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An experimental comparison of diffuser designs in a centrifugal compressor.

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	An experimental comparison of diffuser designs in a centrifugal compressor./
作者:	Methel, Cam-Tu Jeanne.
面頁冊數:	1 online resource (119 pages)
附註:	Source: Masters Abstracts International, Volume: 56-01.
Contained By:	Masters Abstracts International56-01(E).
標題:	Aerospace engineering. -
電子資源:	click for full text (PQDT)
ISBN:	9781369023343

An experimental comparison of diffuser designs in a centrifugal compressor.
Methel, Cam-Tu Jeanne.

An experimental comparison of diffuser designs in a centrifugal compressor. - 1 online resource (119 pages)

Source: Masters Abstracts International, Volume: 56-01.

Thesis (M.S.A.A.)

Includes bibliographical references

The objective of this investigation was to compare the effects of two different diffuser vane geometries on the performance of a centrifugal compressor. Vaned diffusers are commonly used in aeroengines because they can achieve higher pressure recoveries than vaneless diffusers of similar size. Improving the diffuser's pressure recovery and effectiveness can result in overall compressor performance benefits that are sought out by engine manufacturers looking to improve overall engine efficiency. An airfoil vane was tested and compared to a baseline wedge diffuser in the Purdue CSTAR research facility, where the centrifugal compressor used for this study is intended to be the last stage of an axial-centrifugal compressor.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2018

Mode of access: World Wide Web

ISBN: 9781369023343Subjects--Topical Terms:

686400
Aerospace engineering.
Index Terms--Genre/Form:

554714
Electronic books.

An experimental comparison of diffuser designs in a centrifugal compressor.
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100 1 $a Methel, Cam-Tu Jeanne. $3 1180237
245 1 3 $a An experimental comparison of diffuser designs in a centrifugal compressor.
264 0 $c 2016
300 $a 1 online resource (119 pages)
336 $a text $b txt $2 rdacontent
337 $a computer $b c $2 rdamedia
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500 $a Source: Masters Abstracts International, Volume: 56-01.
500 $a Adviser: Nicole L. Key.
502 $a Thesis (M.S.A.A.) $c Purdue University $d 2016.
504 $a Includes bibliographical references
520 $a The objective of this investigation was to compare the effects of two different diffuser vane geometries on the performance of a centrifugal compressor. Vaned diffusers are commonly used in aeroengines because they can achieve higher pressure recoveries than vaneless diffusers of similar size. Improving the diffuser's pressure recovery and effectiveness can result in overall compressor performance benefits that are sought out by engine manufacturers looking to improve overall engine efficiency. An airfoil vane was tested and compared to a baseline wedge diffuser in the Purdue CSTAR research facility, where the centrifugal compressor used for this study is intended to be the last stage of an axial-centrifugal compressor.
520 $a The overall stage performance for the compressor with the airfoil diffuser was first obtained at open impeller tip clearances and then at tight clearances. In the tight clearance configuration, the compressor consistently had higher total pressure ratio and higher isentropic efficiency compared to the open clearance configuration. In particular, impeller isentropic efficiency and shroud static pressure along the entire impeller passage were highest at the tight impeller clearance configuration, indicating less losses due to tip leakage flow. The reduction in tip leakage flow, and resulting blockage, at tight clearance operation was also suggested by the increase in choke mass flow rate for all corrected speeds.
520 $a For the comparison of the airfoil and wedge diffuser assemblies, data were acquired with the impeller in the tight clearance configuration. Despite slight differences in exducer tip clearances (less than 2x10-3 in.), stage total pressure ratio and isentropic efficiency at 100% corrected speed were not significantly different between the two diffuser assemblies. Upon closer inspection of individual components, the airfoil diffuser actually had, on average, higher pressure recovery and higher diffuser effectiveness than the wedge diffuser. However, the airfoil diffuser assembly had higher losses in the deswirl region compared to the wedge diffuser assembly. Excluding measurements from the deswirl, the total pressure ratio for the airfoil diffuser assembly was slightly greater than that of the wedge diffuser assembly. A physical mismatch in the airfoil diffuser and deswirl assembly could be responsible for the losses recorded in the deswirl region and could have resulted in the limited performance improvements observed. Additionally, the similar vane geometries at the leading edge (in terms of inlet metal angle and thickness) combined with any deviation from design during manufacturing could have limited the predicted performance benefits.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2018
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 686400
655 7 $a Electronic books. $2 local $3 554714
690 $a 0538
710 2 $a ProQuest Information and Learning Co. $3 1178819
710 2 $a Purdue University. $b Aeronautics and Astronautics. $3 845678
773 0 $t Masters Abstracts International $g 56-01(E).
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10147038 $z click for full text (PQDT)