Loading patent…
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorsKhoze Kessaev, Vassili Zinoviev, Vladimir Demtchenko
Estimating the term…
The invention concerns an acoustic igniter for igniting a mixture of rocket fuels in a liquid propellant rocket engine combustion chamber comprising a cylindrical precombustion chamber (101) including a cylindrical wall (111) and first and second end walls (112, 113), a rocket fuel injection nozzle (103) emerging into the precombustion chamber (101) through the first end wall (112) via an orifice of diameter dn, a rocket fuel injector (104) arranged inside said nozzle (103) along the axis thereof, at least an outlet orifice (102) of minimum diameter df provided in the cylindrical wall (111), an acoustic resonator (105) defining a cavity opening into the precombustion chamber (101) opposite the nozzle (103), through the second end wall (113), via an orifice (151) of diameter dr. The acoustic resonator (105) is enclosed by a housing (106) which defines around the acoustic resonator (105) a closed auxiliary chamber (160) which communicates only with the precombustion chamber (101) by at least one conduit (107).
An acoustic igniter for igniting a mixture of propellents in the combustion chamber of a liquid propellent rocket engine, the igniter comprising a cylindrical precombustion chamber having a cylindrical wall and first and second end walls, a propellent injection nozzle opening out into the precombustion chamber through the first end wall via an orifice of minimum diameter dn, a fuel injector disposed inside said propellant injection nozzle on the axis thereof, at least one outlet orifice of minimum diameter df, formed through the cylindrical wall, and an acoustic resonator defining a cavity opening out into the precombustion chamber opposite the propellant injection nozzle through the second end wall via an opening of diameter dr,
Dependencies are inferred from the claim text.