Studies on Transonic Turbines with Film Cooled Blades PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Studies on Transonic Turbines with Film Cooled Blades PDF full book. Access full book title Studies on Transonic Turbines with Film Cooled Blades by H. O. Demuren. Download full books in PDF and EPUB format.
Author: H. O. Demuren Publisher: ISBN: Category : Languages : en Pages : 139
Book Description
The goal of these studies has been to gather the necessary heat transfer data and develop the design procedure for high performance, film cooled, highly loaded transonic turbine stages. In the pursuit of this goal, three key tasks were accomplished: the measurement of heat transfer rates and film effectiveness in the low supersonic range, a study of the flow at the trailing edge of transonic turbine blades and the heat transfer at this critical part of the blade, and a determination of an optimum profile for a turbine stage providing high work per unit of cooled blade surface.
Author: H. O. Demuren Publisher: ISBN: Category : Languages : en Pages : 139
Book Description
The goal of these studies has been to gather the necessary heat transfer data and develop the design procedure for high performance, film cooled, highly loaded transonic turbine stages. In the pursuit of this goal, three key tasks were accomplished: the measurement of heat transfer rates and film effectiveness in the low supersonic range, a study of the flow at the trailing edge of transonic turbine blades and the heat transfer at this critical part of the blade, and a determination of an optimum profile for a turbine stage providing high work per unit of cooled blade surface.
Author: Publisher: ISBN: Category : Languages : en Pages : 123
Book Description
During the fourth year of the contract, further advances were made towards the goal of gathering the heat transfer and aerodynamics flow data necessary for a good understanding of the performance of film-cooled, highly- loaded, transonic turbine blading. Surface Mach number and heat transfer rate distributions were determined for a reference transonic airfoil over a range of exit Mach numbers, for inlet incidence angle variation of + or - 15 deg. An evaluation and comparison of all cascade data collected so far was then conducted. Progress was also made in the investigation of the effects of unsteadiness on transonic airfoil aerodynamics and heat transfer.
Author: Publisher: ISBN: Category : Languages : en Pages : 66
Book Description
This study is an investigation of the film cooling effectiveness and heat transfer coefficient of a two-dimensional turbine rotor blade in a linear transonic cascade. Experiments were performed in Virginia Tech's Cascade Wind Tunnel with an exit Mach number of 1.2 and an exit Reynolds number of 5 x 10 (exp 6) to simulate real engine flow conditions. The freestream and coolant flows were maintained at a total temperature ratio of 2 +0.4 and a total pressure ration of 1.04. The freestream turbulence was approximately 1%. There are six rows of staggered, discrete cooling holes on and near the leading edge of the blade in a showerhead configuration. Cooled air was used as the coolant. Experiments were performed with and without film cooling on the surface of the blade. The heat transfer coefficient was found to increase with the addition of film cooling an average of 14% overall and to a maximum of 26% at the first gauge location. The average film cooling effectiveness that suggest either a transition from a laminar to a turbulent film regime or the regime or the existence of three-dimensionality in the flow-field over the gauges.
Author: Publisher: ISBN: Category : Languages : en Pages : 63
Book Description
This report is the culmination of a two year effort to demonstrate the capability for performing near wall high resolution Time Resolved Particle Image Velocimetry (TRDPIV) measurements in a transonic turbine. Performing TRDPIV in high speed wall bounded flows with high resolution/magnification often posses significant difficulties. For this reason, two preliminary studies where conducted in order to further understand the challenges that would be present in this type of environment. Hardware and algorithm advancements and developments ultimately enabled performing TRDPIV in the transonic cascade facility. However, high pressure, high speed and the turbine blade complex geometries (high curvature and acceleration) significantly inhibit our ability to deliver homogeneous distribution of flow tracers, especially in the near wall region resulting in low quality measurements and regions with randomly missing data. In addition to our experimental results this effort delivers a novel advanced data reconstruction methodology based on proper orthogonal decomposition that was developed to overcome the aforementioned limitation. The following report documents in detail the methods and results generated throughout this effort.
Author: Ernst Rudolf Georg Eckert Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 44
Book Description
Summary: Transpiration and film cooling promise to be effective methods of cooling gas-turbine blades; consequently, analytical and experimental investigations are being conducted to obtain a better understanding of these processes. This report serves as an introduction to these cooling methods, explains the physical processes, and surveys the information available for predicting blade temperatures and heat-transfer rates. In addition, the difficulties encountered in obtaining a uniform blade temperature are discussed, and the possibilities of correcting these difficulties are indicated. Air is the only coolant considered in the application of these cooling methods.
Author: H. O. Demuren
Author: H. O. Demuren
Author: 
Author: 
Author: Fariborz Forghan
Author: B. R. Haller
Author: James D. Heidmann
Author: Andrew Saul
Author: 
Author: A. Kaufman
Author: Ernst Rudolf Georg Eckert