Details
| Original language | English |
|---|---|
| Title of host publication | Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air |
| Pages | 141-152 |
| Number of pages | 12 |
| Publication status | Published - 19 Sept 2008 |
| Event | 2006 ASME 51st Turbo Expo - Barcelona, Spain Duration: 6 May 2006 → 11 May 2006 |
Publication series
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Volume | 6 PART A |
Abstract
The present paper provides a comparison of a CDA-bladed four-stage high-speed axial compressor and a configuration in which the first three rows are replaced with forward swept blades and vanes. The blades are designed with sweep from mid-span to tip, the vanes from mid-span to the hub. The non-swept portion of the leading edge is kept radial and identical to the CDA blading. The overall performance of the compressor with both configurations is measured at five engine speeds. The flow fields of each rotor and stator at two operating points ("Design Point" and "Near Stall") of both configurations are investigated at the design speed. On the suction and the pressure side of the third stage vane, static surface pressures are measured to determine the local Mach number distribution and to identify zones of separation. Multistage CFD-computations are carried out for both configurations. The numerical and experimental results of both configurations are compared and show the effect of sweep on the operating map of the compressor from choke to stall: Sweep reduces corner stall and the end-wall losses at high aerodynamic loads. It is shown that the reduction of separation due to sweep leads to an increase of total pressure rise towards lower mass flow so that the present swept compressor achieves higher total pressure ratios at and near the stall limit. An analysis along streamlines suggests that the performance of the compressor could have been improved further by a more uniform total pressure distribution in the front stages and a better match of the sweep in stages 2 and 3.
Keywords
- 3D blade design, Axial compressor, CDA, Forward sweep, Secondary flow
ASJC Scopus subject areas
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Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air. 2008. p. 141-152 (Proceedings of the ASME Turbo Expo; Vol. 6 PART A).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Forward Sweep in a Four-Stage High-Speed Axial Compressor
AU - Braun, Michael
AU - Seume, Joerg R.
N1 - Funding information: The authors were both members of the Northrn Terrry iUtoersny, iDitrviwan, Australia, when this research was undertaken, and wish to acknowledge a research grant from the University which permitted the projcet tbouen ken.derta Thyaelso wish to acknowledge the permission granted by Aboriginal ownrs e and managemenof Ut ru-Kaltua Tjuta National Park allowing them access to the Park and its clientele, and also to the Parks and Wildlife Commission of the Northern Territory, and the staffof the Dsert PeraAke,Sl ipcfor rsiiinrlmalgys
PY - 2008/9/19
Y1 - 2008/9/19
N2 - The present paper provides a comparison of a CDA-bladed four-stage high-speed axial compressor and a configuration in which the first three rows are replaced with forward swept blades and vanes. The blades are designed with sweep from mid-span to tip, the vanes from mid-span to the hub. The non-swept portion of the leading edge is kept radial and identical to the CDA blading. The overall performance of the compressor with both configurations is measured at five engine speeds. The flow fields of each rotor and stator at two operating points ("Design Point" and "Near Stall") of both configurations are investigated at the design speed. On the suction and the pressure side of the third stage vane, static surface pressures are measured to determine the local Mach number distribution and to identify zones of separation. Multistage CFD-computations are carried out for both configurations. The numerical and experimental results of both configurations are compared and show the effect of sweep on the operating map of the compressor from choke to stall: Sweep reduces corner stall and the end-wall losses at high aerodynamic loads. It is shown that the reduction of separation due to sweep leads to an increase of total pressure rise towards lower mass flow so that the present swept compressor achieves higher total pressure ratios at and near the stall limit. An analysis along streamlines suggests that the performance of the compressor could have been improved further by a more uniform total pressure distribution in the front stages and a better match of the sweep in stages 2 and 3.
AB - The present paper provides a comparison of a CDA-bladed four-stage high-speed axial compressor and a configuration in which the first three rows are replaced with forward swept blades and vanes. The blades are designed with sweep from mid-span to tip, the vanes from mid-span to the hub. The non-swept portion of the leading edge is kept radial and identical to the CDA blading. The overall performance of the compressor with both configurations is measured at five engine speeds. The flow fields of each rotor and stator at two operating points ("Design Point" and "Near Stall") of both configurations are investigated at the design speed. On the suction and the pressure side of the third stage vane, static surface pressures are measured to determine the local Mach number distribution and to identify zones of separation. Multistage CFD-computations are carried out for both configurations. The numerical and experimental results of both configurations are compared and show the effect of sweep on the operating map of the compressor from choke to stall: Sweep reduces corner stall and the end-wall losses at high aerodynamic loads. It is shown that the reduction of separation due to sweep leads to an increase of total pressure rise towards lower mass flow so that the present swept compressor achieves higher total pressure ratios at and near the stall limit. An analysis along streamlines suggests that the performance of the compressor could have been improved further by a more uniform total pressure distribution in the front stages and a better match of the sweep in stages 2 and 3.
KW - 3D blade design
KW - Axial compressor
KW - CDA
KW - Forward sweep
KW - Secondary flow
UR - http://www.scopus.com/inward/record.url?scp=33750883187&partnerID=8YFLogxK
U2 - 10.1115/GT2006-90218
DO - 10.1115/GT2006-90218
M3 - Conference contribution
AN - SCOPUS:33750883187
SN - 079184241X
SN - 9780791842416
T3 - Proceedings of the ASME Turbo Expo
SP - 141
EP - 152
BT - Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air
T2 - 2006 ASME 51st Turbo Expo
Y2 - 6 May 2006 through 11 May 2006
ER -