Abstract
The target of this paper is to develop an enhanced flow-thermo-structural (FTS) model with high computational accuracy, to perform the integrated analysis of film cooling nozzle guide vane (NGV). An efficient turbulence model and weak spring approach are utilized in the enhanced FTS model. In respect of the power balance principle of aeroengine rotor shaft and temperature test of a typical combustor, the mean temperature inlet and five normalization temperature curves were confirmed, respectively. The temperature-sensitive paint (TSP) technology was used to verify the numerical simulation. From this study, we find that the predicted temperature caters for the TSP test well, between which the maximum error is less than 6%, and the maximum thermal stress is 758 MPa around the hole edges and the location of stress concentration keeps the consistency with that of the cracks. The maximum thermal stress increases by 10% with the increasing inlet temperature and reduces by about 16% with the shifting of flame peak from the outer to inner hub. The prediction provides general information on the initiation of cracks on a vane segment. The developed enhanced FTS model is validated to be workable and precise in the integrated analysis of film cooling NGV. The efforts of this study provide an integrated analysis approach of film cooling NGV and are promising to provide guidance for the integrated design of film cooling components besides NGV.
Highlights
With the development of aeronautical technology, turbine inlet temperature reaches to 2000 K which exceeds the melting point of high-temperature metal materials
With the development of conjugate heat transfer (CHT) technology, the aerodynamic heat transfer of nozzle guide vane (NGV) is attracting the attention of numerous researchers
The comparison results of midspan pressure and heat transfer coefficient (HTC) are shown in Figures 6 and 7, where q is comparison wall heat flux; Taw isof wall temperature; Tsp isand mean temperature at gas
Summary
With the development of aeronautical technology, turbine inlet temperature reaches to 2000 K which exceeds the melting point of high-temperature metal materials. Based on FTS coupling technology, the influence of non-uniform temperature field on thermal strength performance of NGV was widely researched [11,12], and some studies about NGV life prediction emerged. Kim et al studied convective heat transfer coefficients and stresses on blade surfaces using finite volume (FV) and finite element (FE) methods [13], showed the maximum material temperature and thermal stress at the trailing edge near the mid-span, and discussed the life prediction methods of turbine components by coupling aero-thermal simulation with a nonlinear deformation thermal-structural FE model and a slip-based constitutive model [14]. This paper attempts to develop an enhanced flow-thermo-structural model to improve the integrated analysis of film cooling NGV in computing accuracy, by regarding non-uniform inlet temperature.
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