東華大學圖書館 |

語系: 繁體中文

說明(常見問題)

回圖書館首頁

手機版館藏查詢

登入

回首頁

切換: 標籤 | MARC模式 | ISBD

Trailing edge noise propagation thro...

Roy, Charlie Desire.

FindBook

Google Book

Amazon

博客來

Trailing edge noise propagation through a cascade of blades.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Trailing edge noise propagation through a cascade of blades./
作者:	Roy, Charlie Desire.
面頁冊數:	93 p.
附註:	Source: Masters Abstracts International, Volume: 41-05, page: 1471.
Contained By:	Masters Abstracts International41-05.
標題:	Engineering, Aerospace. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=1413132

Trailing edge noise propagation through a cascade of blades.
Roy, Charlie Desire.

Trailing edge noise propagation through a cascade of blades. - 93 p.

Source: Masters Abstracts International, Volume: 41-05, page: 1471.

Thesis (M.S.)--Florida Atlantic University, 2003.

Aircraft engine fan trailing edge noise prediction is very challenging. To achieve a better understanding of the physics of the propagation problem, the fan has been modeled as an infinite cascade of blades and acoustic monopoles and dipoles have been placed at the trailing edges. The flow has been computed using the Transonic Small Disturbance equation. As soon as the critical Mach number is exceeded by the free stream, a supersonic region that joins two consecutive blades appears. It completely blocks the sound and limits the study to entirely subsonic flow.Subjects--Topical Terms:

1018395
Engineering, Aerospace.

Trailing edge noise propagation through a cascade of blades.
LDR:01788nmm 2200277 4500 001 1810208
005 20040126131523.5
008 130610s2003 eng d
035 $a (UnM)AAI1413132
035 $a AAI1413132
040 $a UnM $c UnM
100 1 $a Roy, Charlie Desire. $3 1899830
245 1 0 $a Trailing edge noise propagation through a cascade of blades.
300 $a 93 p.
500 $a Source: Masters Abstracts International, Volume: 41-05, page: 1471.
500 $a Adviser: S. A. L. Glegg.
502 $a Thesis (M.S.)--Florida Atlantic University, 2003.
520 $a Aircraft engine fan trailing edge noise prediction is very challenging. To achieve a better understanding of the physics of the propagation problem, the fan has been modeled as an infinite cascade of blades and acoustic monopoles and dipoles have been placed at the trailing edges. The flow has been computed using the Transonic Small Disturbance equation. As soon as the critical Mach number is exceeded by the free stream, a supersonic region that joins two consecutive blades appears. It completely blocks the sound and limits the study to entirely subsonic flow.
520 $a In this type of flow, a sound propagation simulator has been implemented. The linearized form of Howe's equation is solved by a high frequency method. The ray caustic problem which causes regular ray tracing failure is fixed by interpolating the field on a preset grid. Results are compared with the analytical solution in uniform flow and computations in realistic flow are presented.
590 $a School code: 0119.
650 4 $a Engineering, Aerospace. $3 1018395
650 4 $a Physics, Acoustics. $3 1019086
690 $a 0538
690 $a 0986
710 2 0 $a Florida Atlantic University. $3 1017837
773 0 $t Masters Abstracts International $g 41-05.
790 1 0 $a Glegg, S. A. L., $e advisor
790 $a 0119
791 $a M.S.
792 $a 2003
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=1413132