbine cascade. Measurements
were performed on a high turning, transonic turbine blade. The facility is capable of
heated flow with inlet total temperature of 120ºC and inlet total pressure of 10 psig. The
Reynolds number based on blade chord and exit conditions (5x106
) and the inlet and exit
Mach numbers (0.4 and 1.2, respectively) are representative of conditions in a modern
gas turbine engine. High intensity, large length-scale freestream turbulence was
generated using a passive turbulence-generating grid to simulate the turbulence generated
in modern combustors after it has passed through the first stage vane row. The grid
produced freestream turbulence with intensity of approximately 10-12% and an integral
length scale of 2 cm near the entrance of the cascade passages, which is believed to be
representative of the core flow entering a first stage gas turbine rotor blade row. Mean
heat transfer results showed an increase in heat transfer coefficient of approximately 8%
on the suction surface of the blade, with increases on the pressure surface on the order of
two times higher than on the suction surface (approximately 17%). This corresponds to
increases in blade surface temperature of 5-10%, which can significantly reduce the life
of a turbine blade. The heat transfer data were compared with correlations from
published literature with good agreement.


Язык: en

Рубрика: Физика/

Статус предметного указателя: Неизвестно

ed2k: ed2k stats

Год издания: 2003

Количество страниц: 171

Добавлена в каталог: 18.04.2013

Операции: Положить на полку | Скопировать ссылку для форума | Скопировать ID
blank
Предметный указатель
blank
Реклама
blank
blank
HR
@Mail.ru
       © Электронная библиотека попечительского совета мехмата МГУ, 2004-2019
Электронная библиотека мехмата МГУ | Valid HTML 4.01! | Valid CSS! О проекте