Impact of the Inflow Conditions on the Heavy-Duty Gas Turbine Exhaust Diffuser Performance

2011 ◽  
Vol 134 (4) ◽  
Author(s):  
Vladimir Vassiliev ◽  
Stefan Irmisch ◽  
Samer Abdel-Wahab ◽  
Andrey Granovskiy
Keyword(s):  
Pressure Distribution ◽  
Gas Turbines ◽  
Field Measurements ◽  
Heavy Duty ◽  
Flow Angle ◽  
Heavy Duty Gas Turbine ◽  
Gas Turbine Exhaust ◽  
The Impact ◽  
Inflow Conditions ◽  
Turbine Exhaust

The flow in exhaust diffusers along with the channel geometry strongly depends on the inflow conditions, including Mach number level, total pressure distribution, flow angle, and turbulence. In the first part of this paper, the impact of these parameters is analyzed using computational fluid dynamics, experimental data from the test rig, and field measurements. A widespread opinion is that the optimal condition for the diffuser is an axial uniform inflow. However, it is shown in this paper that nonuniform pressure distribution compared with a uniform one can lead to better diffuser performance and that a moderate residual swirl can improve the performance as well. In the second part of this paper, the minimization of exhaust losses in heavy-duty gas turbines is discussed and illustrated by two practical examples.

Impact of the Inflow Conditions on the Heavy-Duty Gas Turbine Exhaust Diffusers Performance

2010 ◽  
Author(s):  
Vladimir Vassiliev ◽  
Stefan Irmisch ◽  
Samer Abdel-Wahab ◽  
Andrey Granovskiy
Keyword(s):  
Pressure Distribution ◽  
Gas Turbines ◽  
Field Measurements ◽  
Heavy Duty ◽  
Flow Angle ◽  
Heavy Duty Gas Turbine ◽  
Gas Turbine Exhaust ◽  
The Impact ◽  
Inflow Conditions ◽  
Turbine Exhaust

The flow in exhaust diffusers along with the channel geometry strongly depends on the inflow conditions, including Mach number level, total pressure distribution, flow angle, and turbulence. In the first part of this paper, the impact of these parameters is analyzed using CFD, experimental data from the test rig and field measurements. A widespread opinion is that the optimal condition for the diffuser is an axial uniform inflow. However, it is shown in this paper that non-uniform pressure distribution as compared to a uniform one can lead to better diffuser performance and that moderate residual swirl can improve the performance as well. In the second part of the paper, the minimization of exhaust losses in heavy-duty gas turbines is discussed and illustrated by two practical examples.

scholarly journals A Different Approach to Gas Turbine Exhaust Silencing

1974 ◽  
Author(s):  
Marv Weiss
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Operating Conditions ◽  
Heavy Duty ◽  
Unique Method ◽  
Acoustic Testing ◽  
Gas Turbine Exhaust ◽  
Attenuation Values ◽  
Turbine Exhaust

A unique method for silencing heavy-duty gas turbines is described. The Switchback exhaust silencer which utilizes no conventional parallel baffles has at operating conditions measured attenuation values from 20 dB at 63 Hz to 45 dB at higher frequencies. Acoustic testing and analyses at both ambient and operating conditions are discussed.

scholarly journals Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines: Part I — Design and Optimization

1999 ◽  
Author(s):  
Ulf Köller ◽  
Reinhard Mönig ◽  
Bernhard Küsters ◽  
Heinz-Adolf Schreiber
Keyword(s):  
Gas Turbines ◽  
Superior Performance ◽  
Experimental Investigations ◽  
Heavy Duty ◽  
Flow Angle ◽  
Design And Optimization ◽  
New Family ◽  
Blade Thickness ◽  
Wide Range ◽  
The Impact

A new family of subsonic compressor airfoils, which are characterized by low losses and wide operating ranges, has been designed for use in heavy-duty gas turbines. In particular the influence of the higher airfoil Reynolds numbers compared to aeroengine compressors and the impact of these differences on the location of transition are taken into account. The design process itself is carried out by the combination of a geometrical code for the airfoil description, with a blade-to-blade solver and a numerical optimization algorithm. The optimization process includes the design-point losses for a specified Q3D flow problem and the off-design performance for the entire operating range. The family covers a wide range of inlet flow angle, Mach number, flow turning, blade thickness, solidity and AVDR in order to consider the entire range of flow conditions which occur in practical compressor design. The superior performance of the new airfoil family is demonstrated by a comparison with conventional controlled diffusion airfoils (CDA). The advantage in performance has been confirmed by detailed experimental investigations, which will be presented in Part II of the paper. This leads to the conclusion that CDA airfoils which have been primarily developed for aero engine applications are not the optimum solution, if directly transferred to heavy-duty gas turbines. A significant improvement in compressor efficiency is possible, if the new profiles are used instead of conventional airfoils.

scholarly journals Design of Gas Turbine Exhaust Heat Recovery Boiler Systems

1984 ◽  
Author(s):  
V. L. Eriksen ◽  
J. M. Froemming ◽  
M. R. Carroll
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Heat Recovery ◽  
Performance Criteria ◽  
Exhaust Heat ◽  
Recovery Boilers ◽  
Gas Turbine Exhaust ◽  
The Impact ◽  
Exhaust Heat Recovery ◽  
Turbine Exhaust

Heat recovery boilers utilizing the exhaust from gas turbines continue to be viable as industrial cogeneration systems. This paper outlines the types of heat recovery boilers available for use with gas turbines (1–100 MW). It discusses the design and performance criteria for both unfired and supplementary fired gas turbine exhaust heat recovery boilers of single and multiple pressure levels. Equations to assist in energy balances are included along with design features of heat recovery system components. The economic incentive to achieve the maximum practical heat recovery versus the impact on boiler design and capital cost are examined and discussed. It is intended that the information presented in this paper will be of use to individuals who are not intimately familiar with gas turbine heat recovery systems so that they can better specify and evaluate potential systems.

1999 Turbomachinery Committee Best Paper Award: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines— Part I: Design and Optimization

1999 ◽  
Vol 122 (3) ◽  
pp. 397-405 ◽  
Author(s):  
Ulf Ko¨ller ◽  
Reinhard Mo¨nig ◽  
Bernhard Ku¨sters ◽  
Heinz-Adolf Schreiber
Keyword(s):  
Gas Turbines ◽  
Superior Performance ◽  
Experimental Investigations ◽  
Heavy Duty ◽  
Flow Angle ◽  
Design And Optimization ◽  
New Family ◽  
Blade Thickness ◽  
Wide Range ◽  
The Impact

A new family of subsonic compressor airfoils, which are characterized by low losses and wide operating ranges, has been designed for use in heavy-duty gas turbines. In particular the influence of the higher airfoil Reynolds numbers compared to aeroengine compressors and the impact of these differences on the location of transition are taken into account. The design process itself is carried out by the combination of a geometric code for the airfoil description, with a blade-to-blade solver and a numerical optimization algorithm. The optimization process includes the design-point losses for a specified Q3D flow problem and the off-design performance for the entire operating range. The family covers a wide range of inlet flow angle, Mach number, flow turning, blade thickness, solidity and AVDR in order to consider the entire range of flow conditions that occur in practical compressor design. The superior performance of the new airfoil family is demonstrated by a comparison with conventional controlled diffusion airfoils (CDA). The advantage in performance has been confirmed by detailed experimental investigations, which will be presented in Part II of the paper. This leads to the conclusion that CDA airfoils that have been primarily developed for aeroengine applications are not the optimum solution, if directly transferred to heavy-duty gas turbines. A significant improvement in compressor efficiency is possible, if the new profiles are used instead of conventional airfoils. [S0889-504X(00)02102-4]

Thermal and Stress Field Analysis in Heavy-Duty Gas Turbine Exhaust System

2012 ◽  
Vol 516-517 ◽  
pp. 688-691 ◽  
Author(s):  
Rui Zhu ◽  
Jian Xing Ren ◽  
Fang Qin Li ◽  
Hong Du Zhang ◽  
Yun Tang
Keyword(s):  
Stress Field ◽  
Gas Turbine ◽  
Thermal Field ◽  
Exhaust System ◽  
Field Analysis ◽  
Distribution Characteristics ◽  
Heavy Duty ◽  
Heavy Duty Gas Turbine ◽  
Gas Turbine Exhaust ◽  
Turbine Exhaust

Heavy-duty gas turbine is used widely in power generation industry for many advantages. Gas turbine exhaust system is an important component of the gas turbine. The work to study the exhaust system was less in the past. In fact, structure design of the exhaust system has important influence on performance and life of the gas turbine. In this paper, the three-dimensional structural model of gas turbine exhaust system is built, the thermal field and stress field for the exhaust system are analyzed by using finite element method (FEM). The maximum stress and distribution characteristics of stress field, the highest temperature and distribution characteristics of thermal field in the exhaust system are computed. These provide a reliable basis for reasonable design and safety evaluation of the exhaust system in gas turbine.

Impact of Different Film-Cooling Modes at Trailing Edge on the Aerodynamic Performance of Heavy Duty Gas Turbine Cascade

2011 ◽  
Vol 84-85 ◽  
pp. 259-263
Author(s):  
Xun Liu ◽  
Song Tao Wang ◽  
Xun Zhou ◽  
Guo Tai Feng
Keyword(s):  
Gas Turbine ◽  
Film Cooling ◽  
Large Mass ◽  
Turbine Cascade ◽  
Heavy Duty ◽  
Trailing Edge ◽  
Central Difference ◽  
Adiabatic Effectiveness ◽  
Heavy Duty Gas Turbine ◽  
The Impact

In this paper, the trailing edge film cooling flow field of a heavy duty gas turbine cascade has been studied by central difference scheme and multi-block grid technique. The research is based on the three-dimensional N-S equation solver. By way of analysis of the temperature field, the distribution of profile pressure, and the distribution of film-cooling adiabatic effectiveness in the region of trailing edge with different cool air injection mass and different angles, it is found that the impact on the film-cooling adiabatic effectiveness is slightly by changing the injection mass. The distribution of profile pressure dropped intensely at the pressure side near the injection holes line with the large mass cooling air. The cooling effect is good in the region of trailing edge while the injection air is along the direction of stream.

Experience With Large Heavy-Duty Gas Turbine Rotors

1981 ◽  
Author(s):  
O. R. Schmoch ◽  
B. Deblon
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Rotor ◽  
Strength Properties ◽  
Operating Conditions ◽  
Material Strength ◽  
Heavy Duty ◽  
Turbine Rotors ◽  
Heavy Duty Gas Turbine ◽  
Response To Temperature

The peripheral speeds of the rotors of large heavy-duty gas turbines have reached levels which place extremely high demands on material strength properties. The particular requirements of gas turbine rotors, as a result of the cycle, operating conditions and the ensuing overall concepts, have led different gas turbine manufacturers to produce special structural designs to resolve these problems. In this connection, a report is given here on a gas turbine rotor consisting of separate discs which are held together by a center bolt and mutually centered by radial serrations in a manner permitting expansion and contraction in response to temperature changges. In particular, the experience gained in the manufacture, operation and servicing are discussed.

Uncertainty Analysis of Inflow Conditions on an HPT Gas Turbine Nozzle: Effect on Particle Deposition

2020 ◽  
Author(s):  
R. Friso ◽  
N. Casari ◽  
M. Pinelli ◽  
A. Suman ◽  
F. Montomoli
Keyword(s):  
Gas Turbine ◽  
Energy Efficient ◽  
Gas Turbines ◽  
Particle Deposition ◽  
Operating Conditions ◽  
Wide Range ◽  
And Performance ◽  
Gas Turbine Nozzle ◽  
The Impact ◽  
Inflow Conditions

Abstract Gas turbines (GT) are often forced to operate in harsh environmental conditions. Therefore, the presence of particles in their flow-path is expected. With this regard, deposition is a problem that severely affects gas turbine operation. Components’ lifetime and performance can dramatically vary as a consequence of this phenomenon. Unfortunately, the operating conditions of the machine can vary in a wide range, and they cannot be treated as deterministic. Their stochastic variations greatly affect the forecasting of life and performance of the components. In this work, the main parameters considered affected by the uncertainty are the circumferential hot core location and the turbulence level at the inlet of the domain. A stochastic analysis is used to predict the degradation of a high-pressure-turbine (HPT) nozzle due to particulate ingestion. The GT’s component analyzed as a reference is the HPT nozzle of the Energy-Efficient Engine (E3). The uncertainty quantification technique used is the probabilistic collocation method (PCM). This work shows the impact of the operating conditions uncertainties on the performance and lifetime reduction due to deposition. Sobol indices are used to identify the most important parameter and its contribution to life. The present analysis enables to build confidence intervals on the deposit profile and on the residual creep-life of the vane.

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