Redesign of an 11-Stage Axial Compressor for Industrial Gas Turbine

2005 ◽  
Author(s):  
Koji Terauchi ◽  
Daisuke Kariya ◽  
Seiichirou Maeda ◽  
Kenichirou Yoshiura
Keyword(s):  
Gas Turbine ◽  
Axial Compressor ◽  
Engine Test ◽  
Test Results ◽  
Design Value ◽  
Cfd Analyses ◽  
Industrial Gas Turbine

Outlined in this paper are the details of redesign of an 11-stage axial compressor for 18MW class industrial gas turbine. Although the design value of adiabatic efficiency is 85%, the efficiency achieved in the prototype engine test was 1 point short of the target. According to the test results and CFD analyses, it was estimated that the stage mismatching due to an excessive work of intermediate stages was a major cause of the losses. To improve the matching, redesign of airfoils were carried out to some blades and vanes. The results of Multistage CFD showed that the matching was improved and the efficiency was increased, which was also confirmed by the engine test.

Enhancements to the Load Acceptance and Rejection Capability of a High Pressure Aeroderivative Engine

2007 ◽  
Author(s):  
Brian Price ◽  
Louis Demers ◽  
Jean-Francois Lebel ◽  
Sylvain Bonneville
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Thermodynamic Model ◽  
Power Imbalance ◽  
Engine Test ◽  
Test Results ◽  
Control Software ◽  
Acceptable Range ◽  
Rapid Transients ◽  
Industrial Gas Turbine

This paper describes improvements to the control of a high pressure, aeroderivative industrial gas turbine in order to better accommodate rapid load changes. In such circumstances it is important to maintain the speed of the driven equipment within an acceptable range. This can require the gas turbine to quickly adjust to the new load, to minimize the power imbalance, which is the cause of the speed variation. The paper describes the theory behind control schedules required to achieve this, and how they relate to avoiding surge, flameout or instability, while minimizing speed variations of the driven equipment. A whole engine thermodynamic model coupled to the control software was used to simulate the engine response during these rapid transients. The features of this model are described. The model allowed optimization of the control software in advance of the engine test. Results of whole engine tests are presented and compared to the model; and the types of load steps that remain most challenging are highlighted. The resulting capability remains partly determined by the specifics of the application, for example the inertia of the driven equipment, the nominal speed of operation, and the allowable speed variations. The effects of these can be predicted using the model and are discussed.

scholarly journals Study on the Turbine Vane and Blade for a 1500°C Class Industrial Gas Turbine

1993 ◽  
Author(s):  
S. Amagasa ◽  
K. Shimomura ◽  
M. Kadowaki ◽  
K. Takeishi ◽  
H. Kawai ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Film Cooling ◽  
High Efficiency ◽  
Development Program ◽  
Test Results ◽  
Directionally Solidified ◽  
Barrier Coating ◽  
Turbine Vane ◽  
Nickel Base ◽  
Industrial Gas Turbine

This paper describes the summary of a three year development program for the 1st stage stationary vane and rotating blade for the next generation, 1500°C Class, high efficiency gas turbine. In such a high temperature gas turbine, the 1st turbine vane and blade are the most important hot parts. Full coverage film cooling (FCFC) is adopted for the cooling scheme, and directionally solidified (DS) nickel base super-alloy and thermal barrier coating (TBC) will be used to prolong the creep and thermal fatigue life. The concept of the cooling configuration, fundamental cascade test results and material test results will be presented.

Failure Investigation of 1st Stage Buckets From Frame 3002, 10 MW Gas Turbine Unit

2011 ◽  
Author(s):  
Girish M. Shejale ◽  
David Ross
Keyword(s):  
Gas Turbine ◽  
Test Results ◽  
High Carbon ◽  
High Carbon Content ◽  
Metallurgical Investigation ◽  
Root Cause ◽  
Failure Investigation ◽  
Surface Failure ◽  
Grain Boundary Embrittlement ◽  
Industrial Gas Turbine

The 1st stage buckets in Frame 3002, 10 MW industrial gas turbine experienced premature failures. The buckets failed unexpectedly much earlier than the designed bucket life. Bucket material is Inconel 738, with platinum-aluminized coating on the surface. Failure investigation of the buckets was performed to know the root cause of the failure. The failure investigation primarily comprised of metallurgical investigation. The results of the metallurgical investigation were co-related with the unit operational history. This paper provides an overview of 1st stage buckets investigation. The metallurgical investigation performed concluded prime failure mechanism due to high carbon content of bucket material and improper heat treatment. The bucket coating was initially damaged during the first loading and fracture occurred due to grain boundary embrittlement in short span of service. The metallurgical tests performed included Visual inspection, Scanning Electron Microscopy (SEM), Energy Dispersive Analysis of X-ray (EDS), Chemical analysis, Tensile test and Hardness survey. The test results, discussions and conclusions are presented in this paper.

Improvement of the aerodynamic parameters of a 16-stage axial compressor for industrial gas turbine power unit

2021 ◽  
Author(s):  
Grigorii M. Popov ◽  
Maxim Miheev ◽  
Vasilii M. Zubanov ◽  
Oleg Baturin ◽  
Evgenii Goriachkin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Axial Compressor ◽  
Aerodynamic Parameters ◽  
Industrial Gas Turbine

Structural Design and High-Pressure Test of a Ceramic Combustor for 1500°C Class Industrial Gas Turbine

1997 ◽  
Vol 119 (3) ◽  
pp. 506-511 ◽  
Author(s):  
I. Yuri ◽  
T. Hisamatsu ◽  
K. Watanabe ◽  
Y. Etori
Keyword(s):  
Fracture Toughness ◽  
High Pressure ◽  
Gas Turbine ◽  
Structural Design ◽  
Metal Structure ◽  
Combustion Efficiency ◽  
Test Results ◽  
Industrial Gas Turbine ◽  
Hybrid Ceramic ◽  
Load Conditions

A ceramic combustor for a 1500°C, 20 MW class industrial gas turbine was developed and tested. This combustor has a hybrid ceramic/metal structure. To improve the durability of the combustor, the ceramic parts were made of silicon carbide (SiC), which has excellent oxidation resistance under high-temperature conditions as compared to silicon nitride (Si3N4), although the fracture toughness of SiC is lower than that of Si3N4. Structural improvements to allow the use of materials with low fracture toughness were made to the fastening structure of the ceramic parts. Also, the combustion design of the combustor was improved. Combustor tests using low-Btu gaseous fuel of a composition that simulated coal gas were carried out under high pressure. The test results demonstrated that the structural improvements were effective because the ceramic parts exhibited no damage even in the fuel cutoff tests from rated load conditions. It also indicated that the combustion efficiency was almost 100 percent even under part-load conditions.

scholarly journals Axial compressor fouling detection for gas turbine driven gas compression unit

2019 ◽  
Vol 15 (3) ◽  
pp. 1257
Author(s):  
Nurlan Batayev
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Power Plants ◽  
Detection System ◽  
Axial Compressor ◽  
Compressor Blades ◽  
Exhaust Temperature ◽  
Gas Compression ◽  
Compressor Power ◽  
Industrial Gas Turbine

<span>One of the main reasons of the performance degradation of gas turbines is the axial compressor fouling due to air pollutants. Considering the fact that the fouling leads to high consumption of fuel, reducing of the axial compressor’s discharge air pressure and increasing of the exhaust temperature, thus designing a compressor degradation detection system will allow prevent such issues. Many gas turbine plants lose power due to dirty axial compressor blades, which can add up to 4% loss of power. In case of power plants, the power loosing could be observed by less megawatts produced by generator. But in case of gas compression stations the effect of power loosing could not be quickly detected, because there is not direct measurement of the discharge power produced by gas turbine. This article represents technique for detection of gas turbine axial compressor degradation in case of gas turbine driven natural gas compression units. Calculation of the centrifugal gas compressor power performed using proven methodology. Approach for evaluation of the gas turbine performance based on machine learning prediction model is shown.  Adequacy of the model has been made to three weeks’ operation data of the 10 Megawatt class industrial gas turbine.</span>

scholarly journals Loss in Axial Compressor Bleed Systems

2019 ◽  
Author(s):  
S. D. Grimshaw ◽  
J. Brind ◽  
G. Pullan ◽  
R. Seki
Keyword(s):  
Gas Turbine ◽  
Control Volume ◽  
Axial Compressor ◽  
Thermodynamic Cycle ◽  
Loss Coefficient ◽  
Dynamic Head ◽  
Definition Of ◽  
Gas Turbine Compressor ◽  
Industrial Gas Turbine ◽  
Loss Mechanisms

Abstract Loss in axial compressor bleed systems is quantified, and the loss mechanisms identified, in order to determine how efficiency can be improved. For a given bleed air pressure requirement, reducing bleed system loss allows air to be bled from further upstream in the compressor, with benefits for the thermodynamic cycle. A definition of isentropic efficiency which includes bleed flow is used to account for this. Two cases with similar bleed systems are studied: a low-speed, single-stage research compressor and a large industrial gas turbine high-pressure compressor. A new method for characterising bleed system loss is introduced, using research compressor test results as a demonstration case. A loss coefficient is defined for a control volume including only flow passing through the bleed system. The coefficient takes a measured value of 95% bleed system inlet dynamic head, and is shown to be a weak function of compressor operating point and bleed rate, varying by ±2.2% over all tested conditions. This loss coefficient is the correct non-dimensional metric for quantifying and comparing bleed system performance. Computations of the research compressor and industrial gas turbine compressor identify the loss mechanisms in the bleed system flow. In both cases, approximately two-thirds of total loss is due to shearing of a high-velocity jet at the rear face of the bleed slot, one quarter is due to mixing in the plenum chamber and the remainder occurs in the off-take duct. Therefore, the main objective of a designer should be to diffuse the flow within the bleed slot. A redesigned bleed slot geometry is presented that achieves this objective and reduces the loss coefficient by 31%.

scholarly journals Inter-Stage Dynamic Performance of an Axial Compressor of a Twin-Shaft Industrial Gas Turbine

Machines ◽  
2020 ◽  
Vol 8 (4) ◽  
pp. 83
Author(s):  
Samuel Cruz-Manzo ◽  
Senthil Krishnababu ◽  
Vili Panov ◽  
Chris Bingham
Keyword(s):  
Gas Turbine ◽  
Dynamic Performance ◽  
Axial Compressor ◽  
Modeling Framework ◽  
Axial Compressors ◽  
Stage Performance ◽  
Compressor Map ◽  
Stage Characteristic ◽  
Industrial Gas Turbine ◽  
Semi Empirical

In this study, the inter-stage dynamic performance of a multistage axial compressor is simulated through a semi-empirical model constructed in the Matlab Simulink environment. A semi-empirical 1-D compressor model developed in a previous study has been integrated with a 0-D twin-shaft gas turbine model developed in the Simulink environment. Inter-stage performance data generated through a high-fidelity design tool and based on throughflow analysis are considered for the development of the inter-stage modeling framework. Inter-stage performance data comprise pressure ratio at various speeds with nominal variable stator guide vane (VGV) positions and with hypothetical offsets to them with respect to the gas generator speed (GGS). Compressor discharge pressure, fuel flow demand, GGS and power turbine speed measured during the operation of a twin-shaft industrial gas turbine are considered for the dynamic model validation. The dynamic performance of the axial-compressor, simulated by the developed modeling framework, is represented on the overall compressor map and individual stage characteristic maps. The effect of extracting air through the bleed port in the engine center-casing on transient performance represented on overall compressor map and stage performance maps is also presented. In addition, the dynamic performance of the axial-compressor with an offset in VGV position is represented on the overall compressor map and individual stage characteristic maps. The study couples the fundamental principles of axial compressors and a semi-empirical modeling architecture in a complementary manner. The developed modeling framework can provide a deeper understanding of the factors that affect the dynamic performance of axial compressors.

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.

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