Multi-mode diagnosis of a gas turbine engine using an adaptive neuro-fuzzy system

Gas Turbine Engines (GTEs) are vastly used for generation of mechanical power in a wide range of applications from airplane propulsion systems to stationary power plants. The gas-path components of a GTE are exposed to harsh operating and ambient conditions, leading to several degradation mechanisms. Because GTE components are mostly inaccessible for direct measurements and their degradation levels must be inferred from the measurements of accessible parameters, it is a challenge to acquire reliable information on the degradation conditions of the parts in different fault modes. In this work, a data-driven fault detection and degradation estimation scheme is developed for GTE diagnostics based on an Adaptive Neuro-Fuzzy Inference System (ANFIS). To verify the performance and accuracy of the developed diagnostic framework on GTE data, an ensemble of measurable gas path parameters has been generated by a high-fidelity GTE model under (a) diverse ambient conditions and control settings, (b) every possible combination of degradation symptoms, and (c) a broad range of signal to noise ratios. The results prove the competency of the developed framework in fault diagnostics and reveal the sensitivity of diagnostic results to measurement noise for different degradation symptoms.     

Trends in research of hydrodynamic damping in rotor supports of gas turbine engines

The paper studies different types of dampers for rotor supports of gas turbine engines (GTE). The advantages of hydrodynamic dampers are shown. Hydrodynamic dampers for GTE rotor supports are studied. A new design and technique of calculation are proposed for an adjustable hydrodynamic damper.     

Analysis of domestic aircraft gas turbine engine development dynamics

The schemes of creating aircraft GTE developments by domestic design bureaus are analyzed and basic engines, their modifications and some projects are shown in chronological succession. The amount of developments of individual engine types is examined and a share of each DB in the general scope of developments is determined. The dynamics of GTE developments in the USSR/CIS is presented.     

Experimental study of radial temperature gradient-reducing devices in GTE rotor disks

In this paper, we examine experimentally some devices the principle of action of which is based on using the dynamic pressure of air extracted to engine cooling and which are meant for reducing the radial temperature gradient in GTE rotor disks. We established that the devices equipped with the ejector channels make it possible to accelerate the process of the disk hub heating by hot air suction from the cavity periphery towards the rotor axis of rotation. Using the data of visualization studies, we show the possibility for efficient operation of ejector devices in the conditions of real GTE rotor circumferential velocities.     

Diagnostics of GTE turbine blades using a new vibroacoustic method

The results of development and application of a new vibroacoustic method for diagnostics of the technical condition of aircraft GTE turbine blades are presented.     

Application of a plasma ignition system to ignite kerosene-air mixture in the GTE afterburner in a wide range of its startup conditions

The calculation made on the basis of simple mathematical models are presented for evaluating the temperature and thermal capacity of a plasma plug flame in the GTE afterburner in a wide range of startup conditions.     

Advanced optimization of gas turbine aero-engine transient performance using linkage-learning genetic algorithm: Part I,building blocks detection and optimization in runway

This paper proposes a Linkage Learning Genetic Algorithm (LLGA) based on the messy Genetic Algorithm (mGA) to optimize the Min-Max fuel controller performance in Gas Turbine Engine (GTE). For this purpose, a GTE fuel controller Simulink model based on the Min-Max selection strategy is firstly built. Then, the objective function that considers both performance indices (response time and fuel consumption) and penalty items (fluctuation, tracking error, overspeed and acceleration/deceleration) is established to quantify the controller performance. Next, the task to optimize the fuel controller is converted to find the optimization gains combination that could minimize the objective function while satisfying constraints and limitations. In order to reduce the optimization time and to avoid trapping in the local optimums, two kinds of building block detection methods including lower fitness value method and bigger fitness value change method are proposed to determine the most important bits which have more contribution on fitness value of the chromosomes. Then the procedures to apply LLGA in controller gains tuning are specified stepwise and the optimization results in runway condition are depicted subsequently. Finally, the comparison is made between the LLGA and the simple GA in GTE controller optimization to confirm the effectiveness of the proposed approach. The results show that the LLGA method can get better solution than simple GA within the same iterations or optimization time. The extension applications of the LLGA method in other flight conditions and the complete flight mission simulation will be carried out in part II.     

Calculation of cutterpath errors in machining GTE monoimpeller vane channels with annular cutting tools

A technique for calculating a cutterpath error that appears in cutting complex-shaped vane channels of GTE monoimpellers is proposed. The values of the cutterpath error are studied when different schemes of shaping with an annular tool are used.     

Improvement of aircraft GTE emission characteristics by using the microflame fuel combustion in a shortened combustion chamber

We present the design of an upgraded shortened combustion chamber with the reduced emission of NO_x and CO. Also shown are the results of experimental studies of the developed design effect on main characteristics of the GTE combustion chamber.     

Determination of GTE part vibration characteristics by the holographic interferometry method

The technical parameters of a holographic setup and an optical scheme for registration of holograms are described. The holographic interferograms of vibration modes for the GTE turbine and compressor blades vibrating at resonance frequencies are presented.     

A high-temperature frameless starter-generator integrated into an aircraft engine

In this paper, a starter-generator (SG) integrated into an aircraft gas turbine engine (GTE) is presented. Operating modes of the SG under different temperature conditions are described.     

Diagnostics of gas turbine engine blades using the forced vibration method

The results of experimental studies with the aid of the forced vibration method to determine the technical condition of GTE turbine blades are presented; the phase difference of two vibrations was used as a diagnostic indicator. The schemes of a diagnostic complex are given, the experiment procedure and results obtained are described.     

Experimental development of a plasma spark plug for GTE altitude start

A working process of a plasma spark plug is described and its improved structure that meets the requirements for start and operation stability limits is given. Also presented are the results of the plug tests under conditions of rarefaction to confirm its normal operation at the GTE altitude start.     

Information technology for adjustment of dynamic processes in aircraft gas turbine engines during the acceptance tests

The aids of simulation that are used to automate the adjustment of aircraft GTE control systems are described. A technique of the information technology for adjustment of a control system by turning on the afterburner and results of its practical application during the acceptance tests in series production are presented. Also given is a model for the process of afterburner ignition and reaching the power augmented conditions of the engine.     

Generalized surge line obtaining jointly with speed lines

The analysis and processing results for the known GTE compressor characteristics data are presented. An original method of the universal dimensionless representation of these characteristics is proposed. The dependences obtained are shown in the graphical and analytical form and they are compared with the experimental results.     

Structural optimization of the neural network model for the gas turbine engine monitoring

The paper presents a technique of the neural network model reduction for the GTE operation mode monitoring during bench tests. The technique is based on the conversion of the neural network training task to the of multi-criteria optimization task.     

Influence of input momentum and losses in the turbine on the efficiency of a turbofan engine with periodic fuel combustion

It is shown that research carried out by leading aeroengine manufactures on the use of the thermodynamically high-efficient GTE cycle with the periodic fuel combustion is very urgent. The investigation results are presented and it is disclosed that the advantages of this cycle effectiveness are particularly evident in flight conditions. Owing to a high degree of gas heating, the influence of input momentum and the expansion process efficiency on the economical engine operation is reduced.     

Gas turbine engine disk risk assessment at the design stage taking into account random failures

In this paper, a technique for estimating the failure rate for GTE disks, taking into account the random failures, is presented. According to this technique, we analyzed the effect of tolerances for geometrical sizes, rotation frequency and disk material density on the failure rate.     

绩效评价体系——分配制度改革的保障

绩效考核是科研管理工作中的难点，是各项制度改革的核心之一，介绍了中国燃气涡轮研究院的岗位绩效工资体系和绩效考核办法。阐述了绩效考核办法的特点和应注意的问题，总结了其实施的效果。