The total temperature and pressure are measured as inter-stage data in axial compressor experiments. Traditional diagnosing methods of 0-dimension (0D) or 1-dimension (1D) could lead to higher errors at hub sections without the presence of the radial equilibrium equation at stator leading edges, and 3-dimensional computational fluid dynamics can hardly provide reliable results for multistage compressors. In this paper, a fast method called “Diagnosis Using Inter-stage Data” (DUID) was developed to convert experiment data into meridional flow fields, which automatically satisfies the radial equilibrium equation and provides more accurate results for axial compressors. An aeroengine fan, a 3-stage compressor and a 6-stage compressor were used to validate the DUID. Their meridional flow fields, which cannot be observed directly in test rigs, were rebuilt. Results reveal facts that hub static pressures are approximately 15% lower than the traditional 0D/1D constant assumption. Though the stator models determine the loss ratio in a single stage, the DUID can avoid the model error amplification and be robustious for multistage compressors. And the generated flow field is sensitive to changes in the total temperature. Analyses of the experiment flow fields provide more quantitative and accurate references for subsequent modifications. In conclusion, using experiment inter-stage data, the DUID can rebuild meridional flow fields, which help to improve data processing accuracy.
BenserWA. Analysis of part-speed operation for high-pressure-ratio multistage axial-flow compressors. Tech Report Archive Image Library1953.
2.
BrownLEGrohFG. Use of experimental interstage performance data to obtain optimum performance of multistage axial compressors. J Eng Gas Turbines Power1962; 84(2): 187–194.
3.
BlochGSO’BrienWF. A wide-range axial-flow compressor stage performance model. In: Proceedings of the ASME 1992 international gas turbine and aeroengine congress and exposition, Cologne, Germany, 1–4 June 1992.
4.
WilkesKO’BrienWFOwenAK. Dynamic modeling of starting aerodynamics and stage matching in an axi-centrifugal compressor. In: ASME 1996 international gas turbine and aeroengine congress and exhibition, Birmingham, UK, 10–13 June 1996.
5.
ConnellJW. Data reduction of single stage compressor. Ohio: Aerospace Research Labs Wright-Patterson AFB. 1975.
6.
DentonJD. Some limitations of turbomachinery CFD. In: ASME turbo expo 2010: Power for land, sea, and air. American society of mechanical engineers digital collection, Glasgow, UK, 14–18 June 2010.
7.
FritschGGilesMB. An asymptotic analysis of mixing loss. J Turbomach1995; 117(3): 367–374.
8.
AdamczykJJ. Aerodynamic analysis of multistage turbomachinery flows in support of aerodynamic design. J Turbomach1999; 122(2): 189–217.
9.
DuPNingF. Validation of a novel mixing-plane method for multistage turbomachinery steady flow analysis. Chin J Aeronautics2016; 29(6): 1563–1574.
10.
HarrisonS. The influence of blade lean on turbine losses. In: ASME 1990 international gas turbine and aeroengine congress and exposition. American society of mechanical engineers, Brussels, Belgium, 11–14 June 1990.
11.
WalshJAGregory-SmithDG. Inlet skew and the growth of secondary losses and vorticity in a turbine cascade. In: ASME 1989 international gas turbine and aeroengine congress and exposition. American society of mechanical engineers, Toronto, Ontario, Canada, 4–8 June 1989. 1989.
12.
MaHWeiWOttavyX. Experimental investigation of flow field in a laboratory-scale compressor. Chin J Aeronautics2017; 30(1): 31–46.
13.
LeiVM. A simple criterion for three-dimensional flow separation in axial compressors. Cambridge, Massachusetts: Massachusetts Institute of Technology, 2006.
14.
KochCCSmithLHJr. Loss sources and magnitudes in axial-flow compressors. J Eng Power1976; 98(3): 411–424.
DongYGallimoreSJHodsonHP. Three-dimensional flows and loss reduction in axial compressors. In: ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, Dusseldorf, West Germany, 8–12 June 1986.
17.
WislerDCKochCCSmithLHJr. Preliminary design study of advanced multistage axial flow core compressors. Cleveland, OH, United States: NASA Lewis Research Center, 1977.
18.
HollowayPRKochCCKnightGL, et al. Energy efficient engine. High pressure compressor detail design report. Cleveland, OH, United States: NASA Lewis Research Center, 1982.
19.
SteinkeRJ. Design of 9.271-pressure-ratio five-stage core compressor and overall performance for first three stages. Washington, DC: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.
20.
LarosiliereLMWoodJRHathawayMD, et al. Aerodynamic design study of advanced multistage axial compressor. Cleveland, OH, United States: NASA Glenn Research Center, 2002.
21.
LakshminarayanaBSuryavamshiNPratoJ, et al.Experimental investigation of the flow field in a multistage axial flow compressor. Int J Rotating Machinery1996; 2: 578343.
22.
BanjacMPetrovicMVWiedermannA. Multistage axial compressor flow field predictions using CFD and through-flow calculations. In: ASME turbo expo 2016: turbomachinery technical conference and exposition. American society of mechanical engineers digital collection, Seoul, South Korea, 13–17 June 2016.
23.
CorneliusCBiesingerTGalpinP, et al.Experimental and computational analysis of a multistage axial compressor including stall prediction by steady and transient CFD methods. J Turbomach2014; 136(6): 061013.
24.
GotoTOshioTTaniN, et al.Effect of turbulence model on the prediction of performance and span-wise mixing in high-speed highly-loaded multi-stage axial-flow compressor. In: Proceedings of the ASME turbo expo 2019: Turbomachinery technical conference and exposition, Phoenix, Arizona, USA, 17–21 June 2019.
25.
WuCH. A general though-flow theory of fluid flow with subsonic or supersonic velocity in turbomachines of arbitrary hub and casing shapes. Washington DC: National Aeronautics And Space Administration, 1951.
26.
WuCH.A general theory of three-dimensional flow in subsonic or supersonic turbomachines in radial, axial and mixed-flow types. Washington DC: National Aeronautics And Space Administration, 1952.
27.
BullockROJohnsenIA. Aerodynamic design of axial flow compressors[J]. Washington, DC: Scientific and Technical Information Division, National Aeronautics and Space Administration, 1965.
28.
DunhamJ. Analysis of high speed multistage compressor throughflow using spanwise mixing. In: ASME international gas turbine & aeroengine congress & exposition, Cologne, Germany, 1–4 June 1992.
29.
ReitenbachSSchnoesMBeckerRG, et al.Optimization of compressor variable geometry settings using multi-fidelity simulation. In: ASME IGTI 2015 turbo expo, Montreal, Quebec, Canada, 15–19 June 2015.
30.
BanjacMPetrovicMVWiedermannA. Secondary flows, endwall effects and stall detection in axial compressor design. J Turbomach2014; 137(5): 051004.
31.
JinHJinDLiX, et al.A time-marching throughflow model and its application in transonic axial compressor. J Therm Sci2010; 19(6): 519–525.
32.
YangCWuHYangJ, et al.Time-marching throughflow analysis of multistage axial compressors based on a novel inviscid blade force model. Proc Inst Mech Eng G: J Aerospace Eng2019; 233(14): 5239–5252.
33.
HeXMaHRenM, et al.Investigation of the effects of airfoil-probes on the aerodynamic performance of an axial compressor. Chin J Aeronautics2012; 25(4): 517–523.
34.
IkeguchiTMatsuokaASakaiY, et al.Design and development of a 14-stage axial compressor for industrial gas turbine. In: Asme turbo expo: turbine technical conference & exposition, Copenhagen, Denmark, 11–15 June 2012.
35.
XiangHRenMMaH, et al.Effect of airfoil probes on the experiment result of axial flow compressor performance. Chengdu, China: Gas Turbine Experiment and Research, 2008[Chinese]
36.
LiebleinS. Aerodynamic Design of Axial-flow Compressors. VI - Experimental Flow in Two-Dimensional Cascades. Cleveland, OH, United States: NASA Special Publication, 1955.
37.
MillerDCWasdellDL. Off-design prediction of compressor blade losses. IMechE Paper. 1987.
38.
DunhamJ. Compressor off-design performance prediction using an endwall model. In: ASME 1996 international gas turbine and aeroengine congress and exhibition. American society of mechanical engineers digital collection, Birmingham, UK, 10–13 June 1996.
