公开(公告)号：US10533523B2

公开(公告)日：2020-01-14

申请号：US14909894

申请日：2014-07-25

Applicant: SNECMA

Inventor： Gérard Roz ,  Lauren Nguyen Duc ,  Stéphanie Dreyer ,  Nicolas Ravier

IPC: F02K9/50 ,  F02K9/94 ,  F02K9/97

Abstract: The device comprises two heat exchangers (74, 90) suitable respectively for vaporizing first and second propellants before they are reintroduced in gaseous form into their tanks (16, 18). The heat exchangers co-operate respectively with first and second gas generators (60, 84) suitable for being fed with a mixture of propellants in order to produce combustion, the second gas generator (84) being suitable for being fed at least in part by the exhaust from the first gas generator (60).

公开(公告)号：US10082106B2

公开(公告)日：2018-09-25

申请号：US14760190

申请日：2014-01-10

Applicant: SNECMA

Inventor： Didier Vuillamy ,  Gérard Roz

IPC: F02K1/00 ,  F02K9/60 ,  F02K9/46 ,  F02K9/64 ,  F02K9/40 ,  F02K9/97

CPC classification number: F02K9/60 ,  F02K9/40 ,  F02K9/46 ,  F02K9/605 ,  F02K9/64 ,  F02K9/972 ,  F05D2260/20 ,  F05D2260/205

Abstract: The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit (6) for feeding a rocket engine (2) at least with a first liquid propellant, the feed circuit including at least one first heat exchanger (18) suitable for being connected to a cooling circuit (17) for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant, and, in addition, downstream from said first heat exchanger, a branch passing through a second heat exchanger.

公开(公告)号：US10371098B2

公开(公告)日：2019-08-06

申请号：US14909945

申请日：2014-07-25

Applicant: SNECMA

Inventor： Gérard Roz ,  David Hayoun ,  Didier Vuillamy ,  François Lassoudiere

IPC: F02K9/50 ,  F02K9/44 ,  F02K9/42 ,  F02K9/60

Abstract: The device comprises a primary heater (58) suitable for heating the propellant coming from the tank (16) prior to it being reintroduced into its tank. The primary heater uses the heat of combustion from the engine (10) and the device further comprises a secondary heater (66) having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater (58) in order to heat the propellant between its outlet from the primary heater and being reintroduced into the tank. The device also has means (62) between the feed to the primary heater (58) and the return of the propellant to the tank for putting the propellant under pressure.