Effect of a Gap Between Inner Casing and Stator Blade on Axial Compressor Performance

2010 ◽  
Author(s):  
Changyong Lee ◽  
Jaewook Song ◽  
Sungryong Lee ◽  
Dongmin Hong
Keyword(s):  
Geometric Modeling ◽  
Axial Compressor ◽  
Flow Distribution ◽  
Navier Stokes ◽  
Engine Operation ◽  
Turbine Engine ◽  
Stator Blade ◽  
Compressor Performance ◽  
Industrial Gas Turbine ◽  
Test Result

The small gap at stator hub section of 10-stage axial compressor of small power class industrial gas turbine engine was studied to confirm its effect on compressor analysis result. This gap is allowed for manufactural tolerance and thermal expansion during engine operation. For the convenient purpose of CFD geometric modeling, such gap was simplified and the 3D Navier-Stokes code was used to predict the compressor performance then compared the results with the case without a gap. In the case of calculation without a gap, the performance was estimated to be lower than that of test result. It is because of the presence of 3D separation at hub corner of every stator except on the 1st and 2nd stator. The CFD calculation shows that, with a gap, the stall observed at hub corner vanished and the predicted compressor performance agrees well with the test result. From this, it is concluded that the existence of a gap between inner casing and stator brings a considerable effects on the compressor flow distribution and must be taken into account in the design.

Quick Start of an Industrial Gas Turbine Engine Through the Development of “Silent Start” VGV Schedule

2020 ◽  
Author(s):  
Senthil Krishnababu ◽  
Vili Panov ◽  
Simon Jackson ◽  
Andrew Dawson
Keyword(s):  
Guide Vane ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Rotating Stall ◽  
Rotor Blades ◽  
Start Time ◽  
Turbine Engine ◽  
High Pressure Ratio ◽  
Compressor Map ◽  
Industrial Gas Turbine

Abstract In this paper, research that was carried out to optimise an initial variable guide vane schedule of a high-pressure ratio, multistage axial compressor is reported. The research was carried out on an extensively instrumented scaled compressor rig. The compressor rig tests carried out employing the initial schedule identified regions in the low speed area of the compressor map that developed rotating stall. Rotating stall regions that caused undesirable non-synchronous vibration of rotor blades were identified. The variable guide vane schedule optimisation carried out balancing the aerodynamic, aero-mechanical and blade dynamic characteristics gave the ‘Silent Start’ variable guide vane schedule, that prevented the development of rotating stall in the start regime and removed the non-synchronous vibration. Aerodynamic performance and aero-mechanical characteristics of the compressor when operated with the initial schedule and the optimised ‘Silent Start’ schedule are compared. The compressor with the ‘Silent Start’ variable guide vane schedule when used on a twin shaft engine reduced the start time to minimum load by a factor of four and significantly improved the operability of the engine compared to when the initial schedule was used.

Complex Gas Dynamic Optimization of a Three Spool Axial Compressor of an Industrial Gas Turbine Engine

2019 ◽  
Author(s):  
Grigorii M. Popov ◽  
Igor Egorov ◽  
Dmitrii Dmitriev ◽  
Evgenii S. Goriachkin ◽  
Andrei A. Volkov
Keyword(s):  
Dynamic Optimization ◽  
Axial Compressor ◽  
Operating Conditions ◽  
Specific Task ◽  
Turbine Engine ◽  
Gas Dynamic ◽  
Impressive Result ◽  
Complex Models ◽  
Overall Efficiency ◽  
Industrial Gas Turbine

Abstract The paper provides a description of the algorithm, an example of a specific task, and the results of the optimization of a 15-stage three-spool compressor for a ground-based GTU by the efficiency criteria of the engine. It can be performed by using the proposed algorithm to find such a compressor configuration that will be not just the optimum compressor, but the best option for working as part of the engine under the specified operating conditions and with various types of required restrictions. Using the proposed algorithm, varying only the stagger angles of the profiles, the authors managed to find a way to increase the overall efficiency of the NK-36ST engine by 0.43%. Obviously, it is possible to achieve a more impressive result and at the same time to increase reliability, reduce the weight and cost of the engine by applying more complex models by changing the shape of the blade profiles.

An Analysis of Axial Compressor Fouling and a Blade Cleaning Method

1998 ◽  
Vol 120 (2) ◽  
pp. 256-261 ◽  
Author(s):  
A. P. Tarabrin ◽  
V. A. Schurovsky ◽  
A. I. Bodrov ◽  
J.-P. Stalder
Keyword(s):  
Mathematical Model ◽  
Axial Compressor ◽  
Axial Compressors ◽  
Cleaning Method ◽  
Engine Efficiency ◽  
Calculation Results ◽  
On Line ◽  
Compressor Performance ◽  
High Level ◽  
Industrial Gas Turbine

The paper describes the phenomenon of axial compressor fouling due to aerosols contained in the air. Key parameters having effect on the level of fouling are determined. A mathematical model of a progressive compressor fouling using the stage-by-stage calculation method is developed. Calculation results on the influence of fouling on the compressor performance are presented. A new index of sensitivity of axial compressors to fouling is suggested. The paper gives information about Turbotect’s deposit cleaning method of compressor blading and the results of its application on an operating industrial gas turbine. Regular on-line and off-line washings of the compressor flow path make it possible to maintain a high level of engine efficiency and output.

An Analysis of Axial Compressors Fouling and a Cleaning Method of Their Blading

1996 ◽  
Author(s):  
A. P. Tarabrin ◽  
V. A. Schurovsky ◽  
A. I. Bodrov ◽  
J.-P. Stalder
Keyword(s):  
Mathematical Model ◽  
Axial Compressor ◽  
Axial Compressors ◽  
Cleaning Method ◽  
Engine Efficiency ◽  
Calculation Results ◽  
On Line ◽  
Compressor Performance ◽  
High Level ◽  
Industrial Gas Turbine

The paper describes the phenomenon of axial compressor fouling due to aerosols contained in the air. Key parameters having effect on the level of fouling are determined. A mathematical model of a progressive compressor fouling using the stage-by-stage calculation method is developed. Calculation results on the influence of fouling on the compressor performance are presented. A new index of sensitivity of axial compressors to fouling is suggested. The paper gives information about the Turbotect’s deposit cleaning method of compressor blading and the results of its application on an operating industrial gas turbine. Regular on line and off line washings of compressor flow path make it possible to maintain a high level of engine efficiency and output.

Vorticity Dynamics in Axial Compressor Flow Diagnosis and Design

2008 ◽  
Vol 130 (4) ◽  
Author(s):  
Yantao Yang ◽  
Hong Wu ◽  
Qiushi Li ◽  
Sheng Zhou ◽  
Jiezhi Wu
Keyword(s):  
Pressure Ratio ◽  
Axial Compressor ◽  
Design Procedure ◽  
Abel Equation ◽  
Navier Stokes ◽  
Design Stage ◽  
Analysis And Design ◽  
Compressor Performance ◽  
Performance Check ◽  
Integrated Performance

It is well recognized that vorticity and vortical structures appear inevitably in viscous compressor flows and have strong influence on the compressor performance. However, conventional analysis and design procedure cannot pinpoint the quantitative contribution of each individual vortical structure to the integrated performance of a compressor, such as the stagnation-pressure ratio and efficiency. We fill this gap by using the so-called derivative-moment transformation, which has been successfully applied to external aerodynamics. We show that the compressor performance is mainly controlled by the radial distribution of azimuthal vorticity, of which an optimization in the through-flow design stage leads to a simple Abel equation of the second kind. The satisfaction of the equation yields desired circulation distribution that optimizes the blade geometry. The advantage of this new procedure is demonstrated by numerical examples, including the posterior performance check by 3D Navier–Stokes simulation.

Comparison of Controlled Diffusion Airfoils With Conventional NACA 65 Airfoils Developed for Stator Blade Application in a Multistage Axial Compressor

1985 ◽  
Vol 107 (2) ◽  
pp. 494-498 ◽  
Author(s):  
H. Rechter ◽  
W. Steinert ◽  
K. Lehmann
Keyword(s):  
Axial Compressor ◽  
Test Facility ◽  
Axial Compressors ◽  
Controlled Diffusion ◽  
Diffusion Technique ◽  
Precise Prediction ◽  
Stator Blade ◽  
Compressor Performance ◽  
Velocity Triangle ◽  
Transonic Cascade

In their transonic cascade wind tunnel, DFVLR has done measurements on a conventional NACA 65, as well as on a controlled diffusion airfoil, designed for the same velocity triangle at supercritical inlet condition. These tested cascades represent the first stator hub section of a three-stage axial/one-stage radial combined compressor developed by MTU with the financial aid of the German Ministry of Research and Technology. One aspect of this project was the verification of the controlled diffusion concept for axial compressor blade design, in order to demonstrate the capabilities of some recent research results which are now available for industrial application. The stator blades of the axial compressor section were first designed using NACA 65 airfoils. In the second step, the controlled diffusion technique was applied for building a new stator set. Both stator configurations were tested in the MTU compressor test facility. Cascade and compressor tests revealed the superiority of the controlled diffusion airfoils for axial compressors. In comparison to the conventional NACA blades, the new blades obtained a higher efficiency. Furthermore, a closer matching of the compressor performance data to the design requirements was possible due to a more precise prediction of the turning angle.

Vorticity Dynamics in Axial Compressor Flow Diagnosis and Design

2007 ◽  
Author(s):  
Yantao Yang ◽  
Hong Wu ◽  
Qiushi Li ◽  
Sheng Zhou ◽  
Jiezhi Wu
Keyword(s):  
Three Dimensional ◽  
Axial Compressor ◽  
Stagnation Pressure ◽  
Rotor Blades ◽  
Navier Stokes ◽  
Compressor Design ◽  
Circulation Distribution ◽  
Compressor Performance ◽  
Vorticity Dynamics

The role of vorticity dynamics in the axial compressor diagnosis and design is investigated analytically and numerically, in terms of the stagnation-pressure flux that controls the compressor’s performance. The stagnation-pressure flux is found to be dominated by the distribution of circumferential vorticity. The circumferential vorticity is directly expressible by the circulation distribution which is the significant parameter in the throughflow compressor design. Some principles of controlling compressor performance are thereby proposed, which are demonstrated by two rotor blades, designed by throughflow procedure and evaluated by three-dimensional Reynolds-average Navier-Stokes simulation.

Aerodynamic Design and Test Result Analysis of a Three Stage Research Compressor

2004 ◽  
Author(s):  
Armel Touyeras ◽  
Michel Villain
Keyword(s):  
Cfd Simulation ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Aerodynamic Design ◽  
New Developments ◽  
Compressor Performance ◽  
Flow Effects ◽  
Stage Matching ◽  
Result Analysis ◽  
Test Result

The present paper describes the aerodynamic design and the test result analysis of a three-stage research compressor designed by Snecma Moteurs and tested at Ecole Centrale de Lyon, France. Firstly, the CREATE compressor, representative of the median or rear stages of modern high-pressure compressors, is presented. Particular emphasis is put on the CFD process employed in its design, which was based largely on three-dimensional Navier-Stokes multistage simulations. A brief description of the stage-by-stage matching achieved on the compressor is also presented. Test results available from traversal probes and laser velocimetry are compared with CFD simulation for overall compressor performance, stage-by-stage matching, and secondary flow effects. Prediction of the design and off-design compressor performance with 3D multistage tools is discussed. Finally, the prospects of new developments concerning the CFD tools and the evolution of the experimental compressor are also mentioned.

scholarly journals Axial Compressor Fouling Evaluation at High Speed Settings Using an Aerothermodynamic Model

1993 ◽  
Author(s):  
Inam Ul Haq ◽  
H. I. H. Saravanamuttoo
Keyword(s):  
High Speed ◽  
Axial Compressor ◽  
Field Tests ◽  
Ambient Conditions ◽  
Turbine Engine ◽  
Discharge Temperature ◽  
Engine Compressor ◽  
Flow Compressor ◽  
Industrial Gas Turbine

An aerothermodynamic model for a widely used industrial gas turbine engine compressor has been developed for studying in-situ compressor deterioration due to atmospheric fouling at high power settings. The model is developed using available geometrical dimensions of the compressor annulus. It is based on a mean line stage stacking method utilizing the basic turbomachinery equations. The model requires minimum inputs (mass flow, compressor speed, ambient conditions) from the instrument sensors and derives all the necessary information (compressor discharge temperature and pressure, isentropic efficiency, and power) that defines overall performance. The validity of the model was confirmed by comparing the results with the field tests and excellent agreement was achieved. The model is very economical in operation and is fully capable of detecting small changes that occur in the compressor due to fouling.

Optimization of a stator blade using response surface method in a single-stage transonic axial compressor

2005 ◽  
Vol 219 (8) ◽  
pp. 595-603 ◽  
Author(s):  
C-M Jang ◽  
K-Y Kim
Keyword(s):  
Response Surface ◽  
Response Surface Method ◽  
Stokes Equations ◽  
Axial Compressor ◽  
Single Stage ◽  
Navier Stokes ◽  
Surface Method ◽  
Reference Shape ◽  
Stator Blade ◽  
Transonic Axial Compressor

This article describes the shape optimization of a stator blade in a single-stage transonic axial compressor. The blade optimization has been performed using response surface method and three-dimensional Navier-Stokes analysis. Thin-layer approximation is introduced to the Navier-Stokes equations, and an explicit Runge-Kutta scheme is used to solve the governing equations. Two geometric design variables of the stator blade, which are used to define a stacking line, are introduced to increase an adiabatic efficiency. D-optimal design is employed to reduce the number of evaluation points for response surface. With the optimization of the stator blade, the adiabatic efficiency is successfully improved when compared with that of the reference shape of the stator with straight stacking line. Positive stacking line, which bends on blade pressure side, effectively suppresses the flow separation on the blade suction surface of the stator.

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