公开(公告)号：US20160319772A1

公开(公告)日：2016-11-03

申请号：US15107700

申请日：2014-12-30

Applicant: SNECMA

Inventor： Gaëlle LE BOUAR

IPC: F02K9/58 ,  F02K9/48

CPC classification number: F02K9/58 ,  F02K9/48 ,  F02K9/563 ,  F05D2270/304 ,  F05D2270/3061

Abstract: The invention relates to the field of propulsion assemblies, and in particular to rocket engines of the “expander” type, wherein at least one propulsion chamber (40) is fed with at least a first propellant by a first pump (33) coupled to a first turbine (34) that is driven by partial expansion of said first propellant upstream from said propulsion chamber (40) after passing, downstream from the first pump (33), through a heat exchanger (23) heated by said propulsion chamber (40). A method of the invention for controlling such a propulsion assembly (10) comprises the steps of determining whether there exists a risk of instability for the propulsion assembly (10), and in response to determining that said risk of instability exists, using a branch connection (28) situated between the first turbine (34) and the propulsion chamber (40) to shed a portion of said first propellant.

Abstract translation: 本发明涉及推进组件领域，特别涉及“膨胀机”类型的火箭发动机，其中至少一个推进室（40）由第一泵（33）供给至少第一推进剂，第一泵（33） 第一涡轮机（34），其在所述推进室（40）的上游在所述第一泵（33）的下游经过由所述推进室（40）加热的热交换器（23）经过所述第一推进剂的部分膨胀之后被驱动， 。 用于控制这种推进组件（10）的本发明的方法包括以下步骤：确定是否存在用于推进组件（10）的不稳定性的风险，并且响应于确定存在所述不稳定性的风险，使用分支连接 （28）位于所述第一涡轮（34）和所述推进室（40）之间以使所述第一推进剂的一部分脱落。