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A Split Type High Temperature Covered Nozzle

A split-type, high-temperature technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve complex curved surface processing and cooling effects and mechanical strength problems

Active Publication Date: 2018-05-22
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical problem solved by the invention is: compared with the prior art, it provides a split-type high-temperature enveloped nozzle, which solves the problems of complex curved surface processing and the balance of cooling effect and mechanical strength

Method used

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  • A Split Type High Temperature Covered Nozzle
  • A Split Type High Temperature Covered Nozzle
  • A Split Type High Temperature Covered Nozzle

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Experimental program
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Embodiment Construction

[0032] Below in conjunction with accompanying drawing, the present invention is described in further detail:

[0033] figure 1 is a schematic structural view of the split-type high-temperature envelope nozzle of the present invention; Picture 1-1 It is another structural schematic diagram of the split-type high-temperature envelope nozzle of the present invention; Figure 4 It is a structural schematic diagram of the combination section of the present invention. Such as figure 1 , Picture 1-1 with Figure 4 As shown, the split-type high-temperature envelope nozzle includes: a transition section 1, an expansion section 2, and a combined section 3; wherein, the transition section 1, the expansion section 2, and the combined section 3 are connected in sequence; the combined section 3 includes a V-shaped Expansion section 12 , V-shaped contraction section 13 and cover plate 14 ; wherein, V-shaped expansion section 12 is connected with V-shaped contraction section 13 , and t...

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Abstract

The invention discloses a split type high-temperature shroud exhaust nozzle. The split type high-temperature shroud exhaust nozzle comprises an adapter section, an expansion section and a combination section, wherein the adapter section, the expansion section and the combination section are connected in sequence. The combination section comprises a V-shaped expansion segment, a V-shaped shrinkage segment and a cover plate, wherein the V-shaped expansion segment is connected with the V-shaped shrinkage segment, and the cover plate is connected to the upper end of the V-shaped shrinkage segment. The balance between the machining and cooling effect and the mechanical strength of a complex curved surface is achieved through the split type high-temperature shroud exhaust nozzle.

Description

technical field [0001] The invention relates to the technical field of aerodynamic thermal ground simulation experiments, in particular to a split-type high-temperature envelope nozzle. Background technique [0002] When the space vehicle re-enters the atmosphere, its surface will be subjected to serious aerodynamic heating and radiation heating, which requires the vehicle to be equipped with a heat protection system. The aerodynamic shape and heat-resistant materials of the heat-resistant system need to conduct aerothermal experiments on the ground to evaluate its heat-resistant performance. Some special-shaped parts of aerospace vehicles are subjected to severe aerodynamic heating during subsonic flight. The sonic heating environment, because of the complex structure and large size of the special-shaped parts, the simulation in the free jet requires a large amount of operating power of the heater, which is often limited by the extreme value of the heater power. In this cas...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/96F02K9/97
CPCF02K9/96F02K9/97
Inventor 袁国伍陈连忠付健壮张友华陈海群杨汝森
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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