Combustion chamber with perspiration cooling
Номер патента: DE19901424A1
Опубликовано: 27-07-2000
Автор(ы): Joachim Kretschmer, Tilman Schenkel
Принадлежит: DaimlerChrysler AG
Опубликовано: 27-07-2000
Автор(ы): Joachim Kretschmer, Tilman Schenkel
Принадлежит: DaimlerChrysler AG
Реферат: A combustion chamber (2) for a rocket engine, comprising an inner wall (4) that is pervious to a cooling agent to allow transpiration cooling and a cooling agent feed device (12, 16) associated therewith. In order to form a stable film according to a simple construction mode even in the case of local fluctuations in pressure inside said pressure chamber, the cooling agent feed device is provided with a collector chamber (12) for said cooling agent with a rear side adjacent to the inner wall, whereby pressure is exerted upon the latter by the non-distributed cooling agent and the inner wall is interspersed with perforation holes (6) on the inlet side directly where the collector chamber is situated in addition to on the outlet side, whereby said holes lead to the combustion chamber. The length, diameter and thickness of the holes are calibrated according to a locally predefined throughput of coolant and a predetermined flow speed.
Combustion Chamber Structure, Particularly for a Rocket Engine
Номер патента: US20200088138A1. Автор: Marc Geyer,Andreas Goetz,Torben Birck,Olivier De Bonn. Владелец: Arianegroup Gmbh. Дата публикации: 2020-03-19.