scholarly journals FSI of a Simplified Aero Engine Compressor Cascade Configuration

PAMM ◽  
2006 ◽  
Vol 6 (1) ◽  
pp. 457-458 ◽  
Author(s):  
Sven Schrape ◽  
Arnold Kühhorn ◽  
Mark Golze
Keyword(s):  
Compressor Cascade ◽  
Aero Engine ◽  
Engine Compressor

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.

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

Numerical Analysis of Particle Deposition in an Aircraft Engine Compressor Cascade

2020 ◽  
Author(s):  
Nicola Casari ◽  
Johannes Altmeppen ◽  
Christian Koch ◽  
Michele Pinelli ◽  
Stephan Staudacher ◽  
...  
Keyword(s):  
Numerical Analysis ◽  
Gas Turbines ◽  
Particle Deposition ◽  
Aircraft Engine ◽  
Compressor Cascade ◽  
Test Rig ◽  
Advantages And Disadvantages ◽  
Performance Reduction ◽  
Engine Compressor ◽  
Wall Interaction

Abstract Solid particles dispersed in the air represent a real hazard for gas turbines in both heavy-duty and aero-propulsion applications. Particles impacting the inner surfaces of the machine can stick to such surfaces or erode them. The geometry modifications related to such occurrences entail aerodynamic surface degradation. As the severity of the problem increases, the performance reduction can increase, demanding engine shut-down and off-line washing or refurbishing. Numerical modeling is one of the techniques employed for understanding and predicting the particle deposition problem. Multiple numerical studies investigated the influences of these phenomena. However, the basic challenge of modeling the particle wall-interaction with sufficient accuracy remains. In this work, a cascade exposed to a particle-laden flow is numerically investigated. The numerical analysis is devoted to investigate a test rig designed to be representative of aircraft engine compressor blading and exposed to an accelerated deposition process. Firstly, the relation between flow structures and particle trajectory is investigated. Then, a computational analysis is carried out considering different particle-wall interaction models of varying complexity levels (e.g. pure adhesion, presence of humidity or the influence of surface roughness) in order to identify advantages and disadvantages of each model and their ability to include different phenomena. The results are discussed by taking into account measurement data from a cascade test rig. The deviation between experimental data and the investigated model is evaluated, showing the increasing reliability that derives from successive model refinement. This work is proposed to be a test case for the numerical analyses of compressor fouling applications and a first step towards a general physical based particle-wall interaction model.

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