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Supersonic turbine nozzle blade and design method thereof

A nozzle blade, supersonic technology, applied to mechanical equipment, stators, engine components, etc., can solve problems such as flow loss and design difficulty

Active Publication Date: 2020-08-28
安徽九州云箭航天技术有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The gas flow inside the nozzle expands from a low speed to a supersonic speed through the convergence-divergence channel, which easily causes flow loss related to the supersonic flow, and the design is more difficult

Method used

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  • Supersonic turbine nozzle blade and design method thereof
  • Supersonic turbine nozzle blade and design method thereof
  • Supersonic turbine nozzle blade and design method thereof

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Embodiment Construction

[0055] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0056] Please refer to Figure 1-Figure 5 , figure 1A schematic structural view of a nozzle blade for a supersonic turbine provided in an embodiment of the present invention; figure 2 Schematic diagram of the structure of the suction surface curve provided for the embodiment of the present invention; image 3 Schematic diagram of the stru...

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Abstract

The invention discloses a supersonic turbine nozzle blade and a design method thereof. The blade profile of each nozzle blade is composed of two curves by taking a leading edge and a tail edge as division points, one of the curves of each nozzle blade is a pressure surface curve, the other one of the curves of each nozzle blade is a suction surface curve, each pressure surface curve is provided with a corresponding convex point which is a corresponding first convex point, each suction surface curve is provided with a corresponding convex point which is a corresponding second convex point, andthe first convex point on each nozzle blade and the second convex point on the adjacent nozzle blade are aligned and are located at the same position perpendicular to a streamline to form a throat part of a nozzle runner, so that a corresponding convergence channel is formed by the two adjacent nozzle blades at the upstream of the throat part, the two adjacent nozzle blades form a corresponding symmetrical expansion channel at the downstream of the throat part, and accordingly, airflow is accelerated from subsonic flow at the airflow inlet side to sonic flow and then accelerated to supersonicflow. According to the nozzle blade, a supersonic flow expansion wave system can be distributed more gently, supersonic flow loss is reduced, and meanwhile the expansion capacity of a nozzle is improved.

Description

technical field [0001] The invention relates to the technical field of cryogenic liquid rocket engine turbopumps, in particular to a nozzle blade for a supersonic turbine and a design method thereof. Background technique [0002] Large-thrust liquid rocket engines at home and abroad all use pump-pressed propellant supply systems to optimize rocket design and improve carrying capacity. [0003] As an important part of the engine system, the efficiency of the turbine affects the performance of the entire engine. According to the different engine circulation systems, the turbines for liquid rocket engines can be divided into independent turbines and front turbines. The independent turbines are used for gas generator cycle engines, and the turbine gas is directly discharged into the atmosphere after doing work. [0004] In order to improve the performance of the engine, it is necessary to reduce the gas flow of the turbine and increase the specific power. The independent turbin...

Claims

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Application Information

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IPC IPC(8): F01D9/04
CPCF01D9/041
Inventor 李旭升刘洋卢明郭军付军锋金富贵马海宁邢斌隗合成季凤来黄仕启周伟
Owner 安徽九州云箭航天技术有限公司
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