IGTC-33 A Study of Flow and Heat Transfer in a Cooling Process of a Two-Stage Gas Turbine(Session B-4 HEAT TRANSFER IN GAS TURBINE COMPONENTS)

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概要

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• A high temperature flow through a gas-turbine produces high rate of turbulent heat transfer between the fluid flow field and the turbine components. The heat transfer process through rotor disks causes stress due to thermal gradient and centrifugal force ; thus an accurate analysis for the evaluation of thermal behavior is needed. This paper presents a numerical study of thermal flow and stress analyses in a two-stage turbine in order to better understand the detailed flow and heat transfer mechanisms through the cavity and the rotating rotor disks. The numerical computations were performed to predict heat and stress fields throughout the rotating disks. The results are presented for temperature and stress distributions through the disk and the velocity fields which illustrate interaction between the cooling air flow and gas flow created by the disk rotation. The temperature distribution in the disks shows reasonable trend. The method developed in this study shows that it can be extended to more general computations for air cooling flow pattern through a rotating blade disks in a gas turbine.

• 公益社団法人日本ガスタービン学会の論文

著者

• Amano R.s.

  Department Of Mechanical Engineering The University Of Wisconsin

• Wang K.D.

  Stress Technology Inc.

関連論文

• IGTC-109 Unsteady Flow Analysis of Turbine Cascade with Rotor Oscillation(Organized Session I ADVANCED COMPUTATIONAL SIMULATION AND DESIGN)
• IGTC-33 A Study of Flow and Heat Transfer in a Cooling Process of a Two-Stage Gas Turbine(Session B-4 HEAT TRANSFER IN GAS TURBINE COMPONENTS)
• TS-30 Optimization of Airfoil Design(Session B-2: Cascade Design 2)

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