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ENCLOSURE CONTAINING HOT GASES COOLED BY TRANSPIRATION, IN PARTICULAR THRUST CHAMBER OF ROCKET ENGINE AND MANUFACTURE METHOD THEREOF
ENCLOSURE CONTAINING HOT GASES COOLED BY TRANSPIRATION, IN PARTICULAR THRUST CHAMBER OF ROCKET ENGINE AND MANUFACTURE METHOD THEREOF
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机译:火箭发动机的特殊推力室中包含通过蒸发冷却的热气的外壳及其制造方法
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摘要
PURPOSE: To make continuous harmonization of cooling conditions easier by constituting the hydraulic calibration sheath that is perforated by a plurality of micro-perforations having non-uniform sizes and densities, arranging a spacer between the sheath and an outer sealing envelope, and constituting a porous wall with sintering materials of metallic beads having the size bigger than the minimum size of the micro-perforations. ;CONSTITUTION: For example, inside portion of a combustion chamber plays a role of nozzle, and has a porous wall 10 exerting the heat exchange. The porous wall 10 is made of sintering materials, and is provided with a hydraulic calibration sheath 20 on its outside face, the said sheath being made of a material that is proof to the cooling liquid. The hydraulic calibration sheath 20 is perforated by micro-perforations 21 having non-uniform sizes and/or densities, for example having higher densities around throat of the nozzle, so as to obtain wholesome optimization of consumption of the cooling liquid. An annular chamber supplying the cooling liquid is defined between the hydraulic calibration sheath 20 and the outside sealing envelope 40, and a spacer is interposed between the outside sealing envelope 40 and the hydraulic calibration sheath 20. Cross-section of the annular chamber is the maximum in its top portion and it reduces toward to the bottom of dispersion section.;COPYRIGHT: (C)1994,JPO
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