35 results about "Rocket-based combined cycle" patented technology

The invention discloses a rocket based combined cycle (RBCC) combustion chamber adopting a slope-type rocket layout mode, and a design method of the RBCC combustion chamber. The combustion chamber issequentially provided with an isolation section, a rocket slope mounting section and an expansion section from an air inlet to an outlet of gas generated by combustion. The isolation section, the rocket slope mounting section and the expansion section are sequentially arranged from the air inlet to the outlet of the gas generated by combustion. A rocket thrust chamber is mounted at the rocket slope mounting section, so that a rocket jet flow is in three-side contact with a stamping main flow and is located in front of a front peak of a fire flame of the expansion section, ignition and flame stability of the combustion chamber are achieved through the rocket jet flow, and the problem that through a step rocket layout mode, rocket high-temperature and high-enthalpy activity jet flow ignitionand flame stability cannot be effectively utilized is avoided.

The invention discloses a variable-gettering control air inlet passage for a rocket based combined cycle engine. The variable-gettering control air inlet passage comprises a precursor precompression section, an inner compression section and an air inlet passage profile of an isolation section, wherein an area-adjustable gettering region is arranged on the upper surface of the inner compression section of the air inlet passage. Under the constraint that the engine totally gives the air inlet passage profile, according to the structural scheme of variable-gettering control provided by a non-viscous air inlet passage theory, in the premise without adding a complex device, the start mach number of the air inlet passage is lowered. Before the rocket based combined cycle engine a shifted to a ramjet mode, an inner contraction section of the air inlet passage as the gettering region is totally opened. After the rocket based combined cycle engine a shifted to the ramjet mode, the inner contraction section of the air inlet passage as the gettering region is gradually closed. According to the structure of the variable-gettering control air inlet passage, the flow coefficient and other performance parameters under an ejecting mode and the ramjet mode are increased; the working range of the air inlet passage for rocket based combined cycle is widened; meanwhile, the air inlet passage still has a good performance under the supersonic mode.

The invention discloses structural design of an inlet isolation segment of a rocket-based-combined-cycle engine. Under the restraint that the minimal section of the inlet isolation segment is located in a throat segment, the sectional area of an effective circulation area of the isolation segment is improved, so that the sectional area of the inlet throat segment is increased to be equal to the sectional area of an intake of a combustion chamber, effective circulation area equal-sectional-area circulation is achieved on an inlet rocket supporting plate segment, and an equal straight segment behind the inlet rocket supporting plate segment is improved into a contraction segment so as to be matched with the section of the intake of the combustion chamber. It is ensured that the minimal section area of the inlet isolation segment is located in the throat segment. By means of the inlet isolation segment, the start mach number of an inlet is lowered, and the flow coefficients of the inlet in an injection mode and a ramjet mode and other performance parameters are increased. The design of the inlet isolation segment of the rocket-based-combined-cycle engine is high in development performance, the inlet isolation segment is designed according to different sectional sizes of the intake of the combustion chamber, the work range of the inlet can be effectively expanded, and the overall performance of the engine can be improved.

The invention discloses a variable-structure exhaust nozzle of a rocket based combined cycle engine. An inner flow field of the exhaust nozzle is in an overexpansion state under an injection modality, the inner flow field of the exhaust nozzle is in an under-expansion state under an under-combustion / super-combustion state, an upper cover plate is driven by a motor, and suction slotted holes in a rear body of an aircraft is made to be in an opened or closed state. The suction slotted holes in the upper wall face of the a spray pipe are opened when the engine works at a non-design point, the suction slotted holes in the wall face of the spray pipe are closed when the engine works at a design point, the work performance of the spray pipe under the injection modality is improved, and meanwhile it is guaranteed that the work performance of the spray pipe under the under-combustion / super-combustion modality is not reduced. The variable-structure exhaust nozzle is strong in expandability, and the suction slotted holes with different section areas can be designed according to the actual geometric structures, the work envelope curve and the work performance needs of the exhaust nozzle. The suction slotted holes are distributed according to the actual structural size of the exhaust nozzle, and the work performance of the exhaust nozzle under the non-design point is improved.

The invention provides a supersonic blending reinforcing structure with an adjustable frequency characteristic and a rocket based combined cycle. The supersonic blending reinforcing structure comprises a supersonic incoming flow baffle, supersonic incoming flow channels are arranged on both sides of the supersonic incoming flow baffle, and the two supersonic incoming flow channels are in communication with each other at the tail end of the supersonic incoming flow baffle and form a supersonic incoming flow blending zone. The supersonic incoming flow blending zone communicates with the supersonic incoming flow channels through flow guiding pipes, the flow guiding pipes comprise expansion cavities formed in the supersonic incoming flow baffle, and expansion pipes with adjustable volume are arranged in the expansion cavities. Due to a pressure difference between the two ends of the flow guiding pipes, jet flow can be formed in the supersonic incoming flow blending zone without providing an additional air source, and blending reinforcing control of the supersonic incoming flow blending zone is realized; and meanwhile, the expansion pipes are arranged in the flow guiding pipes, the jetflow ejected by flow guiding rear pipes has a certain frequency characteristic, and moreover, the volumes of the expansion pipes are adjustable, so that the frequency of the jet flow ejected by the flow guiding rear pipes is adjustable. The supersonic blending reinforcing structure with the adjustable frequency characteristic and the rocket based combined cycle are applied to the field of supersonic incoming flow blending control.

The invention discloses a motive sealing structure of a variable-geometry combustor of a rocket based combined cycle engine. The mode that contact type sealing and non-contact type sealing are combined is adopted, so that rotary motive sealing of the joint of hinges and transverse motive sealing of all top plates and side plates of the combustor are achieved. A sealing groove is formed in the end face of a connection flange between the fixed section and the variable section of the combustor. Sealing grooves are formed in the two side edges of a bottom plate of an inner cavity of the combustor. The top plates of the inner cavity of the variable section of the combustor are connected with arc grooves to form mechanical sealing. Graphite bars in longitudinal grooves and a rotation shaft are sealed through packing. The top plates of the variable section of the combustor are provided with labyrinth channels. The top plates and the side plates are in transverse motive sealing. Red copper bars in the horizontal grooves formed in the side faces of the top plates and the side plates are sealed through packing. The red copper bars of every two top plates are attached to the joints of the top plates to achieve mechanical sealing. The sealing structure can meet the sealing requirement of the engine and also has the advantages of being simple in structure, convenient to machine, and easy to implement.

The invention discloses a variable structure combustion chamber of a rocket-based-combined-cycle engine. The variable structure combustion chamber is composed of a drive system, a back pressure cavity and a combustion chamber body. The drive system is located at the upper portion of the back pressure cavity. The back pressure cavity is fixed to the portion above variable sections of the combustion chamber body and forms an integral structure with the combustion chamber body. A combustion chamber fixed section is sequentially connected with variable sections of the combustion chamber body. The variable sections are connected through cooperation of ball head hinge convex faces and ball head hinge concave faces. Two sets of hydraulic drive mechanisms drive the first variable section and the third variable section of the combustion chamber body through drive rods and connecting rods. Axial sealing grooves of the variable sections are filled with graphite strips so as to isolate high-temperature fuel gas in the combustion chamber body, and sealing is guaranteed. According to the variable structure combustion chamber, stable transition among different modes is achieved through grade adjustment. In the injection mode and the subsonic combustion mode, the variable sections of the combustion chamber body are adjusted by a hydraulic drive mechanism to generate different divergence angles and throat heights, so that the combustion chamber body is in the optimal work state, and the thrusting force and specific impulse performance of the combustion chamber body are obviously improved.

The invention discloses a rocket-based combined cycle ejector mode performance test engine. A main rocket combustor is fixed in the front of a secondary combustor; intake ducts are mounted above and below the main rocket combustor respectively; intake ends of the intake ducts are fixed in the rear of the main rocket combustor through support lugs; the rear ends of the intake ducts are connected with the secondary combustor through an intake duct flange and a second combustor flange; the secondary combustor is in a divergent straight structure; the main rocket combustor is fitly connected with the secondary combustor; a flue of a nozzle divergent segment gradually changes from round to square. The main rocket combustor is charged through the combination of seven-pointed star shape and inner holes by close-to-wall pouring; after ignition, the flow of gas in a main rocket is kept basically unchanged; variation pattern of the rocket-based combined cycle ejector mode performance along with flight Mach number and height is verified; the basis is provided for passage design. The rocket-based combined cycle ejector mode performance test engine is simple in structure and convenient to maintain, and the influence of gas composition upon engine performance and trajectory climb can be extensively researched.