|Table of Contents|

Aerodynamic redesign of supersonic Curtis-stage turbine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2014年01期
Page:
65-70
Research Field:
研究与设计
Publishing date:

Info

Title:
Aerodynamic redesign of supersonic Curtis-stage turbine
Author(s):
LIN Qi-yan;  JIN Zhi-lei;  WANG Lei
Beijing Aerospace Propulsion Institute, Beijing 100076, China
Keywords:
-
PACS:
V434-34
DOI:
-
Abstract:
3D flow field analysis of the supersonic Curtis-stage turbine in a liquid rocket engine was conducted by mean of numerical simulation. On the base of analysis result, the blade profile of two-row rotor was redesigned. The blade cascade of the first row rotor was redesigned with the method of free vortex flow, which weakened the interactive effect of shock wave on boundary layer and restrained the flow separation inside the cascade with the constant flow channel design. The parameterized blade shape construction method was adopted in the redesign of the second row rotor blade cascade, which was presented by Bezier curve. The separation loss was declined by reducing the intake incidence. The results of the numerical simulation indicate that the characteristic of internal flow in the redesigned Curtis-stage turbine is improved remarkably, the separation loss is reduced obviously and the turbine efficiency is increased by more than 5%.

References:

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