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.

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

Performance of Axial-Flow Turbines

1948 ◽  
Vol 159 (1) ◽  
pp. 230-244 ◽  
Author(s):  
D. G. Ainley
Keyword(s):  
Gas Turbine ◽  
Experimental Work ◽  
Gas Flow ◽  
High Efficiency ◽  
Gas Turbine Engine ◽  
Steam Turbines ◽  
Aerodynamic Design ◽  
Turbine Engine ◽  
Turbine Performance ◽  
Economic Operation

The advent of the gas-turbine engine, with its absolute dependence on high component efficiencies for reasonable economic operation, and the necessity for new materials which will withstand high stresses at much greater temperatures than encountered on steam turbines, has led engineers to review the design of turbines closely both from an aerodynamic and a mechanical standpoint: there is still a great deal to be learnt. Reeman† has outlined the present mathematical approach to the design of turbines and surveyed very comprehensively the mechanical problems that are involved. This paper is intended to indicate the manner in which the aerodynamic design of a turbine has developed from that of its steam predecessor and, in particular, surveys some recent experimental work relating to turbine performance. The general aims of the experimental work are to explore the gas-flow processes within a turbine stage, to determine the associate aerodynamic efficiencies, and to gain some understanding of the limitations imposed upon the aerodynamic design of a stage by the necessity for the high efficiency which is required for economic operation of a gas-turbine engine. The data that have so far come to light, though incomplete, illustrate the general overall characteristics of high- and low-reaction turbines, and also the effect that high Mach number or low Reynolds number may have on turbine performance. To conclude the paper, a brief description of the technique adopted for adequate full-scale testing of turbines is presented. This covers the essential points of, power absorption, instrumentation, and safety precaution. The effects of errors in measurements are also discussed.

scholarly journals Theory of gas turbine engine optimal gas generator

2019 ◽  
Vol 18 (2) ◽  
pp. 52-61
Author(s):  
A. V. Grigoriev ◽  
A. A. Kosmatov ◽  
О. A. Rudakov ◽  
A. V. Solovieva
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Flow ◽  
Turbine Blades ◽  
Target Function ◽  
Gas Turbine Engine ◽  
Gas Generator ◽  
Joint Operation ◽  
Turbine Engine ◽  
Wide Range

The article substantiates the necessity of designing an optimal gas generator of a gas turbine engine. The generator is to provide coordinated joint operation of its units: compressor, combustion chamber and compressor turbine with the purpose of reducing the period of development of new products, improving their fuel efficiency, providing operability of the blades of a high-temperature cooled compressor turbine and meeting all operational requirements related to the operation of the optimal combustion chamber including a wide range of stable combustion modes, high-altitude start at subzero air and fuel temperature conditions and prevention of the atmosphere pollution by toxic emissions. Methods of optimizing the parameters of coordinated joint operation of gas generator units are developed. These parameters include superficial flow velocities in the boundary interface cross sections between the compressor and the combustion chamber, as well as between the combustion chamber and the compressor turbine. The effective efficiency of the engine thermodynamic cycle is the optimization target function. The required depth of the turbine blades cooling is a functional constraint evaluated with account for calculations of irregularity and instability of the gas temperature field and the actual flow turbulence intensity at the blades’ inlet. We carried out theoretical analysis of the influence of various factors on the gas flow that causes changes in the flow total pressure in the channels of the gas generator gas dynamic model, i.e. changes in the efficiencies of its units. It is shown that the long period (about five years) of the engine final development time, is due to the necessity to perform expensive full-scale tests of prototypes, in particular, it is connected with an incoordinate assignment in designing the values of the flow superficial velocities in the boundary sections between the gas generator units. Designing of an optimal gas generator is only possible on the basis of an integral mathematical model of an optimal combustion chamber.

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

scholarly journals CHARACTERISTICS OF HEAT TRANSFER IN FIRE TUBE OF MARINE GAS TURBINE ENGINE IN STARTING MODE

2018 ◽  
pp. 66-74
Author(s):  
Yuri Gorjanovich Volodin ◽  
Yury Ivanovich Matveev ◽  
Mikhail Yurievich Khramov
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Heat Flow ◽  
Turbulent Boundary Layer ◽  
Gas Turbine ◽  
Gas Flow ◽  
Experimental Studies ◽  
Gas Turbine Engine ◽  
Working Fluid ◽  
Turbine Engine

The paper presents the results of experimental studies of heat transfer in a cylindrical tube, which is a simulation model of a fire tube. The experiments were performed on a gas-dynamic pipe of open type. The starting mode during operation of the gas turbine engine is one of the main modes in which failures sometimes occur. The failure may occur due to external heat transfer mode, when the thermal parameters of the gas flow exceed the calculated values and there takes place intense local heating of the streamlined surface of the structural element(s) of the engine. Experimental studies were carried out at different intensity of the increasing temperature of the working fluid, which allowed to fix the phenomenon of laminarization of the thermal turbulent boundary layer at the heat flow directed from the gas flow to the channel wall. In the event of laminarization phenomenon, the values of local heat transfer coefficients are reduced by 2.5-3 times. Since the discovery of this phenomenon, it has also been observed in various situations of accelerating the gas flow and even at high degrees of heating of the cylindrical pipe wall under stationary flow conditions. This phenomenon has been recorded for the first time in the non-stationary mode and the specified direction of the heat flow. The temperature head or temperature factor is proposed as a laminarization parameter of a turbulent boundary layer, and the boundary of the laminarization area of a turbulent boundary layer is Δ T ≥ 700 K.

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