Local heat transfer and film effectiveness of a film cooled gas turbine blade tip /
Gas turbine engines due to high operating temperatures undergo severe thermal stress and fatigue during operation. Cooling of these components is a very important issue during the lifetime of the engine. Cooling is achieved through the use of internal and external cooling holes. Several studies have...
| Main Author: | |
|---|---|
| Format: | Thesis eBook |
| Language: | English |
| Published: |
[Place of publication not identified] :
[publisher not identified] ;
1999.
|
| Subjects: | |
| Online Access: | Link to OAKTrust copy |
| Summary: | Gas turbine engines due to high operating temperatures undergo severe thermal stress and fatigue during operation. Cooling of these components is a very important issue during the lifetime of the engine. Cooling is achieved through the use of internal and external cooling holes. Several studies have been conducted to help in understanding the heat transfer of gas turbines. This study presents the heat transfer and film effectiveness distribution on the cavity surface of a gas turbine blade tip. A transient liquid crystal technique is used to obtain contour plots of the cavity surface temperature profile. The results are presented for different Reynolds number, hole, and cavity configurations. |
|---|---|
| Item Description: | "Major subject: Mechanical Engineering". Vita. |
| Physical Description: | xiv, 140 leaves : illustrations ; 28 cm. Also available online. Issued also on microfiche from Lange Micrographics. |
| Bibliography: | Includes bibliographical references (leaves 79-81). |