Experimental and Numerical Research of Fan Bypass Duct Flows in Japanese Environmentally Compatible Engine for Small Aircraft Project

2011 ◽  
Author(s):  
Yoshinori Ooba ◽  
Takeshi Murooka ◽  
Takashi Yamane ◽  
Osamu Nozaki ◽  
Takeshi Ishiyama
Keyword(s):  
Cfd Simulation ◽  
Aerodynamic Performance ◽  
Measured Data ◽  
Turbine Engines ◽  
Cfd Analysis ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Numerical Research ◽  
Long Nose ◽  
Small Aircraft

This research aims at developing fan integration technologies to improve the installation loss due to the fan/OGV/strut/pylon interaction of gas-turbine engines for small aircraft on Small Aircraft Project in Japan (the ECO Engine Project). Researches on experimental measurement using fan rig testing and numerical prediction using unsteady CFD analysis are conducted. The UPACS code which is developed by JAXA is used in order to accurately simulate the phenomena which occur in the interaction between a rotating fan and its downstream obstacles like strut/pylon in the fan duct. The accuracy of the CFD simulation is also validated by the measured data acquired in the rig testing. Through the investigations, its interaction mechanisms are clarified and the reducing technologies of such interaction for small aircraft engines are created. In the paper, the achievement of the improved aerodynamic performance by introducing the new concept of the long nose shaped fat pylon L/E are demonstrated.

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure

1990 ◽  
Author(s):  
Yoshiharu Tsujikawa ◽  
Makoto Nagaoka
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Specific Impulse ◽  
Optimization Procedure ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Scramjet Engine ◽  
Aero Engines

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including scramjet engine) to achive the maximum performance. The optimization of such criteria as thermal efficiency, specific output and total performance for gas turbine engines, and overall efficiency, non-dimensional thrust and specific impulse for aero-engines have been performed by the optimization procedure with multiplier method. The comparisons of results with analytical solutions establishes the validity of the optimization procedure.

Investigation of Fixed-Rake Sampling System for the Assessment of Emission Characteristics of Gas Turbine Engines

1983 ◽  
Author(s):  
H. C. Low ◽  
A. P. Dowling
Keyword(s):  
Environmental Protection Agency ◽  
Sampling Methods ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Sampling System ◽  
Turbofan Engine ◽  
Optimum Configuration ◽  
Compliance Testing ◽  
The Us

The regulations proposed by the US Environmental Protection Agency to limit the quantity of pollutant gases emitted by aircraft engines allow the exhaust of engines submitted for compliance testing to be sampled by a fixed-multipoint rake. However, the onus is placed on the manufacturer to prove the representativeness of the samples taken in this relatively cheap fashion. To illustrate best possible accuracies, the exhaust of an M45H civil turbofan engine has hen extensively sampled and a computer program has been used to select the optimum configuration of a cruciform rake. The program demanded excellent agreement between the sampling methods and this proved to be the case in actual tests. However, the program also indicates that the errors of a simply designed rake giving area-weighted samples would also be less than 10%. Sampling in the FAA diamond pattern would give rise to a 20% error in CO emissions.

scholarly journals Some Aerodynamic Problems of Aircraft Engines: Fifty Years After -The 2007 IGTI Scholar Lecture-

2009 ◽  
Vol 131 (3) ◽  
Author(s):  
Edward M. Greitzer
Keyword(s):  
Gas Turbine ◽  
Collaborative Research ◽  
Research Process ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Jet Engines ◽  
Organizational Boundaries ◽  
Turbine Performance ◽  
Single Discipline

Problems of high technological interest, for example the development of gas turbine engines, span disciplinary, and often organizational, boundaries. Although collaboration is critical in advancing the technology, it has been less a factor in gas turbine research. In this paper it is proposed that step changes in gas turbine performance can emerge from collaborative research endeavors that involve the development of integrated teams with the needed range of skills. Such teams are an important aspect in product development, but they are less familiar and less subscribed to in the research community. The case histories of two projects are given to illustrate the point: the development of the concept of “smart jet engines” and the Silent Aircraft Initiative. In addition to providing a capability to attack multidisciplinary problems, the way in which collaboration can enhance the research process within a single discipline is also discussed.

scholarly journals EFFECT OF HYSTERESIS IN AXIAL COMPRESSORS OF GAS-TURBINE ENGINES

Aviation ◽  
2012 ◽  
Vol 16 (4) ◽  
pp. 97-102 ◽  
Author(s):  
Mykola Kulyk ◽  
Ivan Lastivka ◽  
Yuri Tereshchenko
Keyword(s):  
Gas Turbine ◽  
Axial Compressor ◽  
Separated Flow ◽  
Aerodynamic Performance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Bladed Disks ◽  
Axial Compressors

The phenomenon of separated flow hysteresis in the process of the streamlining the axial compressor of gas-turbine engines is considered. Generalised results of research on the occurrence of hysteresis in the aerodynamic performance of compressor grids and its influence on the performance of the bladed disks of compressors that operate in real conditions of periodic circular non-uniformity are demonstrated.

Computational Investigation on Centrifugal Compressor Performance at Various Altitudes

2011 ◽  
Vol 230-232 ◽  
pp. 1123-1128
Author(s):  
Yu Wang ◽  
Zhen Luo
Keyword(s):  
Gas Turbine ◽  
Centrifugal Compressor ◽  
Cfd Simulation ◽  
Numerical Solutions ◽  
Weight Ratio ◽  
Critical Factor ◽  
Computational Method ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Ambient Temperatures

Small gas turbine engines have been considered as a potential and popular mean of propulsion for Unmanned Aerial Vehicles (UAV). With the advantage of high thrust/power-to-weight-ratio from these engines, small aircraft can have larger payload allowance and higher altitude capability. However, at present, these gas turbine engines are not mature enough to perform critical mission for UAV. To be used for such critical mission, these gas turbine engines need a better reliability, efficiency and endurance. The capability of the engine to work efficiently in conditions at different altitude with the variant of air density is a critical factor related to higher operational ceiling. Hence this work aims to present a Computational Fluid Dynamics (CFD) simulation approach focusing on centrifugal compressors which are applied to turbo machines. A computational method is developed for studying the performance of small gas turbine engines over a range of altitude and ambient temperatures under different engine rates, and a centrifugal compressor simulation model is generated by using CFD techniques. Through numerical solutions obtained for different mesh sets the finest mesh of the model was determined. The performance curves obtained by the CFD simulation has been compared with the results obtained from the analytical method.

Some Aerodynamic Problems of Aircraft Engines: Fifty Years After

2007 ◽  
Author(s):  
Edward M. Greitzer
Keyword(s):  
Gas Turbine ◽  
Research Process ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Jet Engines ◽  
Case Histories ◽  
Disciplinary Boundaries ◽  
Turbine Performance ◽  
Single Discipline

Problems of high technological interest, for example the development of gas turbine engines, span disciplinary boundaries. Collaboration is critical in advancing the technology, but it has been less a factor in gas turbine research. In this paper it is proposed that step changes in gas turbine performance can emerge from such collaborative endeavors. In these, success depends on the development of integrated teams with the appropriate range of skills. This is well known in product development, but it is less familiar, and less subscribed to, in the research community. Case histories of two projects are given to illustrate the point: the development of the concept of “smart jet engines” and the Silent Aircraft Initiative. In addition to providing the ability to attack multidisciplinary issues discussion is also given about the way in which collaboration can enhance the research process within a single discipline.

scholarly journals Methods of clustering parameters in the creation of neural network multi-mode dynamic models of aircraft engines

2021 ◽  
pp. 71-78
Author(s):  
Александр Анатолиевич Тамаргазин ◽  
Людмила Борисовна Приймак ◽  
Валерий Владиславович Шостак
Keyword(s):  
Neural Network ◽  
Cluster Analysis ◽  
Gas Turbine ◽  
Technical Condition ◽  
Technical State ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Clustering Methods ◽  
Aviation Engines

The presence on modern aviation gas-turbine engines of dozens and even hundreds of sensors for continuous registration of various parameters of their operation makes it possible to collect and process large amounts of information. This stimulates the development of monitoring and diagnostic systems. At the same time the presence of great volumes of information is not always a sufficient condition for making adequate managerial decisions, especially in the case of evaluation of the technical condition of aviation engines. Thus it is necessary to consider, that aviation engines it is objects which concern to individualized, i.e. to such which are in the sort unique. Therefore, the theory of creating systems to assess the technical state of aircraft engines is formed on the background of the development of modern neural network technology and requires the formation of specific methodological apparatus. From these positions in the article the methods which are used at carrying out clustering of the initial information received at work of modern systems of an estimation and forecasting of a technical condition of aviation gas-turbine engines are considered. This task is particularly relevant for creating neural network multimode models of aircraft engines used in technical state estimation systems for identification of possible failures and damages. Metric, optimization and recurrent methods of input data clustering are considered in the article. The main attention is given to comparison of clustering methods in order to choose the most effective of them for the aircraft engine condition evaluation systems and suitable for implementation of systems with meta-learning. The implementation of clustering methods of initial data allows us to breakdown diagnostic images of objects not by one parameter, but by a whole set of features. In addition, cluster analysis, unlike most mathematical-statistical methods do not impose any restrictions on the type of objects under consideration, and allows us to consider a set of raw data of almost arbitrary nature, which is very important when assessing the technical condition of aircraft engines. At the same time cluster analysis allows one to consider a sufficiently large volume of information and sharply reduce, compress large arrays of parametrical information, make them compact and visual.

PULSE THERMAL CONTROL OF MOISTURE IN AIRCRAFT LIQUID FUELS

2020 ◽  
Author(s):  
A. A. Starostin ◽  
◽  
D. V. Volosnikov ◽  
P. V. Skripov ◽  
◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Control ◽  
Liquid Fuels ◽  
Turbine Engines ◽  
Jet Fuels ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Turbine Engine ◽  
Fuel Tanks

The reliability of the operation of aircraft engines is determined by chemical reliability, which is due to the quality of the used fuels and lubricants: jet fuels and aircraft oils and their influence on the operational properties of units and assemblies of gas turbine engines. One of the factors reducing the smooth operation of a gas turbine engine is the presence of water traces in the fuel. The main reason is the condensation of water traces in the fuel tanks and its freezing in filters and fuel pipes at temperature differences. In addition, water dissolved in fuel significantly increases the wear of fuel system components and friction pairs.

Combined Air Supply at Fuel Pump Entrance

2014 ◽  
Author(s):  
Salimzhan Gafurov ◽  
Leonid Rodionov ◽  
Asgat Gimadiev
Keyword(s):  
Three Dimensional ◽  
Aviation Fuel ◽  
Turbine Engines ◽  
Cfd Analysis ◽  
Gas Turbine Engines ◽  
Cfd Simulations ◽  
Fuel Pump ◽  
Operating Modes ◽  
Air Supply ◽  
Series Of Experiments

Previous research has shown that aviation fuel pumps, which consist of a screw and centrifugal wheels are the most loaded units of the gas turbine engines. Thus a fuel pump is the key component that limits the reliability and endurance of the fuel system and, as a result, of the whole engine. This paper describes the results of CFD simulations of the process getting free gas to enter the combined pump. The CFD analysis has been used to calculate an unsteady three-dimensional viscous flow of multi-component fluid in the fuel pump. The calculations have been used to determine unsteady loads of fuel pump in different operating modes. To examine the efficiency of the CFD analysis, we conducted a series of experiments. The experimental results proved the accuracy of the numerical model. The results can help to develop measures for the reduction of dynamic loads in aviation fuel pumps in case where combined air is at entrance to pump.

scholarly journals Effect of a Slat Arm Door on the Wing Efficiency of a Commercial Aircraft.

2021 ◽  
Author(s):  
Sharman Perera
Keyword(s):  
Residence Time ◽  
Coming Out ◽  
Cfd Simulation ◽  
Leading Edge ◽  
Aerodynamic Performance ◽  
Cfd Analysis ◽  
Inert Particle ◽  
Commercial Aircraft ◽  
Local Flow ◽  
Closed Model

The objective of this thesis is to determine the influence of a slat arm door on the aerodynamic performance of a wing of a commercial aircraft during it's take off and landing configurations using CFD simulation. The slats are extended forward by extendable arms coming out from the leading edge of the wing after the slat arm is deployed. CFD analysis of wing and slat configuration of the aircraft showed that the removal of this slat door at higher angle of attacks increased the drag by 0.88%, reduced the lift by 1.29%, increased the inert particle residence time inside the slat door compartment by 200.00% and increased the local flow separation area on the top surface of the wing by 42.81% with reference to the closed model.

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