A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models

نویسنده

  • A. A. Ameri
چکیده

Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientific and Technical Information (STI) Program Office plays a key part in helping NASA maintain this important role. The NASA STI Program Office is operated by Langley Research Center, the Lead Center for NASA's scientific and technical information. The NASA STI Program Office provides access to the NASA STI Database, the largest collection of aeronautical and space science STI in the world. The Program Office is also NASA's institutional mechanism for disseminating the results of its research and development activities. These results are published by NASA in the NASA STI Report Series, which includes the following report types: • TECHNICAL PUBLICATION. Reports of completed research or a major significant phase of research that present the results of NASA programs and include extensive data or theoretical analysis. Includes compilations of significant scientific and technical data and information deemed to be of continuing reference value. NASA's counterpart of peer-reviewed formal professional papers but has less stringent limitations on manuscript length and extent of graphic presentations. • TECHNICAL MEMORANDUM. Scientific and technical findings that are preliminary or of specialized interest, e.g., quick release reports, working papers, and bibliographies that contain minimal annotation. Does not contain extensive analysis. • CONTRACTOR REPORT. Scientific and technical findings by NASA-sponsored contractors and grantees. • TECHNICAL TRANSLATION. English-language translations of foreign scientific and technical material pertinent to NASA's mission. Specialized services that complement the STI Program Office's diverse offerings include creating custom thesauri, building customized data bases, organizing and publishing research results. .. even providing videos. This report is a preprint of a paper intended for presentation at a conference. Because of changes that may be made before formal publication, this preprint is made available with the understanding that it will not be cited or reproduced without the permission of the author. ABSTRACT A computational study has been performed to predict the distribution of convective heat transfer coefficient on a simulated blade tip with cooling holes. The purpose of the examination was to assess the ability of a three-dimensional Reynolds-averaged Navier-Stokes solver to predict the rate of tip heat transfer and the distribution of cooling effectiveness. To this end, the simulation of tip clearance flow with blowing of Kim and Metzger was used. The agreement of the computed effectiveness with the data was quite good. The agreement with the heat transfer …

برای دانلود رایگان متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

ثبت نام

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

منابع مشابه

Effect of Inlet Geometry on the Turbine Blade Tip Region Heat Transfer Coefficient and Effectiveness

An experimental investigation of the local film cooling effectiveness and heat transfer coefficient downstream of a row of elongated holes in a simulated axial turbine blade tip is presented. Film cooling is needed to protect the turbine blade tip region from high heat transfer rates, especially when cooling by convection is insufficient to keep the temperature distribution of the blade within ...

متن کامل

Analysis and Multi-disciplinary Optimization of Internal Coolant Networks in Turbine Blades

This paper presents the theoretical methodology, conceptual demonstration, and validation of a fully automated computer program for the inverse design and optimization of internal convectively cooled three-dimensional axial gas turbine blades. A parametric computer model of the three-dimensional internal cooling network was developed, including the automatic generation of computational grids. A...

متن کامل

Numerical Simulation Of the Componend Angles Effects On Adiabatic Film Cooling Effectiveness

Abstract Film Cooling Adiabatic Effectiveness on a Profile of a Gas Turbine blade that Using Holes with 45 Degree Combined Angles to the Flow Direction and Radial Along the Attack Edge as well as 25 Degree Angles to the Flow Direction and Surface Area of the Attack Edge Area and 35 degrees relative to the outlet hole suefaces along stagnation line, Under a specified blowing ratios, using the Re...

متن کامل

Aero-thermal-elasticity-materials Optimization of Cooled Gas Turbine Blades: Part I

The first lecture in this two-lecture sequence provides background and general concepts. The second lecture provides practical examples. The objective of these two lectures is to provide a modular design optimization tool description that will take into account interaction of the hot gas flow-field, heat transfer in the blade material, internal coolant flow-field, stresses and deformations of t...

متن کامل

Computation of heat transfer in a linear turbine cascade

The efficiency of a turbine increases in general with an increase of the temperature of the working gas. In modern turbines this gas temperature may well exceed the melting temperature of the metal walls (Harasgama, 1995). Locally high heat transfer can lead to an excessive temperature and high thermal stresses in the walls, causing an early fatigue of the high pressure turbine components. Thus...

متن کامل

Film Cooling: a Comparative Study of Different Heater- Foilconfigurations for Liquid Crystals Experiments

A new measurement technique for the determination of the heat transfer coefficient and the film cooling effectiveness is presented. It is based on a regression of multiple transient liquid crystals experiments using an electrical heater-foil producing a nonhomogeneous surface heat flux. This is particularly interesting for film-cooled surfaces where each cooling hole in the heater-foil leads to...

متن کامل

ذخیره در منابع من


  با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید

عنوان ژورنال:

دوره   شماره 

صفحات  -

تاریخ انتشار 1999