Abstract
Gas turbine engines are highly intricate machines, and every component of them is closely associated with one another. In the traditional engine developing process, vast experiment tests are needed. To reduce unnecessary trials, a whole gas turbine engine simulation is extremely needed. For this purpose, a compressor simulation tool is now developed. Considering the inherent drawbacks of 0D analysis and 3D CFD (Computational Fluid Dynamics) calculation, the 2D throughflow method is an indispensable tool. Based on the circumferential average method (CAM), 3D Navier–Stokes is transformed into a 2D method. One phenomenon arising is that the lack of description about circumferential motion leads to the need for the blade force modeling in compressor simulation. Previous models are based on the assumption that flow passes through the average stream surface without entropy increasing, which is not applicable in the CAM. An improved model is proposed based on the result analysis from CAM and NUMECA method in a linear cascade. Whereafter, the model is applied in a highly loaded and low-speed fan, which has been tested for its performance characteristics. Utilizing the new model, the error of the adiabatic efficiency between CAM and experiment decreases from 4.0% to 1.0% and the accuracy of the mass flow, and pressure ratio remains unchanged. The time involved in the CAM simulation is nearly 70 times faster than that of the 3D simulation.
Highlights
When a new gas turbine engine is under development, abundant hardware builds are necessary to measure the performance characteristics, which are much too expensive [1]
The throughflow method (2D) is still a significant part of its performance prediction and rapid flow field acquisition [9]. To achieve this ultimate goal of the whole gas turbine engine simulation, the throughflow method applied in compressors is first explored in this paper
This paper focuses on two parts of the circumferential average method (CAM) derived from the Navier–Stokes (N-S)
Summary
The simulation of an overall gas turbine engine is extremely needed. Thanks to both the advance of the CFD (Computational Fluid Dynamics) and the increasingly developed computer technology, fully three-dimensional (3D) computation is increasingly involved [2,3]. The throughflow method (2D) is still a significant part of its performance prediction and rapid flow field acquisition [9]. To achieve this ultimate goal of the whole gas turbine engine simulation, the throughflow method applied in compressors is first explored in this paper
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
