Investigations on static aeroelastic problems of transonic fans based on fluid

Abstract

Fan blades of high bypass ratio gas turbine engines are subject to substantial aerodynamic and centrifugal loads, producing the well-known phenomenon of blade untwist. Accurate fan blade shape prediction is very crucial for high-performance aero-engine. In order to investigate the effects of static aeroelastic deflections on aerodynamic performances, a time domain two-way fluid–structure interaction method was applied to simulate the deflection of NASA Rotor 67 fan blades under different operating conditions. This paper pays attention to the deviation of fan profile and aerodynamic performance due to the varying aerodynamic loads, especially for off-design conditions. The results show that the static aeroelastic deflection has a 1.8% impact on the total pressure ratio under near stall condition, and a 1.7% impact on the choke mass flow rate, relative to the cold configuration. Thus, the blade design in industrial practice should adopt a two-way fluid–structure interaction method to consider the influence of static aeroelastic problems on aerodynamic performance.

Keywords

Transonic compressor blade deformation two-way fluid–structure interaction aerodynamic performance

Get full access to this article

View all access options for this article.

References

Chen

Liu

. Fan/compressor aero design trend and challenge on the development of high bypass ratio turbofan. J Aerosp Power 2008; 23: 961–975.

Dhopade P, Neely AJ, Young J, et al. High-cycle fatigue of fan blades accounting for fluid-structure interaction. In: ASME turbo expo 2012: Turbine technical conference and exposition, Copenhagen, Denmark, 2012, pp.1365–1372.

Hong

Zhang

Hong

. Prediction on high cycle life of blades using probability method. J Propul Technol 2009; 30: 462–467.

Mahajan AJ and Stefko GL. An iterative multidisciplinary analysis for rotor blade shape determination. In: AIAA 29th joint propulsion conference and exhibit, AIAA 93-2085, Monterey, CA, USA, June 1993.

Wilson

Imregun

Sayma

. The effect of stagger variability in gas turbine fan assemblies. J Turbomach 2007; 129: 404–411.

Zheng

Wang

Yang

. Static aeroelastic problems of transonic fan blades. J Aerosp Power 2013; 28: 2475–2482.

Song

. Numerical investigations on aerodynamic and mechanical performance of long blade based on two-way fluid-structure coupling approach. J Propul Technol 2014; 35: 202–207.

Kallesøe BS and Hansen MH. Some effects of large blade deflections on aeroelastic stability. In: AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition, Orlando, FL, USA, 2007, pp.5–8.

Kallesøe

. Equations of motion for a rotor blade, including gravity, pitch action and rotor speed variations. Wind Energy 2007; 10: 209–230.

10.

Doi H and Alonso JJ. Fluid/structure coupled aeroelastic computations for transonic flows in turbomachinery. In: ASME turbo expo 2002: Power for land, sea, and air, Amsterdam, Netherlands, 2002, pp.787–794.

11.

Yang H and Zheng Y. A fluid-structure coupling method for rotor blade un-running design. In: ASME turbo expo 2013: Turbine technical conference and exposition, San Antonio, TX, USA, June 2013.

12.

Zheng

Wang

Yang

. Numerical study on blade un-running design of a transonic fan. J Mech Eng 2013; 49: 147–153.

13.

Strazisar AJ, Wood JR, Hathaway MD, et al. Laser anemometer measurements in a transonic axial-flow fan rotor. NASA Technical Paper, vol. 2879, 1989.

14.

Zheng RY, Xiang JH and Sun JT. Blade geometry optimization for axial flow compressor. In: ASME turbo expo 2010: Power for land, sea, and air, Glasgow, UK, June 2010, pp.633–644.

15.

Sadeghi M and Liu F. Coupled fluid-structure simulation for turbomachinery blade rows. In: 43rd AIAA aerospace sciences meeting and exhibit, vol. 18, Reno, NV, USA, January 2005.

16.

Castaneda J, Ahad M, Cugno D, et al. A preliminary numerical CFD analysis of transonic compressor rotors when subjected to inlet swirl distortion. In: Proceedings of ASME turbo expo, Vancouver, BC, Canada, June 2011, pp.417–429.

17.

Liu

Zou

Yan

. Present status and future development of CFD in turboma- chinery. Acta Aeronaut Astronaut Sin 2002; 23: 394–404.

18.

Fan

Tang

Zhang

. Failure analysis of third-stage rotor blade of high-pressure compressor in aero-engine. Fail Anal Prev 2014; 9: 110–114.

19.

Strazisar

. Investigation of flow phenomena in a transonic fan rotor using laser anemometry. J Eng Gas Turbines Power 1985; 107: 427–435.

20.

Razavi

Boroomand

. Numerical and performance analysis of one row transonic rotor with sweep and lean angle. J Therm Sci 2014; 23: 438–445.

21.

Du J, Lin F, Zhang HW, et al. Numerical investigation on the originating mechanism of unsteadiness in tip leakage flow for a transonic fan rotor. In: ASME turbo expo 2008: Power for land, sea, and air, Berlin, Germany, June 2008, pp.707–717.

Investigations on static aeroelastic problems of transonic fans based on fluid–structure interaction method

Abstract

Keywords

Get full access to this article

References