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Numerical Investigation on the Effects of Cavity-Blowing Jet on Intermediate Turbine Duct Flowfield

  • Jun LiuEmail author
  • Qiang Du
Original Paper
  • 5 Downloads

Abstract

Intermediate turbine duct is an important part of engine, which guides the hot gas from upstream high-pressure turbine to downstream low-pressure turbine without much loss. To promise such goal, much work has been done to investigate flow mechanism in this kind of duct as well as its design criterion with numerical and experimental methods. Usually intermediate turbine duct simplified from real engine structure was adopted with upstream and downstream blades. However, cavity-blowing jet exists to disturb the duct flow field in real engine to change its performance. Naturally, the wall vortex pair would develop in different ways. In addition to that, the blowing jet flow rate changes at different engine representative operating conditions. This paper deals with the influence of cavity-blowing jet on the aerodynamic performance of an aggressive intermediate turbine duct. The objective is to reveal the physical mechanism of blowing jet ejected from the wheel-space and its effects on the duct flow field. First, ten cases with and without cavity are simulated simultaneously. On one hand, the influence of cavity structure without blowing jet on the flow field inside duct would be discussed. On the other hand, the effect of blowing jet rate on flow field could be analyzed to investigate the mechanisms at different engine operating conditions. Second, seventy other more configurations with different cavity inlet swirl angle have been discussed to study its influence on the flow mechanisms in the ducts.

Keywords

Intermediate turbine duct Cavity-blowing jet Mass flow rate Swirl angle Pressure loss 

Abbreviations

HPT

High-pressure turbine

ITD

Intermediate turbine duct

LPT

Low-pressure turbine

Ma

Mach number

SP

Static pressure

TP

Total pressure

TT

Total temperature

H

Inlet passage height of ITD

\( V_{\text{IN}} \)

Velocity at ITD inlet

\( V_{\text{Z}} \)

Axial velocity

\( V_{\text{r}} \)

Radial velocity

\( V_{\theta } \)

Circumferential velocity

\( \omega_{Z} \)

Axial vorticity

\( \omega_{r} \)

Radial vorticity

\( \omega_{\theta } \)

Circumferential vorticity

\( {\text{C}}_{\text{ps}} \)

Static pressure coefficient

\( {\text{Cpt}} \)

Total pressure coefficient

\( C\omega_{s} \)

Streamwise vorticity coefficient

\( \omega_{s} \)

Streamwise vorticity

\( \zeta \)

Relative total pressure loss

Notes

Acknowledgements

The authors would like to thank for the support from the National Natural Science Foundation of China (No. 51776200).

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Copyright information

© The Korean Society for Aeronautical & Space Sciences 2019

Authors and Affiliations

  1. 1.Key Laboratory of Light-Duty Gas-Turbine, Institute of Engineering ThermophysicsChinese Academy of SciencesBeijingChina

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