The invention discloses a
hydrogen-
oxygen fuel-rich precombustion chamber used for a full flow
staged combustion cycle engine
system, and belongs to the field of structural design of a
rocket engine. The
hydrogen-
oxygen fuel-rich precombustion chamber comprises an ignition tube 1, an
oxygen cavity 2, an oxygen
nozzle component 3, a
hydrogen nozzle component 4, a hydrogen cavity 5, a
choke plug 6 or an ignition tube (6), a connecting section 7, a body part 8, a threaded
flange 9 and a contraction section 10. In the precombustion chamber, a hydrogen-oxygen pneumatic
resonance igniter for combusting the hydrogen and oxygen is adopted, and the hydrogen and oxygen are supplied by a hydrogen ignition line and an oxygen ignition line respectively. The igniter has three mounting positions so as to form the following three ignition schemes: 1, ignition of the head; 2, ignition of the front part of the body part; and 3, ignition of the rear part of the body part. The three ignition schemes can form the hydrogen-oxygen-
hydrogen combustion mode and are favorable for mixing
combustion of propellants. The oxygen
nozzle component 3 and the hydrogen nozzle component 4 can be detached and replaced and can meet different flow requirements. The length of the whole precombustion chamber is variable and is adjusted by increasing the number of the body part 8 or increasing the dimension of the body part 8. Due to the adoption of the threaded
flange, the material is saved and the weight is lightened. The whole structural scheme of the precombustion chamber is favorable for deeply researching the ignition schemes, the hydrogen-oxygen-
hydrogen combustion mode, the influence of a
spoiler ring on
fuel gas uniformity, and other problems.