###### Abstract  
Compressor characteristic evaluation is a critical step in design and optimization. Corrected characteristic curves are typically derived via experimental testing or CFD computation which is typically executed through manual manipulation. For compressors necessitating extensive characteristic computation across multiple speeds and operational conditions, the involved process is inherently complex. This paper introduces an automation approach, employing dichotomy and optimization algorithms aligned with a 3D numerical solver, to streamline the derivation of compressor characteristic curves. Initially, the paper delineated the procedural frameworks for two methodologies and validated them using a single-stage transonic compressor. Both methods achieved the automated resolution of the characteristic lines. The result indicates that the volume of the iterative computations hinges on the granularity of the space searching step and the precision in identifying the stall boundary point. Pertaining to the subject investigated herein, the dichotomy method entailed fewer iterations relative to the optimization algorithm. Subsequent adjustments to the optimization algorithmic process revealed that direct optimization mitigated computational demands substantially by reducing a cycle, thereby attesting to its superior efficacy. In summary, when simulating compressor characteristic curves, the dichotomy method proves more efficient when the interval value of the stall boundary range can be approximated. Conversely, direct optimization is preferable when the estimation of the compressor's stall boundary is imprecise. The proposed methodologies contribute to compressor research and expedite the progression of compressor development and performance advancement. compressor performance characteristics; automated process; numerical simulation; dichotomy method; optimization algorithm +
Footnote †: journal: Applied  
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Footnote †: journal: Applied  
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Footnote 1: email: [EMAIL_ADDRESS]  
Footnote †: journal: Applied  
1
Footnote 1: email: xqfan@nudt. effects of the widest circumferential position of the blade tip winglet on the characteristics of high-load compressor stages. They approached the stall point by gradually increasing the exit static pressure, with an increment of 10 Pa near stall conditions [2]. [PERSON] et al. conducted an analysis and improved the design of a FLADE rotor with a tip ring by progressively adjusting the outlet average pressure to obtain fan characteristics at design speed. The back pressure increase step was 500 Pa as they moved closer to the stall boundary [3]. Apart from setting an average pressure at the outlet mentioned above, boundary conditions can also be stipulated through alternative ways. In investigating the characteristics of transonic compressors with total temperature distortion, [PERSON] et al. placed a nozzle at the exit with a fixed back pressure of 30 kPa. Varying nozzle throat dimensions allowed for the gain of different operational characteristics [4]. Substantial studies [5; 6; 7; 8] have shown that such a boundary setting fosters computational stability at lower flow conditions in compressors. Furthermore, [PERSON] et al. investigated the impact of rotor-stator spacing on compressor performance across various conditions, specifying the outlet boundary as the radial profile of averaged static pressure in accordance with stable findings [9]. Moreover, [PERSON] et al. [10] examined the pipelines of two-stage centrifugal compressors, obtaining the characteristic curves by outlining the exit flow rates. This method is widely applied in the numerical simulation of centrifugal compressors with small flow rates, and [PERSON] et al. [11] also adopted the same approach in their study. Additionally, a throttle valve model can be created at the exit to simulate the experimental choking process. [PERSON] et al. [12] and [PERSON] et al. [13] applied this method in their recent research. Distinctively, [PERSON] et al.