DEVICE FOR FORMATION OF FUEL-AIR MIXTURE IN COMBUSTION CHAMBER OF RAMJET ENGINE Russian patent published in 2024 - IPC F02K7/10 F23R3/34 

FIELD: rocket engineering.

SUBSTANCE: invention relates to rocket engineering, namely to devices intended for formation of fuel-air mixture in combustion chamber of ramjet engine. Device for forming a fuel-air mixture in the combustion chamber of a ramjet consists of housing, front flange, rear flange with fuel feed holes, fuel feed manifolds, sector manifolds with continuous fuel feed, sector manifolds with disconnected fuel feed and straightening casing. Housing is made three-layer in form of truncated cone and consists of inner shell with fuel supply holes along its entire length, corrugated filler, outer shell, front frame and rear frame. Corrugated filler forms longitudinal channels of continuous fuel supply and longitudinal channels with disconnected fuel supply with fuel supply holes along their entire length. Cross-section area of channels of continuous fuel supply is larger than cross-section area of channels with disconnected fuel supply. Channels of continuous fuel supply are plugged by front frame, channels of continuous fuel supply and channels with disconnected fuel supply are plugged by rear frame. Inner shell and corrugated filler comprise jet nozzles to feed fuel into housing inner space. Fuel unions and sector manifolds are installed on the front flange; at that, sector manifolds are equipped with vortex nozzles, and sector manifolds with disconnected fuel supply are additionally equipped with cooling channels with jet nozzles and connectors for fuel supply to cooling channels.

EFFECT: efficient control of fuel-air mixture flow rate and provision of ramjet operation in various flight modes of aircraft at qualitative mixture formation; achieved: high manufacturability due to the possibility of making the structure by different methods; structural unification: combination of functions of fuel supply and distribution and cooling of structure; simplified design of the engine in terms of cooling; high strength in relation to low weight; efficiency; possibility of increasing flight range at different speeds of aircraft flight.

1 cl, 1 dwg