Computational Analysis of Cooling Effect with Different Flow Injection Angles On Double Chamber Model

Tao Xu,Jun-Lou Li,Zheng-Lei Yu

doi:10.19026/rjaset.6.4180

Abstract

In order to explore a better cooling performance of transition piece, a numerical simulation is performed in this study. Advanced gas turbines are designed to operate at increasingly higher inlet temperatures to enhance efficiency and specific power output. This development in the operating temperature is enabled by advances in high-temperature resistant materials and by the development of effective cooling methods that lower the temperature of all surfaces that come in contact with the hot gases. Thus, there is a need for new cooling techniques or enhancing the current techniques available. The current study is a numerical simulation of film cooling in a double chamber model, which could simulate the Transition Piece’s (TP) structure and performance. The adiabatic wall temperature and flow cooling effectiveness for the coolant injection angles (seven orientations, 90°, 75°, 60°, 45°, 30°, 15° and 0o) were investigated numerically. Fluent, a commercial CFD software, is extensively used in the current study for numerical simulations.

Highlights

Transition Piece (TP), primarily consisting heavier walls, single-piece aft ends, ribs, seal arrangements, selective cooling etc., is one of the hottest parts of a combustor of gas turbine
The new transition piece features a rounded body shape that balances the heat transfer loading both internally and externally and eliminates resonant frequency concerns (Fig. 1). It has an upstream aperture for the gas flow and it is used to receive the gas flow directly from the corresponding combustion liners with a high level of enthalpy, they are conjured in a longitudinal direction so that their downstream ends comprise arched segments to form a ring-type configuration which opens toward the first stage of the gas turbine
The mechanical stresses experienced by the TP are within acceptable limits compared to other parts, high temperatures and large temperature gradients affect the structural integrity of these components, which makes it a very critical component of a combustor in structural and thermal designs

Summary

Introduction

Transition Piece (TP), primarily consisting heavier walls, single-piece aft ends, ribs, seal arrangements, selective cooling etc., is one of the hottest parts of a combustor of gas turbine. The new transition piece features a rounded body shape that balances the heat transfer loading both internally and externally and eliminates resonant frequency concerns (Fig. 1). It has an upstream aperture for the gas flow (which is cylindrical) and it is used to receive the gas flow directly from the corresponding combustion liners with a high level of enthalpy, they are conjured in a longitudinal direction so that their downstream ends comprise arched segments to form a ring-type configuration which opens toward the first stage of the gas turbine (stator). Film cooling is a traditional method of cooling the inner surface of a TP (Xu et al, 2012)

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Conclusion