Thrust chamber
阅读：792发布：2023-06-16
专利汇可以提供Thrust chamber专利检索，专利查询，专利分析的服务。并且A rocket engine thrust chamber comprising a combustion chamber having its fuel inlet-mixing section and thrust nozzle section formed of integrally interconnecting pyrolyzed graphite filaments so oriented and extended that the fibers thereof individually interconnect the thrust nozzle throat and fuel inlet-mixing sections of the engine, and provide more effective heat conduction from the nozzle throat section to the fuel inletmixing section. Accordingly, the temperature of the nozzle throat section is significantly lowered, and the fuel reactants are preheated in improved manner. The disclosure also relates to methods of fabricating and operating such engines.，下面是Thrust chamber专利的具体信息内容。
1. In a gas generating unitary thrust chamber construction of elongate conduit form providing a reactant/gas passage bore therethrough wherein fuel and oxidizer supplies are reacted, with high heat concomitance, and which comprises in directional sequence: a mixing section wherein the reactants are blendEd; an intermediate reaction section wherein the reaction proceeds; and a nozzle section wherein the reaction is carried to completion and which includes a throat portion through which the gas products exit; the improvement comprising: a chamber wall construction formed substantially throughout of a densified pyrolyzed integration of graphite filaments layered in criss-cross spirally wound relation so arranged as to circumscribe and span said mixing-reaction-nozzle sections and to interface at their opposite ends the chamber bore in the regions of the mixing and nozzle sections thereof, whereby said filaments effectively operate to conduct heat away from the throat section of said chamber to provide an improved nozzle section cooling facility.
2. A thrust chamber according to claim 1 wherein said filaments are wound in substantially parallel paths and conduct heat from said nozzle section to said mixing section.
3. A thrust chamber according to claim 2 wherein the carbon filaments are arcuately wound and interface at their ends with substantially all the surface areas of said nozzle and mixing sections, and the paths of heat flow from said nozzle section to said mixing section are along the lengths of said filaments.
4. A thrust chamber according to claim 3 which comprises means for directing at least a portion of reactant charged to the mixing chamber along the external walls thereof, whereby heat transfer away from the nozzle section to said walls is improved and the walls of the nozzle section are cooled.
5. A thrust chamber according to claim 4 wherein the graphite filaments are wound about a pyrolyzed solid graphite core, a part of which core forms a portion of the wall of the intermediate section of the chamber.
6. A method of making a thrust chamber construction having mixing, intermediate and exit nozzle sections which comprises: covering a mandrel with graphite filaments by winding them thereon to extend substantially from one end of the mandrel to the other, removing the assembly and shaping the interior thereof to the shape of the bore of a thrust chamber, and pyrolyzing the assembly to produce a structurally stable chamber construction having heat conductive graphite filaments therein so disposed and extending between the nozzle section thereof and the mixing section to conduct heat away from the nozzle section.
7. A method according to claim 6 wherein the graphite filaments are wound in the form of a plurality of layers of filaments each substantially parallel to the next adjoining filaments; the total thicknesses of the layers of which are at least equal to the lengths of the mixing and nozzle sections.
8. A method according to claim 7 wherein graphite cloth is employed to cover the graphite filament winding assembly, and wherein upon completion of pyrolysis, the assembly is encased in a refractory shell.
9. A method of cooling the exit nozzle section of a thrust chamber which comprises conducting heat away from said nozzle section along paths of pyrolytic graphite filaments to a heat sink of lower temperature than said nozzle section, said filaments being in criss-cross spirally wound relation so arranged as to circumscribe and span said nozzle section and said heat sink and to interface at their opposite ends the nozzle section and heat sink walls, whereby said filaments effectively operate to conduct heat away from the nozzle section of the thrust chamber.
10. A method according to claim 9 wherein the heat sink comprises said mixing section of the thrust chamber.
11. A method according to claim 10 wherein the pyrolytic graphite filaments thermally interconnect the walls of the nozzle and mixing sections of the reaction chamber, and at least a portion of the wall of the mixing section is cooled by having directed onto it at least a portion of a reactant supply.
12. A method according to claim 11 wherein the thrust chamber is the site of reaction of a fuel and an oxidizer and at least part of the fuel is directed onto the mixing section of the chamber wall, and wherein the graphite filaments which conduct heat more readily longitudinally than transversely thereof are maintained out of contact with the intermediate section of the chamber.
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