DUAL-MODE IGNITER AND TWO-MODE METHOD OF INJECTION FOR IGNITION OF ROCKET ENGINE

• Main Authors: VERPLANK Siril, LE KRA Zhan-Lyuk
• Format: Patent
• Language: English; Russian
• Published: 22.11.2017
• Subjects: BLASTING; COMBUSTION ENGINES; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS; INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04; JET-PROPULSION PLANTS; LIGHTING; MECHANICAL ENGINEERING; WEAPONS

FIELD: engine devices and pumps.SUBSTANCE: in accordance with the invention, the igniter comprises a supply element (21) for feeding a first propellant (A), a feed element (31) for supplying a second propellant (B), a feed element (41) for supplying high-pressure fluid medium (F), a first buffer tank (22), a second buffer tank (32), a first switching device (50), a second switching device (60) and a flare-forming combusion chamber (10); an opening located downstream of the first buffer tank (22) and the second buffer tank (32) - both open into the chamber (10), the first switching device (50) and the second switching device (60) are designed so as to connect respectively the upstream opening of the first buffer tank (22) either with the feed element (21) for feeding the first propellant or with the feed element (41) for supplying the high-pressure fluid (F), and to connect the upstream opening of the second buffer tank (32) or to the feed element (31) for feeding the second propellant or with the feed element for feeding the high-pressure fluid (F).EFFECT: invention ensures launching of the rocket engine both under low pressure conditions and under high pressure conditions.10 cl, 2 dwg