Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
-
Yang Yong
,
Gao Jie
Abstract
In order to improve the effectiveness of compressor efficiency measurement results under the influence of complex factors, several research work have been carried out, such as inverse connection of thermocouple suitable for efficiency measurement under low pressure ratio and small temperature rise conditions, torque efficiency correction considering the mechanical loss of high speed gearbox under various working conditions, and identification of the impact of seal cavity leakage flow on efficiency measurement. Compared with the conventional connection method of thermocouple, the inverse connection method of thermocouple shows obvious advantages in efficiency measurement under low pressure ratio and small temperature rise conditions. At medium and low speeds, the conventional simplified correction method will lead to the high measurement results of torque efficiency after installing the high speed gearbox. The accuracy of torque efficiency measurement can be improved by adopting the improved correction method. Increasing the oil supply pressure of the high speed gearbox or reducing the oil supply temperature will increase the mechanical loss of the high speed gearbox. The air flow in the compressor bearing seal chamber will leak into the flow passage through the labyrinth clearance, resulting in discontinuous changes of the inlet/outlet flow of compressor.
Acknowledgement
This research work has been funded by Sichuan Science and Technology Program (No. 2022JDRC0013, No. 2020YFG0177, and No. 2022YFG0360), Basic Military Research Institute Stability Support Project (No. GJCZ-0207-21), Advanced Aviation Power Innovation Workstation Project (No. HKCX2022-01-022) and the Open Fund Project of Key Laboratory of Civil Aviation Flight Technology and Fight Safety (Grant No. FZ2020KF09 and FZ2021ZZ06). The authors would like to express their gratitude to Sichuan Gas Turbine Establishment of Aero Engine Corporation of China for its support and permission to publish.
-
Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
-
Research funding: None declared.
-
Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Adamczyk, JJ, Hansen, JL, Prahst, PS. A post test analysis of a high-speed two-stage axial flow compressor. In: ASME paper GT2007-28057, turbo expo: power for land, sea, and air; 2007, vol 47950:377–88 pp.10.1115/GT2007-28057Search in Google Scholar
2. Gannon, AJ, Hobson, GV, Shreeve, RP, Villescas, LJ. Experimental investigation during stall and surge in a transonic fan stage and rotor-only configuration. In: ASME paper GT2006-90925, turbo expo: power for land, sea, and air; 2006, vol 4241:367–76 pp.10.1115/GT2006-90925Search in Google Scholar
3. Hah, C, Voges, M, Mueller, M, Schiffer, HP. Characteristics of tip clearance flow instability in a transonic compressor. In: ASME paper GT2010-22101, turbo expo: power for land, sea, and air; 2010, vol 44021:63–74 pp.10.1115/GT2010-22101Search in Google Scholar
4. Ottavy, X, Trebinjac, I, Vouillarmet, A. Analysis of the inter-row flow field within a transonic axial compressor: part 1-experiment investigation. In: ASME paper 2000-GT-496, turbo expo: power for land, sea, and air. American Society of Mechanical Engineers; 2000, vol 4096:4104 p.10.1115/2000-GT-0496Search in Google Scholar
5. Jiang, S, Qiu, Q, Yuan, S, Shi, XJ, Li, L, Zhang, XY, et al.. Stochastic resonance for a bistable system with multiplicative noise and additive recycled noise. Indian J Phys 2022;96:1–7. https://doi.org/10.1007/s12648-022-02301-7.Search in Google Scholar
6. Walther, R, Frischbier, J, Selmeier, R. Aeromechanical design of advanced engine compressors. In: ISABE-2001-1241, international symposium on air breathing engines, 15th. Bangalore, India; 2001.Search in Google Scholar
7. Broichhausen, KD, Ziegler, KU. Supersonic and transonic compressors: past, status and technology trends. In: ASME paper GT 2005-69067, turbo expo: power for land, sea, and air; 2005, vol 47306:63–74 pp.10.1115/GT2005-69067Search in Google Scholar
8. Mansour, ML, Gunaraj, J, Goswami, S. Validation of steady average-passage and mixing plane CFD approaches for the performance prediction of a modern gas turbine multistage axial compressor. In: ASME paper GT2008-50653, turbo expo: power for land, sea, and air; 2008, vol 43161:393–403 pp.10.1115/GT2008-50653Search in Google Scholar
9. Miller, DP, Prahst, PS. Inlet flow test calibration for a small axial compressor facility part 1: design and experimental results. In: AIAA 94–2690, joint propulsion conference; 1994.10.2514/6.1994-2690Search in Google Scholar
10. Casey, MV, Fesich, TM. On the efficiency of compressor with diabatic flows. In: ASME paper GT2009-59015, turbo expo: power for land, sea, and air; 2009, vol 48821:785–97 pp.10.1115/GT2009-59015Search in Google Scholar
11. Abernethy, RB, Thompson, JW. Uncertainty in gas turbine measurements. In: 9th propulsion conference, Las Vegas, NEVADA, AIAA 73–1230; 1973.10.2514/6.1973-1230Search in Google Scholar
12. Brun, K, Kurz, R. Measurement uncertainties encountered during gas turbine driven compressor field testing. In: ASME paper 98-GT-1; 1998.10.1115/98-GT-001Search in Google Scholar
13. Bettocchi, R, Pinelli, M. A multi-stage compressor test facility: uncertainty analysis and preliminary test results. In: ASME paper GT2003-38397, turbo expo: power for land, sea, and air; 2003, vol 36878:53–61 pp.10.1115/GT2003-38397Search in Google Scholar
14. Barankiewicz, WS, Hathaway, MD. Effects of stator indexing on performance in a low speed multistage axial compressor. In: NASA TM-113113; 1997.10.1115/97-GT-496Search in Google Scholar
15. Xiang, HH, Ge, N, Gao, J, Yang, RF, Hou, MJ. Experimental investigation of the effect of the probe support tail structure on the compressor cascade flow field. Int J Turbo Jet Engines 2019;36:9–18. https://doi.org/10.1515/tjj-2016-0071.Search in Google Scholar
16. Xiang, HH, Ge, N, Hou, MJ, Gao, J, Yang, RF. An experimental investigation of the effects of upstream probe disturbance on compressor cascade performance. Proc IME G J Aero Eng 2017;231:1248–57. https://doi.org/10.1177/0954410016652435.Search in Google Scholar
17. He, X, Ma, HW, Ren, ML, Xiang, HH. Investigation of the effects of airfoil-probes on the aerodynamic performance of an axial compressor. Chin J Aeronaut 2012;25:517–23. https://doi.org/10.1016/s1000-9361(11)60415-9.Search in Google Scholar
18. Berdanier, RA, Smith, NR, Fabian, JC, Key, NL. Humidity effects on experimental compressor performance-corrected conditions for real gases. J Turbomach 2015;137:031011. https://doi.org/10.1115/1.4028356.Search in Google Scholar
19. Tomita, JT, Bontempo, LP, Barbosa, JR. An axial-flow compressor for operation with humid air and water injection. In: ASME paper GT2010-22996, turbo expo: power for land, sea, and air; 2010, vol 43987:721–31 pp.10.1115/GT2010-22996Search in Google Scholar
20. Anderson, NE, Loewenthal, SH. Spur-gear-system efficiency at part and full load. In: NASA TP-1622; 1980.Search in Google Scholar
21. Wellborn, SR, Koiro, ML. Bleed flow interactions with an axial-flow compressor power-stream. In: AIAA 2002-4057, 38th AIAA/ASME/SAE/ASEE joint propulsion conference & exhibit; 2002:4057 p.10.2514/6.2002-4057Search in Google Scholar
22. Wellborn, SR, Okiishi, TH. Effects of shrouded stator cavity flows on multistage axial compressor aerodynamic performance. Cleveland, OH: NASA CR 198536; 1996.Search in Google Scholar
23. Wisler, DC. Loss reduction in axial-flow compressors through low-speed model testing. ASME J Eng Gas Turbines Power 1984;107:353–63.10.1115/1.3239730Search in Google Scholar
24. Shabbir, A, Celestina, ML, Adamczyk, JJ, Strazisar, AJ. The effect of hub leakage flow on two high speed axial compressor rotors. In: ASME paper 97-GT-346, IGTI-ASME congress and exhibition. Orlando; 1997.10.1115/97-GT-346Search in Google Scholar
25. Xiang, HH, Ren, ML. Discussion of several questions with efficiency assessment in axial flow compressor experiment. In: 2009 Asia-Pacific international symposium on aerospace technology. Gifu, Japan, JSASS-2009-5537; 2009.Search in Google Scholar
© 2022 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- The International Journal of Turbo and Jet Engines
- The aerothermodynamic cycle optimal design of a turbofan engine
- Multi-condition design optimization of groove flow control technique in an axial-flow pump
- Analysis on impulse characteristics of pulse detonation engine with nozzles
- Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
- Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
- Applicability of correlational data-mining to small-scale turbojet performance map generation
- Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
- Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
- Modeling and analysis of 3D radiative heat transfer in combustor
- A creep-fatigue life prediction model considering multi-factor coupling effect
- Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
- Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
- A study on design optimization for compressor blisks
- Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
- Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
- Predicting remaining useful life of turbofan engines using degradation signal based echo state network
- Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
- Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
- Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
- Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
- Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
- Performance enhancement and flow separation control in an S-duct by air injection
- Gas dynamic analysis of the modern single shaft gas turbine engine flow path
- Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
- Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils
- The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
- Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
- Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
- Research on temperature rise characteristics of end V-groove ring seal
- Research on the influence of honeycomb cell blockage on the seal leakage characteristics
- Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation
- Development and application of a profile loss model considering the low-Re effect in low-pressure turbine
- Optimization of ACE mode transition control schedule considering geometric adjustment speed
- Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps
- The design method of the V-shaped groove piston ring
- Control of subsonic jets using vanes as vortex generators
- Impact investigation of inlet environmental changes on the rated condition performance of a high-pressure compressor
- Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed
- Effect of the distribution of the upstream probe support on performance of compressor cascade
- Effect of bypass ratio on sonic underexpanded co-flow jets with finite lip thickness
- Machine learning augmented multi-sensor data fusion to detect aero engine fan rotor blade flutter
- CFD analysis of flow control in compressor cascade using MVGs
- Quantitative investigation of the evaporation and resistance characteristics of inlet jet precooling
- Study on laser de-weight and dynamic balance technology of rotating machines
- Integrated design and analysis of inlet and missile with two side layout
- Research on turboprop engine control method based on linear parameter varying model
- Modeling and validation of the volume effect on the axial fan transient performance
- Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
- Multidisciplinary sensitivity analysis for turbine blade considering thickness uncertainties
- Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
- Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex
- Infrared simulation of aircraft rear fuselage based on a coupled CFD method
- Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
- Numerical study of transition process in different zones of a compressor cascade channel
Articles in the same Issue
- Frontmatter
- The International Journal of Turbo and Jet Engines
- The aerothermodynamic cycle optimal design of a turbofan engine
- Multi-condition design optimization of groove flow control technique in an axial-flow pump
- Analysis on impulse characteristics of pulse detonation engine with nozzles
- Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
- Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
- Applicability of correlational data-mining to small-scale turbojet performance map generation
- Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
- Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
- Modeling and analysis of 3D radiative heat transfer in combustor
- A creep-fatigue life prediction model considering multi-factor coupling effect
- Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
- Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
- A study on design optimization for compressor blisks
- Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
- Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
- Predicting remaining useful life of turbofan engines using degradation signal based echo state network
- Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
- Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
- Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
- Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
- Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
- Performance enhancement and flow separation control in an S-duct by air injection
- Gas dynamic analysis of the modern single shaft gas turbine engine flow path
- Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
- Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils
- The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
- Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
- Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
- Research on temperature rise characteristics of end V-groove ring seal
- Research on the influence of honeycomb cell blockage on the seal leakage characteristics
- Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation
- Development and application of a profile loss model considering the low-Re effect in low-pressure turbine
- Optimization of ACE mode transition control schedule considering geometric adjustment speed
- Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps
- The design method of the V-shaped groove piston ring
- Control of subsonic jets using vanes as vortex generators
- Impact investigation of inlet environmental changes on the rated condition performance of a high-pressure compressor
- Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed
- Effect of the distribution of the upstream probe support on performance of compressor cascade
- Effect of bypass ratio on sonic underexpanded co-flow jets with finite lip thickness
- Machine learning augmented multi-sensor data fusion to detect aero engine fan rotor blade flutter
- CFD analysis of flow control in compressor cascade using MVGs
- Quantitative investigation of the evaporation and resistance characteristics of inlet jet precooling
- Study on laser de-weight and dynamic balance technology of rotating machines
- Integrated design and analysis of inlet and missile with two side layout
- Research on turboprop engine control method based on linear parameter varying model
- Modeling and validation of the volume effect on the axial fan transient performance
- Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
- Multidisciplinary sensitivity analysis for turbine blade considering thickness uncertainties
- Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
- Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex
- Infrared simulation of aircraft rear fuselage based on a coupled CFD method
- Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
- Numerical study of transition process in different zones of a compressor cascade channel
