Log in

Relevant bibliographies by topics / Aircraft Engine Compressor Blade / Journal articles

To see the other types of publications on this topic, follow the link: Aircraft Engine Compressor Blade.

Journal articles on the topic 'Aircraft Engine Compressor Blade'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 journal articles for your research on the topic 'Aircraft Engine Compressor Blade.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

1

Gilge, Philipp, Andreas Kellersmann, Jens Friedrichs, and Jörg R. Seume. "Surface roughness of real operationally used compressor blade and blisk." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 14 (2019): 5321–30. http://dx.doi.org/10.1177/0954410019843438.

Full text

Abstract:

Deterioration of axial compressors is in general a major concern in aircraft engine maintenance. Among other effects, roughness in high-pressure compressor reduces the pressure rise and thus efficiency, thereby increasing the specific fuel consumption of an engine. Therefore, it is important to improve the understanding of roughness on compressor blading and their impact on compressor performance. To investigate the surface roughness of rotor blades of a compressors, different stages of an axial high-pressure compressor and a first-stage blisk (BLade–Integrated–dISK) of a regional aircraft eng

APA, Harvard, Vancouver, ISO, and other styles

2

Potapov, V. A., and A. A. Sanko. "Performance simulation of multi-stage axial-flow compressor of turbo-shaft engine with account for erosive wear nonlinearity of its blades." Civil Aviation High Technologies 23, no. 5 (2020): 39–53. http://dx.doi.org/10.26467/2079-0619-2020-23-5-39-53.

Full text

Abstract:

The construction and useful practice of gas-turbine engine diagnosis systems depend largely on the availability of the engine mathematical models and its certain components in their structure. Utilization of multi-stage axial flow compressor performance with account for erosive wear of its parts during the operation fundamentally raises possibilities of such systems as erosive wear of flow channel, blade rings of impellers and vane rings of multi-stage compressor is a common cause of preschedule gas-turbine engine detaching from an aircraft. As evidenced by various contributions presented in t

APA, Harvard, Vancouver, ISO, and other styles

3

ILIE, Marcel, and Augustin SEMENESCU. "AERODYNAMIC STUDIES OF AIRCRAFT ENGINE TURBINE STAGE." ANNALS OF THE ACADEMY OF ROMANIAN SCIENTISTS Series on ENGINEERING SCIENCES 14, no. 2 (2022): 5–18. http://dx.doi.org/10.56082/annalsarscieng.2022.2.5.

Full text

Abstract:

The present research concerns the aerodynamic computational studies of stator-rotor turbine stage. The computational studies are carried out using the large-eddy simulation approach. In the aircraft engine compressor/turbine stage blade-vortex interactions occur. The present study aims at the understanding the blade-vortex interaction mechanism and its impact on the aerodynamics of rotor-stator compressor/turbine stages. The computational studies are carried out in a rotating frame of reference, for high-Reynolds number flow, Re = 1.3x105. The analysis reveals that the blade-vortex interaction

APA, Harvard, Vancouver, ISO, and other styles

4

Obrocki, Wojciech, Amadeusz Setkowicz, Maciej Masłyk, and Jan Sieniawski. "Influence of aircraft engine compressor blades leading edge damage on their fatigue strength." Mechanik 91, no. 3 (2018): 205–9. http://dx.doi.org/10.17814/mechanik.2018.3.35.

Full text

Abstract:

Article presents the research results of aircraft compressor blade damage length and its position influence on fatigue strength under high number cycles conditions. The criteria for blade damage detection classification and test research methodology were developed. Designed and tested the instrumentation for compressor blades fatigue tests. Fluorescent method was used to determine the source of fatigue cracking initiation and its propagation direction during fatigue test.

APA, Harvard, Vancouver, ISO, and other styles

5

Kvasha, Yu A., and N. A. Zinevych. "Aerodynamic improvement of an aircraft gas-turbine engine fan." Technical mechanics 2021, no. 3 (2021): 23–29. http://dx.doi.org/10.15407/itm2021.03.023.

Full text

Abstract:

This work is concerned with the development of approaches to the aerodynamic improvement of axial-flow compressors for gas-turbine engines. The aim of this work is the aerodynamic improvement of an aircraft gas-turbine engine two-stage fan by numerical simulation of 3D turbulent gas flows. The approach used in this study features: varying the spatial shape of the fan blades for the first- and the second-stage impeller by varying the profile angle along the blade height; formulating quality criteria as the mean integral values of the power characteristics of each impeller of the fan over the op

APA, Harvard, Vancouver, ISO, and other styles

6

Lee, Bok-Won, Jungjun Suh, Hongchul Lee, and Tae-gu Kim. "Investigations on fretting fatigue in aircraft engine compressor blade." Engineering Failure Analysis 18, no. 7 (2011): 1900–1908. http://dx.doi.org/10.1016/j.engfailanal.2011.07.021.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Ngoret, Joshua Kimtai, and Venkata Parasuram Kommula. "Comprehending Occurrence of Premature Failure in Compressor Turbine (CT) Blades for Short-Haul Aircraft Fleet." International Journal of Engineering Research in Africa 42 (April 2019): 10–23. http://dx.doi.org/10.4028/www.scientific.net/jera.42.10.

Full text

Abstract:

This paper presents results from modeling of Compressor Turbine (CT) blades for short-haul aircraft fleet occasioned by thermo-mechanical stresses in order to comprehend the occurrence of premature failure. A 3D PT6A-114A engine high pressure (HP) CT blade geometrical model was developed in commercial CAD-SolidWorks, then imported to ANSYS 15.0 environment for finite element analysis (FEA). The CT blade was investigated for transient thermal stresses from heat generated by the combustors and static structural stresses from rotational velocities of the engine which account for 80% of inertial f

APA, Harvard, Vancouver, ISO, and other styles

8

Boyko, Ludmila, Vadym Datsenko, Aleksandr Dyomin, and Nataliya Pizhankova. "Devising a method for calculating the turboshaft gas turbine engine performance involving a blade-by-blade description of the multi-stage compressor in a two-dimensional setting." Eastern-European Journal of Enterprise Technologies 4, no. 8(112) (2021): 59–66. http://dx.doi.org/10.15587/1729-4061.2021.238538.

Full text

Abstract:

The design and adjustment of modern gas turbine engines significantly rely on the use of numerical research methods. This paper reports a method devised for calculating the thermogasdynamic parameters and characteristics of a turboshaft gas turbine engine. The special feature of a given method is a two-dimensional blade-by-blade description of the compressor in the engine system. Underlying the calculation method is a nonlinear mathematical model that makes it possible to describe the established processes occurring in individual nodes and in the engine in general. To build a mathematical mode

APA, Harvard, Vancouver, ISO, and other styles

9

MacLeod, J. D., and J. C. G. Laflamme. "Compressor Coating Effects on Gas Turbine Engine Performance." Journal of Engineering for Gas Turbines and Power 113, no. 4 (1991): 530–34. http://dx.doi.org/10.1115/1.2906273.

Full text

Abstract:

In an attempt to increase the time between maintenance actions and to improve performance retention of turboprop engines installed in transport and maritime patrol aircraft, the Canadian Department of National Defence is evaluating an erosion and corrosion-resistant blade coating, for use on compressors. As coatings could appreciably alter engine performance by virtue of their application thickness and surface quality, the National Research Council of Canada was asked to quantify any performance changes that could occur. A project was initiated, utilizing a new Allison T56 turboprop engine, to

APA, Harvard, Vancouver, ISO, and other styles

10

Xu, Wen Chen, De Bin Shan, Wei Feng Zhang, and Yan Lu. "Precision Forging Process Analysis and Preform Optimization of Small Compressor Blade of Titanium Alloy." Applied Mechanics and Materials 364 (August 2013): 493–99. http://dx.doi.org/10.4028/www.scientific.net/amm.364.493.

Full text

Abstract:

Small compressor blades of titanium alloy are important mechanical structural components of advanced aircraft engines. In the present study, the preheating scheme and the forging process of the small compressor blade were modeled by the commercial software DEFORM3D and the forging experiments were conducted on a 10,000KN screw press. The results show that the reasonable preheating temperature for the small blade should be controlled in 960-970°C. The geometric shape and size of the blade preform influenced not only overlap and underfilling defects but also the dimensional precision of small co

APA, Harvard, Vancouver, ISO, and other styles

11

Kvasha, Yu A., N. A. Zinevych, and N. V. Petrushenko. "Features of blade shape variation in the aerodynamic improvement of aircraft gas-turbine engine compressors." Technical mechanics 2022, no. 2 (2022): 17–24. http://dx.doi.org/10.15407/itm2022.02.017.

Full text

Abstract:

This work is devoted to the development of procedures for the aerodynamic improvement of gas-turbine engine axial-flow compressor blade rows. The aim of the work is to compare the efficiency of two methods for impeller blade shape variation in the aerodynamic improvement of an aircraft gas-turbine engine two-stage fan. The first method consists only in varying the blade profile angle along the blade height, while the second consists in varying the blade profile angle and geometrical parameters. The features of the approach used in the solution of this problem are as follows: formulating qualit

APA, Harvard, Vancouver, ISO, and other styles

12

Kachan, О., and S. Ulanov. "The influence of deformation conditions of titanium alloys on the surface quality of the feather of compressor blades." Innovative Materials and Technologies in Metallurgy and Mechanical Engineering, no. 2 (December 7, 2021): 26–31. http://dx.doi.org/10.15588/1607-6885-2021-3-5.

Full text

Abstract:

Purpose of work. Improving the quality of manufacturing of blanks of compressor blades from titanium alloys by precision stamping. Research methods and equipment. The research was carried out by precise stamping of blade blanks from the VT8 titanium alloy of the compressor of the D-436 aircraft engine at various temperatures of deformation. Precise stamping of parts was carried out in one tool stroke from a preliminary blank obtained by extrusion from a rod with a diameter of 30 mm. The research of the surface of the workpiece was carried out after processing by X-ray spectra

APA, Harvard, Vancouver, ISO, and other styles

13

Tabakoff, W. "Compressor Erosion and Performance Deterioration." Journal of Fluids Engineering 109, no. 3 (1987): 297–306. http://dx.doi.org/10.1115/1.3242664.

Full text

Abstract:

Aircraft engines operating in areas where the atmosphere is polluted by small solid particles are typical examples of jet engines operating under hostile atmospheric environment. The particles may be different kinds of sand, volcanic ashes or others. Under these conditions, the gas and particles experience different degrees of turning as they flow through the engine. This is mainly due to the difference in their inertia. This paper presents the results of an investigation of the solid particle dynamics through a helicopter engine with inlet particle separator. The particle trajectories are com

APA, Harvard, Vancouver, ISO, and other styles

14

Зиньковский, Анатолий Павлович, Анатолий Леонидович Стельмах та Сергей Николаевич Кабанник. "РЕЗУЛЬТАТЫ ОЦЕНКИ ДИНАМИЧЕСКОЙ УСТОЙЧИВОСТИ К ДОЗВУКОВОМУ ФЛАТТЕРУ ЛОПАТОЧНЫХ ВЕНЦОВ КОМПРЕССОРОВ НЕКОТОРЫХ АВИАЦИОННЫХ ГАЗОТУРБИННЫХ ДВИГАТЕЛЕЙ". Aerospace technic and technology, № 8 (31 серпня 2019): 78–84. http://dx.doi.org/10.32620/aktt.2019.8.12.

Full text

Abstract:

The paper outlines the results of the investigation on the verification of the express method of prediction of dynamic stability for subsonic flutter using the blade assemblies of individual stages of the compressor of some types of aircraft gas-turbine engines at different modes of their operation. The paper gives a brief overview of the basic concepts of the developed express estimation method, possibilities of the determination of the stability limit for the blade assemblies for a subsonic flutter, as well as the results of the assessment of the dynamic stability of the compressor stages of

APA, Harvard, Vancouver, ISO, and other styles

15

Tishkunov, Alexander, Sergejs Gluhihs, Aleksandrs Korjakins, and Andris Popovs. "ANALYSIS OF REPAIRED GAS TURBINE AND COMPRESSOR BLADES." Aviation 12, no. 2 (2008): 46–50. http://dx.doi.org/10.3846/1648-7788.2008.12.46-50.

Full text

Abstract:

In order to reach desired levels of efficiency and power output of jet engines, advanced gas turbine and compressor blades made from Ti‐6AL‐4V alloy operate at very high temperatures (up to 600°C) and speeds (up to 10000 rpm) [3–4]. Pressure of springing streams and inertial forces are main reasons of stress appearance in the blades. Besides that, blade usually could be out of action after one's edges had become damaged under temperature or foreign object hit negative influence. High cycle fatigue (HCF) accounts for 56 % of major aircraft engine failures and ultimately limits the service life

APA, Harvard, Vancouver, ISO, and other styles

16

Bednarz, Arkadiusz, Krzysztof Puchała, Michał Sałaciński, and Volodymyr Hutsaylyuk. "Numerical Investigation of the Influence of Aerodynamic Loads on the Resonant Frequency of a Compressor Blade Made of EI-961 Alloy." Materials 15, no. 23 (2022): 8391. http://dx.doi.org/10.3390/ma15238391.

Full text

Abstract:

The aim of this work was to numerically determine the influence of aerodynamic loads on the value of the resonant frequency of the compressor blade. The object of the research was the 1st stage compressor blade of the PZL-10W engine. As part of the research, analytical calculations of the resonance frequency were performed and compared with the literature ones (first, second, and third forms of forced vibrations). In the next step of the investigation, a computational model of the compressor stage (fluid domain and rotors) was built and FSI analysis was performed. This analysis was based on CF

APA, Harvard, Vancouver, ISO, and other styles

17

Moumen Idres and Muhamad Adi Muqri Saiful Azmi. "Computational Prediction of the Performance Map of a Transonic Axial Flow Compressor." CFD Letters 14, no. 3 (2022): 11–21. http://dx.doi.org/10.37934/cfdl.14.3.1121.

Full text

Abstract:

Aviation fuel efficiency is an important target for aviation industry. Aircraft engine compression ratio is a key factor to improve fuel consumption. Compression ratio can be increased using transonic compressor. In this study, performance prediction of a transonic axial compressor at design and off-design operating conditions is investigated numerically using ANSYS-CFX software. The compressor is NASA Rotor 37. Firstly, the performance at design point is predicted, where mesh independence study is performed to determine suitable mesh size. Three-dimensional flow details for meridional plane,

APA, Harvard, Vancouver, ISO, and other styles

18

Roberts, William B., Albert Armin, George Kassaseya, Kenneth L. Suder, Scott A. Thorp, and Anthony J. Strazisar. "The Effect of Variable Chord Length on Transonic Axial Rotor Performance." Journal of Turbomachinery 124, no. 3 (2002): 351–57. http://dx.doi.org/10.1115/1.1459734.

Full text

Abstract:

Aircraft fan and compressor blade leading edges suffer from atmospheric particulate erosion that reduces aerodynamic performance. Recontouring the blade leading edge region can restore blade performance. This process typically results in blades of varying chord length. The question therefore arises as to whether performance of refurbished fans and compressors could be further improved if blades of varying chord length are installed into the disk in a certain order. To investigate this issue the aerodynamic performance of a transonic compressor rotor operating with blades of varying chord lengt

APA, Harvard, Vancouver, ISO, and other styles

19

Filippov, A. A. "Calculation of natural frequencies and effective elastic properties of the axial compressor rotor blade." Proceedings of the Mavlyutov Institute of Mechanics 11, no. 1 (2016): 81–87. http://dx.doi.org/10.21662/uim2016.1.012.

Full text

Abstract:

The results of the numerical calculations of the natural frequencies of the composite rotor blade axial compressor of aircraft gas turbine engine. Shows the way of solving of а unit cell problem arising in the application of asymptotic homogenization method to elastic deformation of regular composite structures. Components of the effective stiffness matrix of the composite blade obtained by asymptotic homogenization.

APA, Harvard, Vancouver, ISO, and other styles

20

Ma, Zhuang, Ying Hong Li, and Cheng Wang. "Investigation of Laser Shock Peening on Aero-Engine Compressor Rotor Blade." Key Engineering Materials 373-374 (March 2008): 404–7. http://dx.doi.org/10.4028/www.scientific.net/kem.373-374.404.

Full text

Abstract:

Compressor rotor blade is one of the critical parts of aero-engine. Because of the complex structure and bad work environment, it often went wrong. More over, the trouble of blade can result in serious accident of engine even the aircraft. But the conventional shot peening strengthen method couldn’t take ideal effect, so a new method, laser shock peening on aero-engine compressor rotor blade was studied in this paper. The principle of laser shock peening strengthening was presented first, and the appropriate shock parameters of a certain type blade are fixed on by modeling. The parameters were

APA, Harvard, Vancouver, ISO, and other styles

21

Bielenda, Leszek, Wojciech Obrocki, Maciej Masłyk, and Jan Sieniawski. "The methodology for measuring the vibration amplitude of the blade of the aircraft engine compressor in the fatigue test." Mechanik 91, no. 3 (2018): 230–32. http://dx.doi.org/10.17814/mechanik.2018.3.38.

Full text

Abstract:

Results of comparison research of various sensors types used in the fatigue tests for aircraft engine compressor blade vibration amplitude measurement were analysed. Sensors under tests: inductive, capacitive, eddy-current, laser and vibration. Presented were sensors characteristics and their faults. Additional test stand instrumentation was designed and performed, including mounting bracket.

APA, Harvard, Vancouver, ISO, and other styles

22

Bednarz, Arkadiusz, and Wojciech Zbigniew Misiolek. "Numerical and Experimental Assessment of the Effect of Residual Stresses on the Fatigue Strength of an Aircraft Blade." Materials 14, no. 18 (2021): 5279. http://dx.doi.org/10.3390/ma14185279.

Full text

Abstract:

The work presents the results of numerical fatigue analysis of a turbine engine compressor blade, taking into account the values of initial stresses resulting from surface treatment-shot-peening. The values of the residual stresses were estimated experimentally using X-ray diffraction. The paper specifies the values of the residual stresses on both sides of the blade and their reduction due to cutting through the blade-relaxation. The obtained values of the residual stresses were used as initial stresses in the numerical fatigue analysis of the damaged compressor blade, which was subjected to

APA, Harvard, Vancouver, ISO, and other styles

23

Hoyniak, D., and S. Fleeter. "Forced Response Analysis of an Aerodynamically Detuned Supersonic Turbomachine Rotor." Journal of Vibration and Acoustics 108, no. 2 (1986): 117–24. http://dx.doi.org/10.1115/1.3269311.

Full text

Abstract:

High-performance aircraft engine fan and compressor blades are vulnerable to aerodynamically forced vibrations generated by inlet flow distortions due to wakes from upstream blade and vane rows, atmospheric gusts, and maldistributions in inlet ducts. In this paper, an analysis is developed to predict the flow-induced forced response behavior of an aerodynamically detuned rotor operating in a supersonic flow with a subsonic axial component. The aerodynamic detuning is achieved by alternating the circumferential spacing of adjacent rotor blades. The total unsteady aerodynamic loading acting on t

APA, Harvard, Vancouver, ISO, and other styles

24

Wang, Zhi De, Jing Li, Zhen Wei Guan, Yu Zhong Zhang, Yan Wang, and Zhi Yong Wang. "Fabrication and Evaluation of an Amino Modified Epoxy Coating for Anti-Scouring and Anti-Corrosion Application." Materials Science Forum 815 (March 2015): 684–89. http://dx.doi.org/10.4028/www.scientific.net/msf.815.684.

Full text

Abstract:

Excellent performance is necessary for compressor blade when aircraft engine serves in harsh environment, where it will go through scouring from jet-stream and extraneous sand, shaking of blades and corrosion from corrosive medium, taking moisture, salt, SO2 for example. Due to the shortage of scouring resistant and anti-corrosion property, shedding of damaged coating is a fundamental reason for the breakdown of aircraft engine blades, which is also the technique bottleneck that hinders the engineering application of compressor blades. Aiming at such problems, an amino modified epoxy coating w

APA, Harvard, Vancouver, ISO, and other styles

25

Srinivas, G., K. Raghunandana, and B. Satish Shenoy. "Flow blockage in a transonic axial flow compressor: simulation analysis under distorted conditions." International Journal of Engineering & Technology 7, no. 2.21 (2018): 43. http://dx.doi.org/10.14419/ijet.v7i2.21.11833.

Full text

Abstract:

Today the aircraft industry is looking for faster and safer engines for both civil and military applications. The performance of all different types of air breathing engines depends on the amount of mass flow rate of air entering and hot gas ejecting out from the engine. Thrust is the key role for any engine performance. To achieve more thrust all the turbo machinery components like axial fan, axial flow compressor and axial flow turbine should function effectively. This paper is primarily dealing about one of the turbo machinery component, axial flow compressor performance where the study is

APA, Harvard, Vancouver, ISO, and other styles

26

Valenti, Michael. "Turbines for Peace." Mechanical Engineering 122, no. 08 (2000): 70–72. http://dx.doi.org/10.1115/1.2000-aug-5.

Full text

Abstract:

This article discusses that military-sponsored research tools can improve the machines that drive civil applications. The Defense Evaluation and Research Agency (DERA) researchers tested the engine of the legendary DeHavilland Vampire single seat jet fighter in the late 1940s. This Vampire is owned by Fred Ihlenburg, president of Yakity Yaks Inc., an importer of foreign military aircraft, based in Aurora, Oregon. DERA is investigating heat transfer on turbine blades to help gas turbine manufacturers develop a cooling system that will keep blades at an optimum temperature while minimizing losse

APA, Harvard, Vancouver, ISO, and other styles

27

Lu, Zhenyong, Shun Zhong, Huizheng Chen, Yushu Chen, Jiajie Han, and Chao Wang. "Modeling and Dynamic Characteristics Analysis of Blade-Disk Dual-Rotor System." Complexity 2020 (January 25, 2020): 1–13. http://dx.doi.org/10.1155/2020/2493169.

Full text

Abstract:

In this paper, a simplified dynamic model of a dual-rotor system coupled with blade disk is built, and the effects of blade parameters of an aircraft engine on the dynamic characteristics of a dual-rotor system are studied. In the methodology, the blade is simplified as a cantilever structure, and the dynamical equations are obtained by the means of a finite element method. The amplitude-frequency response curves and orbits of shaft centre-vibration shape diagram are used to analyze the effects of blade parameters on dynamic characteristics of a dual-rotor system. The results indicate that the

APA, Harvard, Vancouver, ISO, and other styles

28

Fan, Tengbo, Baotong Wang, Chuanxiang Yan, Wenchao Zhang, Zhaoyun Song, and Xinqian Zheng. "Effect of Self-Recirculating Casing Treatment on the Aerodynamic Performance of Ultra-High-Pressure-Ratio Centrifugal Compressors." Processes 11, no. 8 (2023): 2439. http://dx.doi.org/10.3390/pr11082439.

Full text

Abstract:

The motivation to design a more efficient and compact aircraft engine leads to a continuous increase in overall pressure ratio and decrease in the stage number in compressors. Compared to the traditional multi-stage compressor, a single-stage ultra-high-pressure-ratio centrifugal compressor with a pressure ratio higher than 10.0 can significantly improve the engine’s power-to-weight ratio and fuel economy with a reduced structure complexity. Thus, it has great potential to be adopted in the compression system of advanced aero engines, such as turboshaft engines, in the future. However, the hig

APA, Harvard, Vancouver, ISO, and other styles

29

Langston, Lee S. "Mounting Troubles." Mechanical Engineering 133, no. 03 (2011): 46–49. http://dx.doi.org/10.1115/1.2011-mar-6.

Full text

Abstract:

This article analyzes the problems encountered in developing the first jumbo jet, the Boeing 747. In the 1960s, the jumbo jet—a wide-body aircraft with two aisles and up to 10 seats per row—was the logical next step in the progression of the airliner. For the Pratt & Whitney JT9D, which was causing the 747 trouble, the engine skin casing was both bending and ovalizing—exhibiting non-circular distortion—under thrust loading that could be as high as 43,500 pounds on takeoff. The ovalizing distortion resulted in turbine and compressor blade rubbing against the interior of the engine case and

APA, Harvard, Vancouver, ISO, and other styles

30

Nyzhnyk, Serhii, Ihor Zorik, Kostiantyn Danko, and Justas Nugaras. "TECHNOLOGY FOR RESTORATION AND REPAIR OF AIRCRAFT ENGINE PARTS." Aviation 25, no. 4 (2021): 262–67. http://dx.doi.org/10.3846/aviation.2021.15924.

Full text

Abstract:

Problems of increasing the service life of compressor blades of aircraft gas turbine engines using detonation spraying technology are considered. The simulation of the parameters of the velocity and temperature of the particles of the sprayed material in the barrel of the detonation unit and in the flooded space to the substrate was carried out, followed by the choice of the optimal technological parameters of the spraying process. The control system of the detonation unit has been modernized. An experiment was carried out on the deposition of the Al2O3 coatings on the samples of a substrate m

APA, Harvard, Vancouver, ISO, and other styles

31

Alozie, O., Y. G. Li, M. Diakostefanis, X. Wu, X. Shong, and W. Ren. "Assessment of degradation equivalent operating time for aircraft gas turbine engines." Aeronautical Journal 124, no. 1274 (2020): 549–80. http://dx.doi.org/10.1017/aer.2019.153.

Full text

Abstract:

ABSTRACTThis paper presents a novel method for quantifying the effect of ambient, environmental and operating conditions on the progression of degradation in aircraft gas turbines based on the measured engine and environmental parameters. The proposed equivalent operating time (EOT) model considers the degradation modes of fouling, erosion, and blade-tip wear due to creep strain, and expresses the actual degradation rate over the engine clock time relative to a pre-defined reference condition. In this work, the effects of changing environmental and engine operating conditions on the EOT for th

APA, Harvard, Vancouver, ISO, and other styles

32

KOZAKIEWICZ, Adam, Olga GRZEJSZCZAK, and Tomasz LACKI. "The comparative analysis of the selected construction types of axial compressor stage including the modal analysis." Journal of Machine Engineering 4, no. 17 (2017): 91–97. http://dx.doi.org/10.5604/01.3001.0010.7008.

Full text

Abstract:

The article concerns the issues of the scope of optimization of the gas turbine jet engine. These issues include limiting the weight and number of engine parts. One way to reduce the weight and number of components, including the compressor assembly, is to use the BLISK's replacement construction. The replacement construction should meet the strength requirement and the vibration spectrum as well. The paper presents a comparative analysis of the influence of rotational speed on the characters and the vibration frequency of the single rotor stage of the high pressure compressor. The analysis wa

APA, Harvard, Vancouver, ISO, and other styles

33

Montano, Zhuzhell, Marcel Seidler, Johannes Riemenschneider, and Jens Friedrichs. "A Coupling Method for the Design of Shape-Adaptive Compressor Blades." Applied Mechanics 3, no. 1 (2022): 182–209. http://dx.doi.org/10.3390/applmech3010014.

Full text

Abstract:

The design of flexible and efficient aircraft engines and propulsion systems plays a crucial role in the development of future low-emission aircraft. Implementing shape-variable blades to compressor front stage rotors presents a high potential for increasing efficiency, since through adaptation, the blades are capable of optimizing their shape for different flight phases and aerodynamic conditions. Modifying the shape of the blades by using structurally integrated actuators allows this adaptation and therefore helps enhance their aerodynamic behavior for different flight regimes. Since up to n

APA, Harvard, Vancouver, ISO, and other styles

34

Kroeger, Jim. "Large and Small Turbofans." Mechanical Engineering 138, no. 09 (2016): 80–82. http://dx.doi.org/10.1115/1.2016-sep-7.

Full text

Abstract:

This article presents a study on common design challenges of large and small turbofans. Turbofan engines powering large transport aircraft have demonstrated much different design objectives than business-jet turbofans including thrust, range, mission type, development cost, unit price, maintainability standards, and production quantities. Prolific use of ‘thermal barrier coating’ has helped turbine designers compensate for the inability to distribute a large quantity of small diameter film holes over the turbine blade surface. The historical trends in overall pressure ratio observed for both l

APA, Harvard, Vancouver, ISO, and other styles

35

Bailey, D. W., K. M. Britchford, J. F. Carrote, and S. J. Stevens. "Performance Assessment of an Annular S-Shaped Duct." Journal of Turbomachinery 119, no. 1 (1997): 149–56. http://dx.doi.org/10.1115/1.2841003.

Full text

Abstract:

An experimental investigation has been carried out to determine the aerodynamic performance of an annular S-Shaped duct representative of that used to connect the compressor spools of aircraft gas turbine engines. For inlet conditions in which boundary layers are developed along an upstream entry length, the static pressure, shear stress and velocity distributions are presented. The data show that as a result of flow curvature, significant streamwise pressure gradients exist within the duct, with this curvature also affecting the generation and suppression of turbulence. The stagnation pressur

APA, Harvard, Vancouver, ISO, and other styles

36

Даценко, Вадим Анатольевич, Александр Евгеньевич Дёмин та Наталия Владимировна Пижанкова. "ОПРЕДЕЛЕНИЕ ПОЛОЖЕНИЯ ГРАНИЦЫ ОБЛАСТИ УСТОЙЧИВОЙ РАБОТЫ ОСЕВОГО МНОГОСТУПЕНЧАТОГО КОМПРЕССОРА ПРИ ВЫПОЛНЕНИИ РАСЧЕТНЫХ ИССЛЕДОВАНИЙ". Aerospace technic and technology, № 6 (27 листопада 2020): 34–44. http://dx.doi.org/10.32620/aktt.2020.6.04.

Full text

Abstract:

The implementation of the high requirements for modern gas turbine engines depends on the perfection of their components. The reliability of the engine operation is largely determined by the compressor gas-dynamic stability margin. In this paper, a review and analysis of some of the most common approaches to determining the boundary of the compressor gas-dynamic stability region calculation are performed. Based on the analysis, it is shown that the diffuser factor and the equivalent diffuser coefficient are the most suitable for the practice of computational studies at the stage of designing a

APA, Harvard, Vancouver, ISO, and other styles

37

Дроконов, Алексей, Aleksey Drokonov, Алексей Дроконов, and Aleksey Drokonov. "GENERATION AND METHODS FOR VIBRO-ACOUSTIC ACTIVITY DECREASE IN GASCOMPRESSOR UNITS WITH GAS TURBINE DRIVE." Bulletin of Bryansk state technical university 2017, no. 1 (2017): 68–71. http://dx.doi.org/10.12737/24894.

Full text

Abstract:

Block-modular gas compressor units (GCU) of a container type with an aircraft and ship gasturbine drive – a power source of vibration and noise pollution of environment.  Their basic inner sources – gas turbine engine and a centrifugal compressor. Besides, to power noise sources in the structure of GCU belong multiplier, an air cleaner of the air inlet system, an exhaust shaft, section walls of an engine and a compressor. A gas turbine engine and a compressor define mainly a distant sound field and the rest of noise sources – near-in one. A complex modernization of such plant

APA, Harvard, Vancouver, ISO, and other styles

38

Leishman, B. A., N. A. Cumpsty, and J. D. Denton. "Effects of Bleed Rate and Endwall Location on the Aerodynamic Behavior of a Circular Hole Bleed Off-Take." Journal of Turbomachinery 129, no. 4 (2006): 645–58. http://dx.doi.org/10.1115/1.2752191.

Full text

Abstract:

In a jet engine bleed off-takes on the hub and casing endwalls, part way through the compressor, supply high-pressure air for cooling, sealing, de-icing, and aircraft cabin air applications; bleed also assists compressor operation at part-speed conditions. Two separate issues are of interest: the bleed off-take air pressure and the interaction of the bleed off-take with the primary flow through the blade passage. In this paper, the aerodynamic behavior is presented for a circular-hole bleed off-take at three endwall locations within a stationary cascade blade passage: at midpassage; near the b

APA, Harvard, Vancouver, ISO, and other styles

39

Редин, Иван Иванович, та Михаил Анатольевич Шевченко. "ДІАГНОСТИКА ПЕРЕДПОМПАЖНОГО СТАНУ ОСЬОВОГО КОМПРЕСОРА З НАДРОТОРНИМ ПРИЛАДОМ". Aerospace technic and technology, № 8 (25 грудня 2018): 97–107. http://dx.doi.org/10.32620/aktt.2018.8.15.

Full text

Abstract:

Ensuring the gas-dynamic stability of gas turbine engine, still remains one of the actual problem of modern aircraft engine building. To date, a significant number of studies have been conducted. This studies are the foundation for different techniques of diagnosing the pre-surge condition condition. Also known that one of the ways to solve the problem of increasing gas-dynamic stability is the use of casing treatment. However, there are no clearly formulated techniques that allow diagnosing the surge line in an axial compressor with casing treatment. Consequently, the problem of their develop

APA, Harvard, Vancouver, ISO, and other styles

40

Kozakiewicz, Adam, and Olga Grzejszczak. "Analysis of operational damage and their impact on the work of the contact surfaces in the axial compressor stage." Mechanik 91, no. 7 (2018): 517–19. http://dx.doi.org/10.17814/mechanik.2018.7.70.

Full text

Abstract:

During the operation, rotating parts of aircraft turbine engines are exposed on different types of damage. These damages mostly ensure from the difficult work conditions of this components. The article presents examples of failure of aircraft engines resulting from damage to the compressor elements. The influence of exemplary damages in the area of the blade on the work of contact surfaces in the disk rim part and the blade footer was analyzed. The distribution of stresses and pressures was determined on assuming different ranges of rotational speed as well. Numerical analyzes were performed u

APA, Harvard, Vancouver, ISO, and other styles

41

Zhao, X., S. Sahoo, K. Kyprianidis, J. Rantzer, and M. Sielemann. "Off-design performance analysis of hybridised aircraft gas turbine." Aeronautical Journal 123, no. 1270 (2019): 1999–2018. http://dx.doi.org/10.1017/aer.2019.75.

Full text

Abstract:

ABSTRACTAn advanced geared turbofan with year 2035 technology level assumptions was established and used for the hybridisation study in this paper. By boosting the low-speed shaft of the turbofan with electrical power through the accessory gearbox, a parallel hybrid concept was set up. Focusing on the off-design performance of the hybridised gas turbine, electrical power input to the shaft, defined as positive hybridisation in this context, generally moves the compressor operation towards surge. On the other hand, the negative hybridisation, which is to reverse the power flow direction can imp

APA, Harvard, Vancouver, ISO, and other styles

42

Joy, Nivin, Subramaniam Prakash, Arunagiri Krishnamoorthy, and Pitchaimuthu Gunasekar. "Characterization of titanium grade 5 alloy compressor blade in a jet engine using advanced materials for optimum thrust production." International Journal of Turbo & Jet-Engines 40, no. 2 (2020): 119–26. http://dx.doi.org/10.1515/tjj-2020-0040.

Full text

Abstract:

Abstract Machining operations on titanium and its alloys have always been a challenge in the design of compressor blade in the jet engine which undergo profound stress during impact of debris and affects the life span of both static and rotary blades. Titanium grade 5 alloy is used to resist the creep and fatigue due to the thermal expansion and sudden impact including bird strike. However, machining them is difficult. An attempt was made to mitigate the temperature during drilling of Ti-6Al-4V by adopting cryogenic coolants LN2, CO2 and a novel approach of coconut oil under varying cutting sp

APA, Harvard, Vancouver, ISO, and other styles

43

Sudhir Sastry, Y. B., B. G. Kiros, F. Hailu, and P. R. Budarapu. "Impact analysis of compressor rotor blades of an aircraft engine." Frontiers of Structural and Civil Engineering 13, no. 3 (2018): 505–14. http://dx.doi.org/10.1007/s11709-018-0493-3.

Full text

APA, Harvard, Vancouver, ISO, and other styles

44

Ernst, A., and M. Weigold. "MACHINE DATA-BASED PREDICTION OF BLISK BLADE GEOMETRY CHARACTERISTICS." MM Science Journal 2021, no. 5 (2021): 5046–51. http://dx.doi.org/10.17973/mmsj.2021_11_2021151.

Full text

Abstract:

The increasing availability of data recording solutions in the field of machining in combination with major developments in Machine Learning and Artificial Intelligence enable new approaches towards optimization in the industrial environment. In the aviation industry, critical components must fulfil extremely high quality standards. This requires a stable and error-free manufacturing process, as well as an extensive geometrical compliance, what is until now verified by long-lasting coordinate measuring machine (CMM) inspection. This publication shows how machine data analysis can contribute to

APA, Harvard, Vancouver, ISO, and other styles

45

De Pratti, Giovanni Maria. "Aerodynamical Performance Decay Due to Fouling and Erosion in Axial Compressor for GT Aeroengines." E3S Web of Conferences 197 (2020): 11002. http://dx.doi.org/10.1051/e3sconf/202019711002.

Full text

Abstract:

The ingestion of solid abrasive particles and/or foulants causes erosion of the compressor blades, resulting in a considerable reduction in the performance and working life of aviation/heavy duty GT and an increase in fuel consumption. The geometry variation at the Leading Edge (L.E. blunting) and Trailing Edge (T.E. thickness reduction), together with the general increase of airfoil surface roughness, depends on the characteristics of the incident particles, the geometry and the materials of the blade cascade, the dynamic parameters of the particles and on the type of impact. In order to rect

APA, Harvard, Vancouver, ISO, and other styles

46

Kozakiewicz, Adam, Stanisław Kachel, Stanisław Jóźwiak, and Przemysław Jóźwiak. "Structural ultimate strength analysis of a first stage fan blade in a turbine jet engine RD-33." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 1 (2016): 77–84. http://dx.doi.org/10.1177/0954410016671344.

Full text

Abstract:

Statistical data clearly points out compressor train outage as one of the main reasons for the breakdown of aircraft power units. Outages are caused by various factors, including material conditions as the main one. Therefore, structural ultimate strength analysis of constructional raw material properties used in the production process of such an important part of an engine is not only of tremendous significance during the designing phase but also in a research phase and expertise associated with emergency situations. Considering the above-mentioned factors the article presents the outcomes of

APA, Harvard, Vancouver, ISO, and other styles

47

Orekhov, A. A., E. V. Shemetova, and Yan Naing Min. "Fabrication and Testing of Rocket Engine Construction Elements by Addictive Production Approach." WSEAS TRANSACTIONS ON APPLIED AND THEORETICAL MECHANICS 16 (September 1, 2021): 120–26. http://dx.doi.org/10.37394/232011.2021.16.12.

Full text

Abstract:

For the first time, using the technology of selective laser sintering, prototypes of rocket engine compressor blades were manufactured with subsequent analysis of the strength, technological, physical and mechanical characteristics of the product. The physical and mechanical properties of the manufactured blades were investigated, it was found that the short-term strength limit at 20 °C is 1450 MPa, and at 300 °C the ultimate strength is 1300 MPa, thus thermal losses in deformation resistance are no more than 12%, which allows the material to be used in aircraft construction, including for sup

APA, Harvard, Vancouver, ISO, and other styles

48

Kozakiewicz, Adam. "Development of a Model for the Intake Channel within a MRCA Turbine Engine in Order to Analyze Intake Vortex Phenomena." Solid State Phenomena 198 (March 2013): 188–93. http://dx.doi.org/10.4028/www.scientific.net/ssp.198.188.

Full text

Abstract:

Turbine engines need to produce the thrust from several to about one thousand kilograms of the air per second depending on the engine type. Due to the demand for such a significant amount of the air a unique three dimensional field of speed occurs in the area of the intake vicinity. The characteristic feature of this field, when the engine runs on the ground, is generation of an inlet stagnation line and a stagnation point. In case of the aircraft engines, a vortex is developed chiefly due to external disturbances e.g. because of crosswind gusts or a stream of engine exhaust from another aircr

APA, Harvard, Vancouver, ISO, and other styles

49

Kvasha, Yu A., and N. A. Zinevych. "On the effect of the meridional contour shape on the power characteristics of a centrifugal compressor wheel." Technical mechanics 2020, no. 3 (2020): 12–17. http://dx.doi.org/10.15407/itm2020.03.012.

Full text

Abstract:

This work is concerned with the development of approaches to the optimal aerodynamic design of centrifugal compressor wheels, which is due to the use of centrifugal stages in compressors of modern aircraft gas turbine engines and power plants. The aim of this work is a computational study of the effect of the meridional contour shape of a centrifugal compressor wheel on its power characteristics. The basic method is a numerical simulation of 3D turbulent gas flows in centrifugal wheels on the basis of the complete averaged Navier¬–Stokes equations and a two-parameter turbulence model. The comp

APA, Harvard, Vancouver, ISO, and other styles

50

Shuvaev, Nikolay, Aleksandr Siner, and Ruslan Kolegov. "DEVELOPMENT OF THE NUMERICAL METHODOLOGY FOR THE ESTIMATION OF RESONANT PROCESSES AT GASTURBINE ENGINE FLOW DUCT." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 62 (2020): 12–19. http://dx.doi.org/10.15593/2224-9982/2020.62.02.

Full text

Abstract:

Ensuring safety of flights is the most important task that is being solved in the process of designing an aircraft engine and aircraft. The most complex are the physical processes occurring inside the aircraft engine, especially in its gas generator: combustion chamber, high-pressure compressor and high-pressure turbine. The unsteady flow of gas in the flow duct of the aircraft engine is very complex, it is difficult to model, because the flow is characterized by a wide range of time and space scales. Unsteady flow in a high-pressure compressor can cause surge and breakdown of the compressor a

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!