Optimizing the axial distance of the nozzle to the engine shell to cool the maximum fluid flow

Document Type : Research Paper

Authors

1 Department of Mechanical Engineering, Yazd Branch, Islamic Azad University, Yazd, Iran

2 Department of Mechanical Engineering, Technical and Vocational University (TVU), Tehran, Iran

Abstract

The purpose of this paper is to obtain the optimal axial distance from the nozzle to the motor shell for suction of the maximum flow rate of the cooling fluid. Given that there is no laboratory data to evaluate numerical analysis, an attempt was made to validate the numerical coefficient of the NACA0012 blade lift by numerical method to validate the numerical method and compare it with its existing laboratory results. As you can see from the results, the distance between the nozzle and the motor has a very small effect on the cooling flow. In fact, this shows that with the changes in axial distance in the mentioned range (between 0 and 2.5 cm), the amount of suction caused by the hot jet of the hot nozzle output of the nozzle has a very small effect on the cooling flow. To check the suction rate of the nozzle output jet on the cooling flow rate, the problem for different discharge nozzles is numerically analyzed to see how much the effect of the nozzle output fluid on the cooling fluid discharge flow is. The coolant flow of the Flow rate engine nozzle does not change much. This factor indicates that the flow rate of the engine coolant flow is mostly due to the pressure of the coolant itself and does not depend on the suction jet of the nozzle output. In this section, the effect of increasing the length of the engine shell on the cooling rate of the engine cooling is discussed. In this analysis, the shell length was increased by 6.5 cm. The increase in shell length is done with a constant diameter. As the shell length increased, the cooling flow rate increased significantly. As the shell length increases, the cooling flow rate increases by about 52% at the relative inlet pressure of 15,000 Pascals. Keywords: nozzle, engine shell, Flow rate suction, cooling.

Keywords

[1] M. Ahmadi and F.A. Khosravi, CFD simulation of non-Newtonian two-phase fluid flow through a channel with
a cavity, Thermal Sci. 24(2B) (2020) 1045–1054.
[2] M. Ahmadi, S.A.A. Mirjalily and S.A.A. Oloomi, RANS K − ω simulation of 2d turbulent natural convection in
an enclosure with heating sources, IIUM Engin. J. 20(1) (2019) 229–244.
[3] A.R. AlAli and I. Janajreh, Numerical simulation of turbine blade cooling via jet impingement, Energy Procedia
75 (2015) 3220–3229.
[4] M. Alhajeri and H. Alhajeri, Heat and fluid flow analysis in gas turbine blade cooling passages with semicircular
turbulators, Int. J. Phys. 4 (2009) 835–845.
[5] A.A. Amell and F.J. Cadavid, Influence of the relative humidity on the air cooling thermal load in gas turbine
power plant, Appl. Thermal Eng. 22(13) (2002) 1533–1529.
[6] F. Bazdidi-Tehrani and A. Mahmoodi, Investigation of the effect of turbulence intensity and injection angle on
the flow and temperature field in the single hole film cooling technique, Int. J. Eng. Sci. 4(12) (2002) 25–38.
[7] S.H. Bhavnani and A.E. Bergles, Interferometric Study of Laminar Natural Convection from An Isothermal
Vertical Plate with Transverse Roughness Elements, PHD Dissertation, Iowa State University, Iowa, 1987.
[8] M. Choi, H.S. Yoo, G. Yang, J.S. Lee and D.K. Sohn, Measurements of impinging jet flow and heat transfer on
a semi-circular concave surface, Int. J. Heat Mass Transfer 43(10) (2000) 1822–1811.[9] J. Cleeton, R. Kavanagh and G. Parks, Blade cooling optimisation in humid-air and steam-injected gas turbines,
Appl. Thermal Eng. 29(16) (2009) 3283–3274.
[10] M. Colins, S.J. Harrison, D. Naylor and P.H. Oosthuizen, Heat transfer from an isothermal vertical surface with
adjacent heated horizontal louvers: Numerical analysis, J. Heat Transfer 124 (2002) 1072–1077.
[11] C. Du, L. Li, X. Wu and Z. Feng, Effect of jet nozzle geometry on flow and heat transfer performance of vortex
cooling for gas turbine blade leading edge, Appl. Thermal Eng. 48(7) (2015).
[12] A. Ghobadi, M. Javadi and B. Rahimi, Cooling turbine blades using exciting boundary layer, World Academy Sci.
Technol. 62 (2010).
[13] W. Haas, W. Rodi and B. Schonung, The influence of density difference between hot and coolant gas on film
cooling by a row of holes: Prediction and experiments, ASME J. Turbo Machin. 114 (1992) 755–747.
[14] J. Horlock, D. Watson and T. Jones, Limitations on gas turbine performance imposed by large turbine cooling
flows, J. Eng. Gas Turb. Power 123(3) (2001) 494–487.
[15] K.M. Kim, J.S. Park, D.H. Lee, T.W. Lee and H.H. Cho, Analysis of conjugated heat transfer, stress and failure
in a gas turbine blade with circular cooling passages, Engin. Failure Anal. 18(4) (2011) 1212–1222.
[16] C. Langowsky and D.T. Vogel, Influence of film cooling on the secondary flow in a turbine nozzle, AIAA 35(1)
(1997).
[17] S.-J. Li, J. Lee, J.-C. Han, L. Zhang and H.-K. Moon, Influence of mainstream turbulence on turbine blade
platform cooling from simulated swirl purge flow, Appl. Thermal Eng. 101 (2016) 678–685.
[18] Z. Liu and Z. Feng, Numerical simulation on the effect of jet nozzle position on impingement cooling of gas turbine
blade leading edge, Int. J. Heat Mass Transfer 54(23–24) (2011) 4959–4949.
[19] Y. Liu, L. Wang and Z.S. Qian, Numerical investigation on the assistant restarting method of variable geometry
for high Mach number inlet, Aerosp. Sci. Technol. 79 (2018) 647–657.
[20] Z. Liu, L. Ye, C. Wang and Z. Feng, Numerical simulation on impingement and film composite cooling of blade
leading edge model for gas turbine, Appl. Thermal Eng. 73(2) (2014) 1432–1443.
[21] W. MacCormack, O.R. Tutty and E. Rogers, Stochastic optimization based control of boundary layer transition,
Control Engin. Practice 10 (2002) 260–243.
[22] K. Mazaheri, M. Zeinalpour and H.R. Bokaei, Turbine blade cooling passages optimization using reduced conjugate
heat transfer methodology, Appl. Thermal Eng. 103 (2016) 1228–1236.
[23] A.B. Moskalenkoa and A.I. Kozhevnikova, Estimation of gas turbine blades cooling efficiency, Int. Conf. Industrial
Engin. ICIE, (2016).
[24] R. Roy, A. Tiwari and J. Corbett, Designing a turbine blades cooling system using a generalize regression genetic
algorithm, CIRP Ann. 52(1) (2003) 415–418.
[25] H. Sun, S. Bu, Y. Luan, T. Sun and X. Pei, Numerical research on the film cooling gas turbine blade with the
conjugate heat transfer method, Materials Res. Innov. 19(6) (2015) 180–175.
[26] L. Torbidoni and A.F. Massardo, Analytical blade row cooling model for innovative gas turbine cycle evaluations
supported by semi-empirical air cooled blade data, Proc. ASME Turbo Expo Amsterdam, Netherlands, (2002).
[27] K. Yu, J. Xu, Z. Lv and G. Song, Inverse design methodology on a single expansion ramp nozzle for scramjets,
Aerosp. Sci. Technol. 92 (2019) 9–19.
Volume 13, Issue 1
March 2022
Pages 2233-2243
  • Receive Date: 17 October 2021
  • Revise Date: 11 November 2021
  • Accept Date: 01 December 2021
  • First Publish Date: 07 December 2021