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A computational approach for investi...

Reid, Terry Vincent.

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A computational approach for investigating unsteady turbine heat transfer due to shock wave impact.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	A computational approach for investigating unsteady turbine heat transfer due to shock wave impact./
作者:	Reid, Terry Vincent.
面頁冊數:	120 p.
附註:	Source: Dissertation Abstracts International, Volume: 60-03, Section: B, page: 1274.
Contained By:	Dissertation Abstracts International60-03B.
標題:	Engineering, Mechanical. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=9917303
ISBN:	0599162007

A computational approach for investigating unsteady turbine heat transfer due to shock wave impact.
Reid, Terry Vincent.

A computational approach for investigating unsteady turbine heat transfer due to shock wave impact. - 120 p.

Source: Dissertation Abstracts International, Volume: 60-03, Section: B, page: 1274.

Thesis (Ph.D.)--Virginia Polytechnic Institute and State University, 1999.

The effects of shock wave impact on unsteady turbine blade heat transfer are investigated. A numerical approach is developed to simulate the flow physics present in a previously performed unsteady wind tunnel experiment. The wind tunnel experiment included unheated and heated flows over a cascade of highly loaded turbine blades. After the flow over the blades was established, a single shock with a pressure ratio of 1.1 was introduced into the wind tunnel test section. A single blade passage was equipped with pressure transducers and heat flux microsensors. As the shock wave strikes the blade, time resolved pressure, temperature and heat transfer data are recorded.

ISBN: 0599162007Subjects--Topical Terms:

783786
Engineering, Mechanical.

A computational approach for investigating unsteady turbine heat transfer due to shock wave impact.
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245 1 2 $a A computational approach for investigating unsteady turbine heat transfer due to shock wave impact.
300 $a 120 p.
500 $a Source: Dissertation Abstracts International, Volume: 60-03, Section: B, page: 1274.
500 $a Chairman: Wing F. Ng.
502 $a Thesis (Ph.D.)--Virginia Polytechnic Institute and State University, 1999.
520 $a The effects of shock wave impact on unsteady turbine blade heat transfer are investigated. A numerical approach is developed to simulate the flow physics present in a previously performed unsteady wind tunnel experiment. The wind tunnel experiment included unheated and heated flows over a cascade of highly loaded turbine blades. After the flow over the blades was established, a single shock with a pressure ratio of 1.1 was introduced into the wind tunnel test section. A single blade passage was equipped with pressure transducers and heat flux microsensors. As the shock wave strikes the blade, time resolved pressure, temperature and heat transfer data are recorded.
520 $a This document describes a numerical approach, where the purpose is to better understand the flow physics contributing to the experimental heat flux data. Simplifications are made to the complete unsteady Navier-Stokes equations to produce a more manageable set of governing equations. The simplified governing equations and the computational discritization will only allow the numerical simulation to address normally impacting shock waves, which were found experimentally to produce the highest levels of heat transfer. The pre-shock wind tunnel flow conditions were used as initial conditions to calculate the boundary layer profiles in a shock-free flowfield. The resulting profiles were then used as the initial conditions for a flowfield containing a shock wave. The solutions were inserted into a first-order time response model, so that the heat flux gage response could be simulated. The comparison of this numerical data showed generally good qualitative and good agreement with the experimentally obtained data.
520 $a Results showed that when the heat transfer is averaged over a 50 musecond period, typical of real blade-passing events, the increase in heat transfer is 110%. However, when integrating over a time period from when the shock first enters the boundary layer, travels down to the surface, reflects and then exits the boundary layer, an order of magnitude increase in heat transfer is observed above the value prior to shock impact.
590 $a School code: 0247.
650 4 $a Engineering, Mechanical. $3 783786
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791 $a Ph.D.
792 $a 1999
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