Commenced in January 2007
Frequency: Monthly
Edition: International
Paper Count: 31231
##### Improvement of Parallel Compressor Model in Dealing Outlet Unequal Pressure Distribution

Abstract:

Parallel Compressor Model (PCM) is a simplified approach to predict compressor performance with inlet distortions. In PCM calculation, it is assumed that the sub-compressors’ outlet static pressure is uniform and therefore simplifies PCM calculation procedure. However, if the compressor’s outlet duct is not long and straight, such assumption frequently induces error ranging from 10% to 15%. This paper provides a revised calculation method of PCM that can correct the error. The revised method employs energy equation, momentum equation and continuity equation to acquire needed parameters and replace the equal static pressure assumption. Based on the revised method, PCM is applied on two compression system with different blades types. The predictions of their performance in non-uniform inlet conditions are yielded through the revised calculation method and are employed to evaluate the method’s efficiency. Validating the results by experimental data, it is found that although little deviation occurs, calculated result agrees well with experiment data whose error ranges from 0.1% to 3%. Therefore, this proves the revised calculation method of PCM possesses great advantages in predicting the performance of the distorted compressor with limited exhaust duct.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1111717

References:

[1] H Pearson and AB McKenzie. Wakes in axial compressors. Journal of the Royal Aeronautical Society, 63(583):415–416, 1959.
[2] Milt W Davis and William T Cousins. Evaluating complex inlet distortion with a parallel compressor model: Part 2—applications to complex patterns, ASME 2011Turbo Expo: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2011.
[3] James A Korn. Compressor distortion estimates using parallel compressor theory and stall delay. Journal of Aircraft, 11(9):584–586, 1974.
[4] William F Kimzey. An analysis of the influence of some external disturbances on the aerodynamic stability of turbine engine axial flow fans and compressors. Technical report, DTIC Document, 1977.
[5] Robert S Mazzawy. Multiple segment parallel compressor model for circumferential flow distortion. Journal of Engineering for Gas Turbines and Power, 99(2):288, 1977.
[6] C Reid. The response of axial flow compressors to intake flow distortion. In ASME 1969 Gas Turbine Conference and Products Show. American Society of Mechanical Engineers, V001T01A029, 1969.
[7] Angélique Angélique Pascale Plas. Performance of a boundary layer ingesting propulsion system. PhD thesis, Massachusetts Institute of Technology, BSN, USA, 2006
[8] Mengqi Wang. The study of criterion on influence factors on the surge and stall of the engine. PhD thesis, Beihang University, (Beijing China 2011).
[9] Qiuyuan Huang. Research on Inlet Distortion’s effect on Aero-engine Using Parallel Compressor Model. PhD thesis, Nanjing University of Aeronautics and Astronautics, Nanjing China 2010.
[10] Holger Krasmann. Einfluss von nichtrotationssymmetrischen Einlaufstörungen auf das Betriebsverhalten von hochbelasteten Axialventilatoren. Faragallah, Germany 1996.
[11] Jörg Rösener. Untersuchungen zur Auslegung von hochbelasteten Axialventilatoren mit radial ungleichmässiger Energieübertragung. PhD thesis, Germany 1996.