scholarly journals Generating axial compressor maps to zero speed

2020 ◽  
pp. 095765092097605
Author(s):  
Luis E Ferrer-Vidal ◽  
Vassilios Pachidis ◽  
Richard J Tunstall
Keyword(s):  
Gas Turbines ◽  
Axial Compressor ◽  
Sensitivity Study ◽  
Generation Process ◽  
Performance Models ◽  
Start Up ◽  
Map Generation ◽  
Industrial Gas Turbines ◽  
Main Components ◽  
Aviation Engines

Gas turbine performance models typically rely on component maps to characterize engine component performance throughout the operational regime. For the sub-idle case, the lack of reliable rig test data or inability to run design codes far from design conditions entails that component maps have to be generated from the extrapolation of existing data at higher speeds. This undermines the accuracy of whole-engine sub-idle performance models, at times impacting engine development and certification of aviation engines and the accuracy of start-up performance prediction in industrial gas turbines. One of the main components driving this issue is the core compression system, which can present operability concerns during light-up and which also sets the combustor airflow required for ignition. This paper presents, discusses, and draws on previous approaches to describe a method enabling the creation of sub-idle compressor maps from analytical and physical grounds. The method relies on the calculation of zero-speed and torque-free lines to generate a map down to zero speed along with analytical interpolation. A method for the interpolation process is described. A sensitivity study is carried out to assess the effects that different elements of the map generation process may have on the accuracy of the resulting performance calculation. Overall, a method for the generation of accurate, consistent maps from limited geometry data is identified.

scholarly journals Considerations on Axial Compressor Bleed for Sub-Idle Performance Models

2020 ◽  
Author(s):  
Ferran Roig Tió ◽  
Luis E. Ferrer-Vidal ◽  
Hasani Azamar Aguirre ◽  
Vassilios Pachidis
Keyword(s):  
Flow Analysis ◽  
Axial Compressor ◽  
Engine Performance ◽  
Analysis Tool ◽  
Performance Models ◽  
Performance Modelling ◽  
Start Up ◽  
Considerable Impact ◽  
Aero Engines ◽  
Analytical Approaches

Abstract The trend towards increased bypass ratio and reduced core size in civil aero-engines puts a strain on ground-start and relight capability, prompting renewed interest in sub-idle performance modelling. While a number of studies have looked at some of the broad performance modelling issues prevalent in this regime, the effects that bleed can have on sub-idle performance have not been addressed in the literature. During start-up and relight, the unknown variation in bleed flows through open handling bleed valves can have a considerable impact on the compressor’s operating line. This paper combines experimental, numerical and analytical approaches to look at the effect that sub-idle bleed flows have on predicted start-up operating lines, along with their effect on compressor characteristics. Experimental whole-engine data along with a purpose-built core-flow analysis tool are used to assess the effect of bleed model uncertainty on engine performance models. An experimental rig is used to assess the effects of reverse bleed on compressor characteristics and measurements are compared against numerical results. Several strategies for the generation of sub-idle maps including bleed effects are investigated.

An analytical approach to predicting particle deposit by fouling in the axial compressor of the industrial gas turbine

2005 ◽  
Vol 219 (3) ◽  
pp. 203-212 ◽  
Author(s):  
T W Song ◽  
J L Sohn ◽  
T S Kim ◽  
J H Kim ◽  
S T Ro
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Particle Deposition ◽  
Axial Compressor ◽  
Design Parameters ◽  
Compressor Blades ◽  
Particle Distributions ◽  
Industrial Gas Turbines ◽  
Industrial Gas Turbine ◽  
Physical Phenomena

The gas turbine performance deteriorates with increased operating hours. Fouling in the axial compressor is an important factor for the performance degradation of gas turbines. Airborne particles entering the compressor with the air adhere to the blade surface and result in the change of the blade shape, which directly influences the compressor performance. It is difficult to exactly understand the mechanism of compressor fouling because of its slow growth and different length scales of compressor blades. In this study, an analytical method to predict the particle motion in the axial compressor and the characteristics of particle deposition onto blade is proposed as an approach to investigating physical phenomena of fouling in the axial compressor of industrial gas turbines. Calculated results using the proposed method and comparison with measured data demonstrate the feasibility of the model. It was also found that design parameters of the axial compressor such as chord length, solidity, and number of stages are closely related to the fouling phenomena. Likewise, the particle size and patterns of particle distributions are also important factors related to fouling phenomena in the axial compressor.

A Method to Evaluate the Heat Exchanger Retrofit for Industrial Gas Turbines Based on Technical and Economic Perspective

2016 ◽  
Author(s):  
Waleed Al-Busaidi ◽  
Pericles Pilidis
Keyword(s):  
Heat Exchanger ◽  
Gas Turbines ◽  
Economic Value ◽  
Integrated Approach ◽  
Sensitivity Study ◽  
Economic Perspective ◽  
Tubular Heat Exchanger ◽  
Utilization Factor ◽  
Exhaust Heat ◽  
Industrial Gas Turbines

One way to enhance the thermal efficiency of simple gas turbines cycle is by using recuperation to recover some of the exhaust heat. Therefore, this study aims to introduce a new integrated approach to evaluate the techno-economic value of recuperator retrofit on existing industrial gas turbines. The original engines are designed for combined cycles so that the pressure ratios are moderate to secure suitable exhaust temperatures. The developed model is described and implemented for two gas turbines, and the obtained characteristics are evaluated against the actual data. This approach will help the users to select the suitable gas turbine models with favorable recuperator characteristics based on a technical and economic perspective. Besides, the performance results are used to select the optimum thermodynamic and geometrical characteristics of TEMA tubular heat exchanger so that the generated design alternatives are optimized using multi-decision process principle in order to ensure the highest techno-economic value. One of the unique features of the new method is that it depends only on the velocity of recuperator streams to derive the rest of the heat exchanger design and performance characteristics. Moreover, this paper includes a sensitivity study to investigate the effects of power setting, utilization factor and operation availability on the selected recuperator features.

Flexible Spacers Compressor Stator Blades for Heavy Industrial Gas Turbines Model 7EA

2003 ◽  
Author(s):  
Steve Ingistov
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Field Experience ◽  
Axial Compressor ◽  
Heavy Duty ◽  
Combustion Gas ◽  
Mechanical Integrity ◽  
Industrial Gas Turbines ◽  
Last Stage

This paper describes efforts to upgrade the mechanical integrity of axial compressor stator blades. The blades under discussion are part of an axial compressor of a heavy duty industrial Combustion Gas Turbine (CGT) made by GE, frame No. 7, model EA. The axial compressor stator blades, in the later stages of compression, are kept in required position by spacers or shims shaped to match the root profile of the blades. These spacers/shims may be as thick as 1/4 of an inch and as thin as 1/32 of an inch. These spacers/shims tend to wiggle out of the slots and eventually liberate themselves from the stator. This paper introduces a proposed solution to minimize liberation of the spacer/shims by introduction of flexible spacers/shims. This paper also describes field experience with loss of the stator blades in the last stage of compression, due to aerodynamic disturbances.

A Gas Turbine Cogeneration Plant With a Gross Electrical Efficiency of Over 50%

1986 ◽  
Author(s):  
A. L. Broekhuizen ◽  
R. R. van Lavieren ◽  
P. Kamminga
Keyword(s):  
Power Generation ◽  
Gas Turbines ◽  
High Efficiency ◽  
District Heating ◽  
Performance Tests ◽  
Steam Turbines ◽  
Electrical Efficiency ◽  
Start Up ◽  
Cogeneration System ◽  
Main Components

District heating projects in the Netherlands are cogeneration projects with special emphasis on high-efficiency power generation. Together with their customer N.V. IJsselcentrale, Thomassen International B.V., designed a cogeneration system based on gas and steam turbines. The system has following main features: - the gross electrical efficiency of the system is over 50%, which is a highly remarkable achievement in power generation - the main components, 2 gas turbines, a steam turbine and one generator are mounted in line on a single shaft. Successful start up of the plant happened in November 1985, performance tests have shown the target of power generation with an efficiency of 50% is met.

Rotor Components Life Evaluation Validated by Field Operation Data

2010 ◽  
Author(s):  
Mauro Maccio` ◽  
Adelmo Rebizzo ◽  
Laura Traversone ◽  
Luca Bordo
Keyword(s):  
Gas Turbines ◽  
Life Prediction ◽  
Fem Analysis ◽  
Experimental Tests ◽  
Life Extension ◽  
Life Evaluation ◽  
Start Up ◽  
Life Analysis ◽  
Main Components ◽  
Turbine Model

Since E class gas turbines manufactured by Ansaldo Energia are approaching their typical life limits for their planned life cycle (100.000 EOH or 3000 start up) a detailed approach has been developed and carried out in order to guarantee main components for a life extension. This approach has become very important in order to overcome the adopted conservative design approach developed in the seventies taking into account an “ideal reference engine” and therefore focusing on the real engine featured by its history and its component peculiarity. This paper presents a complete life analysis approach which includes experimental tests, FEM analysis and life prediction for the gas turbine model AE94.2, using the 170MW-class 3000 rpm.

Fuel System Suitability Considerations for Industrial Gas Turbines

2004 ◽  
Vol 126 (1) ◽  
pp. 119-126 ◽  
Author(s):  
F. G. Elliott ◽  
R. Kurz ◽  
C. Etheridge ◽  
J. P. O’Connell
Keyword(s):  
Gas Turbines ◽  
Equations Of State ◽  
Dew Point ◽  
Liquid Fuels ◽  
Physical Parameters ◽  
Special Focus ◽  
Fuel System ◽  
Fuel Gas ◽  
Pressure Drops ◽  
Industrial Gas Turbines

Industrial Gas Turbines allow operation with a wide variety of gaseous and liquid fuels. To determine the suitability for operation with a gas fuel system, various physical parameters of the proposed fuel need to be determined: heating value, dew point, Joule-Thompson coefficient, Wobbe Index, and others. This paper describes an approach to provide a consistent treatment for determining the above physical properties. Special focus is given to the problem of determining the dew point of the potential fuel gas at various pressure levels. A dew point calculation using appropriate equations of state is described, and results are presented. In particular the treatment of heavier hydrocarbons, and water is addressed and recommendations about the necessary data input are made. Since any fuel gas system causes pressure drops in the fuel gas, the temperature reduction due to the Joule-Thompson effect has to be considered and quantified. Suggestions about how to approach fuel suitability questions during the project development and construction phase, as well as in operation are made.

Deformation and Fracture Behaviors in the Freestanding APS-TBC - Effects of Process Parameters and Thermal Exposure

2007 ◽  
Vol 353-358 ◽  
pp. 1935-1938 ◽  
Author(s):  
Yasuhiro Yamazaki ◽  
T. Kinebuchi ◽  
H. Fukanuma ◽  
N. Ohno ◽  
K. Kaise
Keyword(s):  
Mechanical Properties ◽  
Process Parameters ◽  
Gas Turbines ◽  
Thermal Exposure ◽  
Substrate Material ◽  
Process Variables ◽  
Microstructural Investigation ◽  
Deformation And Fracture ◽  
Industrial Gas Turbines ◽  
Tbc Systems

Thermal barrier coatings (TBCs), that reduce the temperature in the underlying substrate material, are an essential requirement for the hot section components of industrial gas turbines. Recently, in order to take full advantage of the potential of the TBC systems, experimental and analytical investigations in TBC systems have been performed. However there is a little information on the deformation behavior of the top coating. In addition, the effects of the thermal exposure and the process parameters on the mechanical properties of the top coating have never been clarified. From these backgrounds, the effects of the process variables in APS and the thermal exposure on the mechanical properties were investigated in order to optimize the APS process of top coatings. The experimental results indicated that the mechanical properties of the APS-TBC, i.e. the tensile strength and the elastic modulus, were significantly changed by the process variables and the long term thermal exposure. The microstructural investigation was also carried out and the relationship between the mechanical properties and the porosity was discussed.

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