Quantitative investigation of the evaporation and resistance characteristics of inlet jet precooling
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Yuming Lu
,
Hongzi Fei
Abstract
A quantitative study is carried out to explore the air/mist-coupled cooling in the cooling section incorporating a spray device, aiming to conduct a comparative simulation on the effects of two radial spray arrangements (Apparatus A and Apparatus B) on the change of flow field. The results show that an even spray arrangement leads to improved flow performance owing to the large temperature drop in the cooling section. Compared with Apparatus A, Apparatus B enables a 1.60–2.25% higher temperature drop coefficient and a 1.1–3.0% higher water evaporation rate. Six high-altitude conditions are simulated to find that the spray device and water injection are the main factors causing flow loss, whereas the additional mass flow caused by water vapor reduces the amount of loss. The highest temperature drop coefficient is observed for Case 6 (27.3%), in which there is a more uniform nozzle arrangement. A slight difference in terms of total pressure drop coefficient between Apparatus A and Apparatus B is observed. Moreover, the highest total pressure drop coefficient (5.8%) at the location of the spray system is observed for Case 6, which has the largest injection rate and highest inlet air Mach number.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: The authors thank for the financial supports of Fundamental Research Funds for the Central Universities (NO. 3072019cfj0309) from AECC Sichuan Research Institute of Gas Turbine.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Wanng, Z, Wang, Y, Zhang, J, Zhang, B. Overview of the key technologies of combined cycle engine precooling systems and the advanced applications of micro-channel heat transfer. Aero Sci Technol 2014;39:31–9. https://doi.org/10.1016/j.ast.2014.08.008.Suche in Google Scholar
2. Chen, F, Ruan, C, Yu, T, Cai, W, Mao, Y, Liu, X. Effects of fuel variation and inlet air temperature on combustion stability in a gas turbine model combustor. Aero Sci Technol 2019;92:126–38. https://doi.org/10.1016/j.ast.2019.05.052.Suche in Google Scholar
3. Mehta, U, Bowles, J, Melton, J, Huynh, L, Hagseth, P. Water injection pre-compressor cooling assist space access. Aeronaut J 2015;119:145–71. https://doi.org/10.1017/s0001924000010319.Suche in Google Scholar
4. Wilcox, EC, Trout, AM. Analysis of thrust augmentation of turbojet engines by water injection at compressor inlet including charts for calculating compression processes with water injection. NACA; 1951, Report No. NACA TR-1006.Suche in Google Scholar
5. Trout, AM. Theoretical turbojet thrust augmentation by evaporation of water during compression as determined by use of a molly diagram. NACA; 1950, Report No. NACA TN-2104.Suche in Google Scholar
6. Burkardt, LA, Norris, R. The design and evolution of the beta two-stage-to-orbit horizontal take off and landing launch system. AIAA; 1992. Report No. AIAA 1992-5080.10.2514/6.1992-5080Suche in Google Scholar
7. Kloesel, K, Clark, C. Preliminary mipcc enhanced F-4 and F-15 performance characteristics for a first stage reusable launch vehicle. In: AIAA SPACE conference & exposition. San Diego: AIAA; 2013.10.2514/6.2013-5528Suche in Google Scholar
8. Bartolotta, PA, Mcnelis, NB, Shafer, DG. High speed turbines: development of a turbine accelerator (rta) for space access. AIAA; 2003. Report No. AIAA 2003-6943.10.2514/6.2003-6943Suche in Google Scholar
9. Balepin, V, Carter, P, Spath, T, Ossello, C. Mipcc technology development. AIAA; 2003. Report No. AIAA 2003-6929.10.2514/6.2003-6929Suche in Google Scholar
10. Henneberry, HM, Snyder, CA. Analysis of gas turbine engines using water and oxygen injection to achieve high mach numbers and high thrust. NASA; 1993. Report No. NASA TM-106270.Suche in Google Scholar
11. Cater, P, Balepin, V. Mass injection and pre-compressor cooling engines analyses. AIAA; 2002. Report No. AIAA 2002-4127.10.2514/6.2002-4127Suche in Google Scholar
12. Balepin, V, Claudio, B, Antonella, I. Evaluation of the combustion process in the mass injection precompression cooling engine. In: Proc. ISABE; 2003.Suche in Google Scholar
13. Alhazmy, MM, Najjar, YSH. Augmentation of gas turbine performance using air coolers. Appl Therm Eng 2004;24:415–29. https://doi.org/10.1016/j.applthermaleng.2003.09.006.Suche in Google Scholar
14. Kim, KH, Ko, HJ, Perez-Blanco, H. Analytical modeling of wet compression of gas turbine systems. Appl Therm Eng 2011;31:834–40. https://doi.org/10.1016/j.applthermaleng.2010.11.002.Suche in Google Scholar
15. Mahto, D, Pal, S. Thermodynamics and thermo-economic analysis of simple combined cycle with inlet fogging. Appl Therm Eng 2013;1–2:413–24. https://doi.org/10.1016/j.applthermaleng.2012.09.003.Suche in Google Scholar
16. Zheng, Q, Li, M, Sun, Y. Thermodynamic performance of wet compression and regenerative (wcr) gas turbine. In: ASME conference proceedings; 2003.10.1115/GT2003-38517Suche in Google Scholar
17. Rahim, MA. Performance and sensitivity analysis of a combined cycle gas turbine power plant by various inlet air-cooling systems. Proc IME J Power Energy 2012;226:922–31. https://doi.org/10.1177/0957650912456657.Suche in Google Scholar
18. Yang, L, Zhou, J, Fan, S, Zheng, Q, Zhang, H. Method and numerical simulation for evaluating the effects of water film on the performance of low-speed axial compressor. Aero Sci Technol 2019;84:306–17. https://doi.org/10.1016/j.ast.2018.09.041.Suche in Google Scholar
19. Lin, A, Sun, Y, Zhang, H, Lin, X, Yang, L, Zheng, Q. Fluctuating characteristics of air-mist mixture flow with conjugate wall-film motion in a compressor of gas turbine. Appl Therm Eng 2018;142:779–92. https://doi.org/10.1016/j.applthermaleng.2018.07.076.Suche in Google Scholar
20. Lin, A, Zhou, J, Fawzy, H, Zhang, H, Zheng, Q. Evaluation of mass injection cooling on flow and heat transfer characteristics for high-temperature inlet air in a mipcc engine. Int J Heat Mass Tran 2019;135:620–30. https://doi.org/10.1016/j.ijheatmasstransfer.2019.02.025.Suche in Google Scholar
21. Lin, A, Zheng, Q, Fawzy, H, Jiang, Y, Zhang, H. Sensitivity of air/mist nonequilibrium phase transition cooling to transient characteristics in a compressor of gas turbine. Int J Heat Mass Tran 2019;137:882–94. https://doi.org/10.1016/j.ijheatmasstransfer.2019.03.143.Suche in Google Scholar
22. Wulff, A, Hourmouziadis, J. Technology review of aeroengine pollutant emissions. Aero Sci Technol 1997;8:557–72. https://doi.org/10.1016/s1270-9638(97)90004-3.Suche in Google Scholar
23. Sun, L, Zheng, Q, Li, Y, Luo, M, Bhargava, RK. Numerical simulation of a complete gas turbine engine with wet compression. J Eng Gas Turbines Power 2013;135:012002. https://doi.org/10.1115/1.4007366.Suche in Google Scholar
24. Novelo, DAB, Igie, U. Aero engine compressor cooling by water injection—part 2: performance and emission reductions. Energy 2018;160:1236–43. https://doi.org/10.1016/j.energy.2018.05.171.Suche in Google Scholar
25. Xiang, G, Ren, Z, Kim, S, Wang, B. Numerical analysis on the disintegration of gas-liquid interface in two-phase shear-laver flows. Aero Sci Technol 2020;98:105710. https://doi.org/10.1016/j.ast.2020.105710.Suche in Google Scholar
26. Elwekeel, FNM, Abdala, AMM. Effect of mist cooling technique on exergy and energy analysis of steam injected gas turbine cycle. Appl Therm Eng 2016;98:298–309. https://doi.org/10.1016/j.applthermaleng.2015.12.040.Suche in Google Scholar
27. Kim, KH, Ko, HJ, Kim, K, Perez-Blacco, H. Analysis of water droplet evaporation in a gas turbine inlet fogging process. Appl Therm Eng 2012;33–34:62–9. https://doi.org/10.1016/j.applthermaleng.2011.09.012.Suche in Google Scholar
28. Zhang, H, Luo, M, Pan, X, Zheng, Q. Numerical analysis of gas turbine inlet fogging nozzle manifold resistance. Proc IME J Power Energy 2016;230:63–75. https://doi.org/10.1177/0957650915616279.Suche in Google Scholar
29. Lin, A, Zhou, J, Fawzy, H, Zhang, H, Zheng, Q. Effect of water injection cooling on flow field characteristics in the cooling section of precooled turbine-based combined cycle engine. Int J Heat Mass Tran 2019;141:615–26. https://doi.org/10.1016/j.ijheatmasstransfer.2019.07.012.Suche in Google Scholar
© 2022 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- 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
Artikel in diesem Heft
- 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
