Unsteady performance and thermodynamic analysis of aero‐engine compressor at different water ingestion conditions

2020 ◽  
Vol 44 (8) ◽  
pp. 6567-6582
Author(s):  
Lu Yang ◽  
Qun Zheng ◽  
Aqiang Lin ◽  
Mingcong Luo
Keyword(s):  
Thermodynamic Analysis ◽  
Water Ingestion ◽  
Aero Engine ◽  
Engine Compressor ◽  
Unsteady Performance

Evaluation on the performance fluctuation after water ingestion for a turbofan engine compressor during flight descent

2020 ◽  
pp. 095441002097798
Author(s):  
Lu Yang ◽  
Qun Zheng ◽  
Aqiang Lin
Keyword(s):  
Droplet Diameter ◽  
Pressure Ratio ◽  
Critical Role ◽  
Water Film ◽  
Heavy Rain ◽  
Diameter Distribution ◽  
Turbofan Engine ◽  
Water Ingestion ◽  
The Core ◽  
Engine Compressor

Turbofan engine compressor is most severely threatened by the entry of liquid water during flight descent. This study aims to deeply understand the fluctuations of compressor performance parameters caused by water ingestion through frequency spectrum analysis. The water content and droplet diameter distribution are determined based on the real heavy rain environment. Results reveal that most of the droplets actually entering the core compressor have a particle size of less than 100 μm. In addition, the formation and motion of water film plays a critical role in affecting the fluctuation characteristics. Water ingestion deteriorates the compression performance and aggravates the unsteady fluctuations of the fan. However, the performance of the core compressor is less affected by water ingestion, but their fluctuations are still exacerbated. For some important parameters, such as inlet mass flow rate, total pressure ratio, total temperature ratio, compression work and efficiency, their main frequency of fluctuation are switched from the original blade passing frequency to the rotor passing frequency, and their amplitudes are correspondingly amplified to varying degrees. These phenomena can be observed in both the fluctuations of the fan and core compressor. Moreover, the operating point of them will be in the long-period and large-amplitude fluctuations, which leads them experiences the non-optimal state for a long time and threatens their operating stability.

Oxidation-Resistance of (Ti,Al,Cr,Y)N Coatings Prepared by Arc Ion Plating

2010 ◽  
Vol 177 ◽  
pp. 338-341
Author(s):  
Ming Sheng Li ◽  
Yong Zhong Fan ◽  
Shu Juan Zhang
Keyword(s):  
Oxidation Resistance ◽  
Crystal Size ◽  
Substrate Bias ◽  
Compressor Blades ◽  
Arc Ion Plating ◽  
Ion Plating ◽  
Cr Content ◽  
Heat Treated ◽  
Aero Engine ◽  
Engine Compressor

In this study, composite metastable (Ti0.49Al0.49Y0.02)N, (Ti0.44Al0.44Cr0.1Y0.02)N and (Ti0.34Al0.34Cr0.3Y0.02)N coatings were respectively deposited on a wrought martensite steel 1Cr11Ni2W2MoV for aero-engine compressor blades by arc ion plating technique with a pulse substrate bias. All the coatings have B1NaCl phase structure with a (220) preferred orientation and dense structures. The introduction of chromium into the coatings gave rise to a minute shrinkage of crystal lattice and a decrease of crystal size. Annealed at 800°C, Oxidation-resistance of the coatings improved with increased Cr content. But heat-treated at 900°C, the incorporation of Cr gave rise to obvious decrease of oxidation-resistance.

scholarly journals Preliminary Optimization of Multi-Stage Axial-Flow Industrial Process Compressors Using Aero-Engine Compressor Design Strategy

2021 ◽  
Vol 11 (19) ◽  
pp. 9248
Author(s):  
Fan Lei ◽  
Chuhua Zhang
Keyword(s):  
Optimal Design ◽  
Gas Turbines ◽  
Design Method ◽  
Industrial Process ◽  
Design Strategy ◽  
Preliminary Design ◽  
Stage Design ◽  
Compressor Design ◽  
Aero Engine ◽  
Engine Compressor

Aero-engine core compressor preliminary design strategy has been successfully applied to the advanced design of gas turbines compressors. However, few researchers have addressed the application of the aero-engine core compressor preliminary design strategy in the preliminary optimal design of industrial process compressors. Here we embedded the aero-engine core compressor preliminary design strategy into a preliminary optimal design method, in which six types of design parameters widely used to define the aero-engine compressor configuration, i.e., aspect ratio, solidity, reaction, rotation speed, outlet axial Mach number, and inlet radius ratio, were used as the design variables. The 4-stage, 5-stage, 6-stage, and 7-stage compressor configuration with the same overall design requirements for a large-scale air separation main compressor were preliminarily optimized by the developed method, in which the 4-stage design has a stage pressure rise level of current aero-engine core compressors, whereas the 7-stage design has that of current industrial process compressors. The optimized compressor configurations were then refined with the throughflow-based detailed design method and finally verified with computational fluid dynamic simulations. It is found that the developed method can optimize design efficiency and accurately predict aerodynamic performance of compressors in a few minutes. Several design guidelines for the advanced industrial process compressors were also identified. This work is of significance in extending aero-engine core compressor design strategy to the design of advanced industrial process compressors.

Thermodynamic Analysis of Flow Field at the End of Combustor Simulator

2012 ◽  
Vol 225 ◽  
pp. 261-266 ◽  
Author(s):  
Kianpour Ehsan ◽  
Nor Azwadi Che Sidik ◽  
Mohsen Agha Seyyed Mirza Bozorg
Keyword(s):  
Flow Field ◽  
Penetration Depth ◽  
Thermodynamic Analysis ◽  
Film Cooling ◽  
Thermal Field ◽  
Three Dimensional ◽  
Leading Edge ◽  
Aero Engine ◽  
Three Dimensional Presentation

This study was carried out to investigate the effects of different cooling holes configurations on the thermal field characteristics inside a combustor simulator. In this research, a three-dimensional presentation of a true Pratt and Whitney aero-engine was simulated and analyzed. This combustor simulator combined the interaction of two rows of dilution jets, which were staggered in the stream wise direction and aligned in the span wise direction. The findings of the study indicate that the thickness of the film-cooling layer was thicker for the greater penetration depth. Furthermore, for the combustor simulator with more cooling holes, the temperature near the wall and between the jets was slightly increased. Also at the leading edge of the jet, the gradients of temperature were quite high at the jet-mainstream interface.

Experimental and Analytical Surge Cycle Analysis of a High Pressure Aero Engine Compressor

2012 ◽  
Author(s):  
Phillip Waniczek ◽  
Harald Schoenenborn ◽  
Peter Jeschke
Keyword(s):  
Flow Field ◽  
Reverse Flow ◽  
Flow Direction ◽  
Specific Work ◽  
Rotor Speed ◽  
Suction Surface ◽  
Trailing Edge ◽  
Wide Range ◽  
Aero Engine ◽  
Engine Compressor

The unsteady flow field during surge of the front rotor of an eight-stage axial aero engine compressor has been investigated experimentally and analytically. For that purpose, two newly designed multi-sensor probes are installed up- and downstream of the first rotor. Surge experiments are conducted at four different speed lines (75–93% speed) covering a wide range of the compressor map and measurements have been taken at two different channel heights (50% and 70% span). The results show that the flow field varies extremely during surge up- and downstream of the rotor. In contrast to the flow at the rotor leading edge, which is nearly independent of the rotor speed, the flow at the rotor trailing edge is highly dependent of the rotor speed. Therefore, the performance of the rotor during surge is dependent on the reverse through-flow of the stators. At low speeds the flow passes the stators without any changes in the flow direction. If speed is increased the reverse flow is guided more and more by the stators. These different flow conditions have a direct impact on the process of energy conversion of the rotor during the surge event. The incoming reverse flow at the rotor trailing edge impinges on the blade from the suction surface side at lower speeds and turns to the pressure surface side when speed is increased. Hence, the deviation and specific work grow. In addition to the surge experiments simulations of the surge events are conducted with a 1D code called SYSQ3D. The simulations and experiments match well and underline the capability of the new multi-sensor probes to accurately measure the flow patterns during surge.

Reliability Analysis of Aero-Engine Compressor Rotor System Considering Cruise Characteristics

2020 ◽  
Vol 69 (1) ◽  
pp. 245-259 ◽  
Author(s):  
Bingfeng Zhao ◽  
Liyang Xie ◽  
Haiyang Li ◽  
Shijian Zhang ◽  
Bowen Wang ◽  
...  
Keyword(s):  
Reliability Analysis ◽  
Rotor System ◽  
Compressor Rotor ◽  
Aero Engine ◽  
Engine Compressor

Analysis on nonlinear dynamics of the aero-engine compressor blade

2013 ◽  
Vol 43 (4) ◽  
pp. 345-362 ◽  
Author(s):  
Wei ZHANG ◽  
XiangYing GUO ◽  
ZhiQing FENG
Keyword(s):  
Nonlinear Dynamics ◽  
Compressor Blade ◽  
Aero Engine ◽  
Engine Compressor
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