Vibration based damage detection of rotor blades in a gas turbine engine

2014 ◽  
Vol 46 ◽  
pp. 26-39 ◽  
Author(s):  
S. Madhavan ◽  
Rajeev Jain ◽  
C. Sujatha ◽  
A.S. Sekhar
Keyword(s):  
Damage Detection ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Turbine Engine

Full-Annulus URANS Study on the Transportation of Combustion Inhomogeneity in a Four-Stage Cooled Turbine

2019 ◽  
Author(s):  
Zhongran Chi ◽  
Haiqing Liu ◽  
Shusheng Zang ◽  
Chengxiong Pan ◽  
Guangyun Jiao
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Inlet Temperature ◽  
Computational Domain ◽  
Temperature Inhomogeneity ◽  
Unsteady Temperature ◽  
Turbine Engine ◽  
Exhaust Temperature ◽  
The Time Domain

Abstract The inhomogeneity of temperature in a turbine is related to the nonuniform heat release and air injections in combustors. In addition, it is influenced by the interactions between turbine cascades and coolant injections. Temperature inhomogeneity results in nonuniform flow temperature at turbine outlets, which is commonly measured by multiple thermal couples arranged in the azimuthal direction to monitor the operation of a gas turbine engine. Therefore, the investigation of temperature inhomogeneity transportation in a multistage gas turbine should help in detecting and quantifying the over-temperature or flameout of combustors using turbine exhaust temperature. Here the transportation of temperature inhomogeneity inside the four-stage turbine of a 300-MW gas turbine engine was numerically investigated using 3D CFD. The computational domain included all four stages of the turbine, consisting of more than 500 blades and vanes. Realistic components (N2, O2, CO2, and H2O) with variable heat capacities were considered for hot gas and cooling air. Coolants were added to the computational domain through more than 19,000 mass and momentum source terms. his was simple compared to realistic cooling structures. A URANS CFD run with over-temperature/flameout at 6 selected combustors out of 24 was carried out. The temperature distributions at rotor–stator interfaces and the turbine outlet were quantified and characterized by Fourier transformations in the time domain and space domain. It is found that the transport process from the hot-streaks/cold-streaks at the inlet to the outlet is relatively stable. The cold and hot fluid is redistributed in time and space due to the stator and rotor blades, in the region with a large parameter gradient at the inlet, strong unsteady temperature field and composition field appear. The distribution of the exhaust gas composition has a stronger correlation with the inlet temperature distribution and is less susceptible to interference.

Effect of long service on the fine structure of the surface of gas turbine engine rotor blades

1977 ◽  
Vol 9 (10) ◽  
pp. 1257-1261
Author(s):  
O. I. Marusii ◽  
Yu. I. Koval' ◽  
E. N. Kaspruk ◽  
V. N. Torgov
Keyword(s):  
Fine Structure ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Turbine Engine ◽  
Engine Rotor

Rational Design of Gas Turbine Engine Compressor to Provide the Required Dynamic Strength Level of Rotor Blades

2016 ◽  
Author(s):  
Daria Kolmakova ◽  
Grigorii Popov ◽  
Aleksandr Shklovets ◽  
Aleksandr Ermakov
Keyword(s):  
Gas Turbine ◽  
Rational Design ◽  
Gas Flow ◽  
Dynamic Strength ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Dynamic Stresses ◽  
Turbine Engine ◽  
Acceptable Method ◽  
Flow Oscillations

Compressors of gas turbine engines often operate under the conditions of uneven gas flow. Oscillations of the blades occur under the influence of circumferential flow unevenness. The goal of the research was to find an acceptable method of reducing the level of dynamic stresses in the rotor blades. Motivation for the study was the problem of destruction of rotor blades of the last stage of Intermediate Pressure Compressor (IPC) which has been designed and produced at JSC “Kuznetsov” (Russia). The source of circumferential flow unevenness was middle annular frame located downstream the IPC. Seven struts with different maximum thickness are arranged irregularly in support passage. The first approaches propose to reduce the dynamic stresses in blades by detuning the blades from the dangerous harmonic due to changes in their natural frequency. The next two consist in reducing the circumferential unevenness of flow. Thus, this study gives the ideas about methods of improving the dynamic strength of rotor blades of gas turbine engine compressors. On the basis of existing conditions (under development or existing compressor) it allows the selection of the most suitable method for reducing dynamic stresses.

scholarly journals Air starting system of small-size gas turbine engine

2016 ◽  
pp. 61-66
Author(s):  
A. I. Kalinichenko
Keyword(s):  
Gas Turbine ◽  
Unmanned Aerial Vehicle ◽  
Experimental Studies ◽  
Turbine Rotor ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Compressed Air ◽  
Turbine Engine ◽  
Aerial Vehicle

To meet the requirements for starting a mid-flight (GTE) of a reusable unmanned aerial vehicle (UAV), we developed an air starting system according to the scheme with the direct feed of compressed air to the turbine rotor blades. The system is an alternative to the commonly used powder or electrical starting systems of a small-size GTE of UAVs. The paper gives the results of experimental studies to determine the reliable starting feasibility and methods for determining the parameters required for starting the GTE of UAVs.

Novel resistor-capacitor (RC) network-based capacitance signal conditioning circuit for tip clearance measurement on gas turbine engine

2019 ◽  
Vol 234 (2) ◽  
pp. 342-360
Author(s):  
TN Satish ◽  
A Vivek ◽  
SN Anagha ◽  
ANV Rao ◽  
G Uma ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Direct Current ◽  
Gas Turbines ◽  
Signal To Noise Ratio ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Tip Clearance ◽  
Turbine Engine ◽  
Blade Tip ◽  
Conditioning Circuit

Blade tip clearance is a critical engine health parameter measured on gas turbines. Increase in tip clearance results in decreased efficiency, whereas with decrease in clearance due to thermal and centrifugal loads, rotor blades might rub the engine case. Various sensing techniques are being used, among them, capacitance-based systems are widely used by many engine houses. Among the capacitance conditioning circuits, resistor-capacitor series network-based circuits are simple to implement but pose many challenges during practical development. During the current work, the authors have designed a novel capacitance conditioning circuit combining resistor-capacitor series network, instrumentation amplifiers, and direct current–direct current converters. Performance of the developed capacitance conditioning electronics was evaluated through lab testing and tip clearance measurement on fan stage of an aero gas turbine engine. The prototype conditioner circuit has efficiently conditioned and resolved small capacitances varying from 1.25 pF to 0.00413 pF for running clearances between 0.4 mm and 3 mm, respectively. The developed electronics produced high output with signal-to-noise ratio of 58.1 dB, resolution of 2.5 µm, bandwidth of about 700 kHz, and an accuracy of about 98%. This development has culminated towards miniaturization of the total electronics and has the potential to get developed as smart capacitance sensor. This paper explains the practical aspects and challenges involved while designing and developing such practical conditioning circuits.

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