CN-224214268-U - Thrust chamber spray pipe with multilayer gradient coating structure

CN224214268UCN 224214268 UCN224214268 UCN 224214268UCN-224214268-U

Abstract

The utility model discloses a thrust chamber spray pipe with a multilayer gradient coating structure, which comprises an air inlet, a convergence section, a throat, an expansion section, an air outlet and a multistage high-temperature-resistant protective coating, wherein the air inlet, the convergence section, the throat, the expansion section and the air outlet are sequentially arranged, the multistage high-temperature-resistant protective coating is arranged on the circumferential surface of the throat, the circumferential surface of the air inlet and the circumferential surface of the air outlet, the multistage high-temperature-resistant protective coating comprises a thermal-adaptation buffer transition layer, a thermal shock-resistant enhancement transition layer and a high-temperature-resistant protection compact surface layer, and the thermal-adaptation buffer transition layer, the thermal shock-resistant enhancement transition layer and the high-temperature-protection compact surface layer are sequentially fused on the circumferential surface of the throat, the circumferential surface of the air inlet and the circumferential surface of the air outlet. The thrust chamber spray pipe with the multilayer gradient coating structure disclosed by the utility model has the advantages that the multistage high-temperature-resistant protective coating is additionally coated on key areas such as the throat part, the air inlet, the air outlet peripheral surface and the like, the whole flow functions of heat conduction from a matrix and gradient transition to surface protection are covered, and the high-efficiency heat protection of the thrust chamber spray pipe is realized.

Inventors

YANG JIAOXI
TIAN YUJIN
GAO FENG
YANG YUXIAO

Assignees

苏州光阵铄维科技有限公司

Dates

Publication Date: 20260508
Application Date: 20250526

Claims (4)

1. A thrust chamber nozzle with a multilayer gradient coating structure is characterized by comprising: The device comprises an air inlet (1), a convergence section (2), a throat (4), an expansion section (5) and an air outlet (3), wherein the air inlet (1), the convergence section (2), the throat (4), the expansion section (5) and the air outlet (3) are sequentially arranged; the multistage high-temperature-resistant protective coating (6) is arranged on the periphery of the throat part (4), the periphery of the air inlet (1) and the periphery of the air outlet (3); The multistage high-temperature-resistant protective coating (6) comprises a thermal-adaptation buffer transition layer (61), a thermal shock-resistant reinforced transition layer (62) and a high-temperature-resistant protective compact surface layer (63), wherein the thermal-adaptation buffer transition layer (61), the thermal shock-resistant reinforced transition layer (62) and the high-temperature-resistant protective compact surface layer (63) are sequentially clad on the peripheral surface of the throat part (4), the peripheral surface of the air inlet (1) and the peripheral surface of the air outlet (3).
2. The thrust chamber nozzle with the multilayer gradient coating structure according to claim 1, further comprising a flow passage (7), wherein the flow passage (7) is arranged in the convergent section (2), the throat section (4) and the divergent section (5).
3. The thrust chamber nozzle with a multilayer gradient coating structure according to claim 2, characterized in that the flow channel (7) is provided with several branches.
4. The thrust chamber nozzle with the multilayer gradient coating structure according to claim 2, wherein the air inlet (1), the convergent section (2), the throat (4), the divergent section (5), the air outlet (3) and the flow passage (7) are integrally formed.

Description

Thrust chamber spray pipe with multilayer gradient coating structure Technical Field The utility model belongs to the technical field of thrust chamber spray pipe manufacturing, and particularly relates to a thrust chamber spray pipe with a multilayer gradient coating structure. Background The thrust chamber nozzle is used as a core component for energy conversion of a rocket engine, and the performance of the thrust chamber nozzle directly determines the thrust and reliability of the engine. The traditional manufacturing process mostly adopts stainless steel or nickel-based superalloy to be molded by casting or welding, although the requirement of basic high temperature resistance can be met, the manufacturing process still has obvious defects under extreme thermal load, namely the stainless steel material has insufficient heat conductivity, high-efficiency thermal management is difficult to realize, local thermal stress accumulation causes deformation failure, and the nickel-based alloy has high temperature resistance but high density characteristic restricts lightweight design. Meanwhile, because the traditional manufacturing technology relies on casting or welding forming, the processing capability of the technology on complex inner runners (such as multi-stage branch cooling channels) is limited, the spray pipe is often required to be split into a plurality of parts to be respectively formed and then assembled, so that the continuity of the runners is poor, the heat conduction efficiency is reduced, and a welding seam area is easy to become a heat stress concentration point. Therefore, the above problems are to be solved. Disclosure of utility model The utility model aims to overcome the defects, and the utility model aims to provide the thrust chamber spray pipe with a multilayer gradient coating structure, wherein the multistage high-temperature resistant protective coating is additionally coated on key areas such as the periphery of the throat part, the periphery of the air inlet, the periphery of the air outlet and the like, so that the full-flow functions of heat conduction from a matrix and gradient transition to surface protection are covered, and the high-efficiency heat protection of the thrust chamber spray pipe is realized. The thrust chamber spray pipe with the multilayer gradient coating structure comprises an air inlet, a convergence section, a throat, an expansion section, an air outlet and a multistage high-temperature-resistant protective coating, wherein the air inlet, the convergence section, the throat, the expansion section and the air outlet are sequentially arranged, the multistage high-temperature-resistant protective coating is arranged on the periphery of the throat, the periphery of the air inlet and the periphery of the air outlet, the multistage high-temperature-resistant protective coating comprises a thermal-fit buffer transition layer, a thermal shock-resistant enhancement transition layer and a high-temperature-protection compact surface layer, and the thermal-fit buffer transition layer, the thermal shock-resistant enhancement transition layer and the high-temperature-protection compact surface layer are sequentially clad on the periphery of the throat, the periphery of the air inlet and the periphery of the air outlet. The design of component gradient is achieved through the arrangement of the thermal adaptation buffer transition layer and the thermal shock resistance enhancement transition layer, so that the thermal expansion matching and the mechanical property optimization are realized, and the high-efficiency thermal protection of the thrust chamber spray pipe is realized through the full-flow function of covering the transition from the heat conduction of the matrix and the gradient to the surface protection through the multi-stage high-temperature resistance protection coating additionally coated on key areas such as the throat circumference, the air inlet circumference, the air outlet circumference and the like. The flow channel is arranged in the convergence section, the throat and the expansion section. The high temperature gas in the combustion chamber can generate strong heat radiation and heat conduction to the nozzle wall in the working process of the thrust chamber nozzle, and the cooling medium flowing in the flow passage can absorb the heat of the nozzle wall and take away the heat, so that the temperature of the nozzle wall is reduced. Further, the flow channel is provided with a plurality of branches. The branched design of the flow channel can divide the fluid into a plurality of small strands, and the contact area of the fluid and the surrounding environment is increased, so that more uniform heat dissipation is promoted. Further, the air inlet, the convergence section, the throat, the expansion section, the air outlet and the runner are integrally formed. The integrated design promotes the continuity of the flow channel, improves the heat conducti