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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Применить Всего найдено 2. Отображено 2.
29-05-2013 дата публикации

Method of monitoring kinematic link clearance in a turbomachine

Номер: GB0002496984A
Автор: POTEL NICOLAS [FR], BELGHAGI HICHEM [FR], POTEL NICOLAS, BELGHAGI HICHEM, NICOLAS POTEL, HICHEM BELGHAGI
Принадлежит:

A method for monitoring the clearance of a kinematic link 12 between a control member, such as a linear actuating cylinder 11, and receiving members of a turbomachine, such as variable stator vanes 5 of a gas turbine engine compressor, and based on an operating parameter of the turbomachine. The method comprises: displacing the control member in a direction as far as a first position, for which the receiving members are rotated so as to take up the clearance of the kinematic link; displacing the control member in the direction opposing the previous direction, as far as a second position, when a variation of the selected operating parameter is observed; ascertaining the travel of the control member between the two positions corresponding to the total clearance of the kinematic link; and comparing the ascertained value of travel with a predetermined limit value, and, if the ascertained value of the travel of the control member is greater than the limit value, carrying out monitoring of the ...

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Номер записи: 1
16-10-2013 дата публикации

Fuel circuit of an aeronautical turbine engine having a fuel pressure regulating valve

Номер: GB0002501198A
Автор: POTEL NICOLAS [FR], GAMEIRO SEBASTIEN [FR], POTEL NICOLAS, GAMEIRO SEBASTIEN, NICOLAS POTEL, SEBASTIEN GAMEIRO
Принадлежит:

The invention relates to a fuel circuit (10) of an aeronautical turbine engine, comprising a main fuel line (12) intended to supply fuel to a combustion chamber (24) of the turbine engine and including a positive-displacement pump (20), an auxiliary fuel line (30) connected to the main fuel line at a joint (32) located downstream of the pump and intended to supply fuel to hydraulic actuators (34) for controlling variable geometry devices of the turbine engine, the auxiliary fuel line including electro-hydraulic servo valves (36) upstream of each cylinder, and a fuel pressure regulating valve (40) arranged on the main fuel line downstream of the pump.

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Номер записи: 2