A 15stage axialflow compressor utilized in steel industry was studied in this paper. The test model is a low speed isolated axial compressor rotor blade row. The design of a heavilyloaded, supersonic axial compressor stage is described. A multistage axial compressor incorporating a counterrotational movement is provided with a series of rotors mounted along and driven by a driveshaft, and a geared counterrotating outer casing. A modified stagestacking method for multistage axial flow compressor calculations tonye k. Proceedings of the asme turbo expo 2003, collocated with the 2003 international joint power generation conference. An inlet guide vane blade row for use in a compressor, the blade row comprising. A modified stagestacking method for multistage axial flow. This differs from other rotating compressors such as centrifugal compressor, axicentrifugal compressors and mixedflow compressors where the fluid flow will include a radial. They concluded low vertical overlap and more camber angle of the second airfoil lead to the best performance. A 2d aerodynamic design of subsonic axial compressor stage. Us9534608b2 multistage axial compressor with counter. A single casing treatment over the second rotor showed approximately the same increase in. Influence of flow coefficient, stagger angle, and tip clearance on tip vortex in axial compressors.
The angle at which the air flows across these airfoil shapes is critical to performance of the system. Abstract nonharmonic acoustic resonance was detected in the static pressure and sound signals in a fourstage highspeed axial compressor when the compressor was operating close to the surge limit. A theory of rotating stall of multistage axial compressors. An axial compressor is a gas compressor that can continuously pressurize gases.
The angle that the chordline makes with the axis of the compressor is. Influence of rotor stagger angle on rotating stall inception. Experimental investigation on the plasma flow control of. The control effects of axial plasma actuation inducing body force of compressor axial direction with three different locations as well as stagger angle plasma actuation inducing body force perpendicular to the compressor rotor tip chordwise direction at different rotation. A lower and upper bound is chosen for each design requirement with values given in table 1. Sachmann and fottner examined tandem stators with low axial overlap. The axial matching or stage stacking of the compressor defines how stageoperating points i.
End wall flow characteristics and overall performance of. Design optimization of a multistage axial compressor using. Influence of rotor stagger angle on rotating stall inception in an axialflow fan. Axialflow compressor design systems utilize experimentallysupported methods for. They also reported a decrease of blockage growth rate.
Chapter 9 design and optimization of turbo compressors. The cascade effect is a primary consideration figure 1. Numerical study of the stagger angle effects in forward. Numerical investigation of basesetting of stators stagger. The turning angle of the camberline is called camber angle. The design and fabrication of low speed axialflow compressor. Structural and conceptual design analysis of an axial compressor for a 100 mw industrial gas turbine ind100. It is a rotating, airfoilbased compressor in which the gas or working fluid principally flows parallel to the axis of rotation, or axially.
The angle at which the air flows across these airfoil shapes is. The axial compressor blades are treated as lifting surfaces like aircraft wings or propeller blades. Experimental study of flow through compressor cascade. Investigation into the flow mechanism of rotating instability. Design methodology of a two stage axial compressor. Inlet guide vane for axial compressor general electric co. This establishment of dsp online adjustment scheme may provide a practical solution for improving performance of multistage axial flow compressor when its operating condition is varied. The axial compressor is designed by integrating a variety of knowledge which includes fluid mechanics and. The axial compressor aerodynamic preliminary design is done by the conventional design methods i. The amplitudes of the resonant acoustic mode are in. The goal is to improve an existing design scheme of the turbine with a simple representation of stagger angle distributions. Design and analysis of stator, rotor and blades of the axial. Numerical study of the stagger angle effects in forward swept axial compressor rotor passages.
This work deals with the numerical simulation of axial flow compressors, from design to performance prediction. Stagger is defined as the angle between the blade chord line and the axial. Pdf numerical study of the stagger angle effects in. Design optimization of a multistage axial compressor. The blade row has a plurality of inlet guide vanes. Axial compressor structure design procedure the axial compressor is designed by integrating a variety of knowledge which includes fluid mechanics and mechanical design to fulfill lower fuel consumption, higher pressure ratio and better performance efficiencies.
In the axial flow compressor, the basic components used in the flow path of the compressor are the rotor blades and the stator blades. In a subsonic axial compressor cascade investigated by li et al. End wall flow characteristics and overall performance of an. So, the stagger angle s m yahya 2003 fundamentals of compressible flow, 81. Numerical study of the stagger angle effects in forward swept.
A planetary gear system is assembled along a static casing, which can be assembled as a forward or aft casing for the compressor. The experimental investigations conducted by mailach et al 2001 in a fourstage lowspeed compressor and a. The observed parameters including axial gap, stagger angle, and tip clearance affect its output power. Accordingly, the design point throughflow calculation fixes these parameters for the offdesign points. Influence of rotor stagger angle on rotating stall. Each inlet guide vane has a meanline approximately equal to naca standard a4k6 meanline, a thickness distribution approximately equal to naca standard sr 63 thickness distribution, a stagger angle, and a lift coefficient between 0. Pdf multiobjective optimum stator and rotor stagger. The twist of the blades can be calculated along the.
Aerospace engineering department indian institute of technology bombay, mumbai 400076, india email. Design and analysis of stator, rotor and blades of the. Gas dynamic compressor performance, modeling and control acknowledgements glossary bibliography biographical sketch summary the basic principles of theory and design of the axial and radial compressors for the gas. Numerical study of camber and stagger angle effects on the. Pranav raheja, amit mangtani, raj patel, achyut panchal, apoorv maheshwari, mitanshu sharma, nishant khanduja. It is an infinite row of equi distant similarly aerofoil bodies.
Multiobjective optimum stator and rotor stagger angle distributions. Automatic efficiency optimization of an axial compressor with. Axial flow fan and compressor blade design data on 52. Deviation angle turning angle prediction for advanced axialflow. Design of industrial axial compressor blade sections for optimal 30.
This boxconstrained requirement space contains large regions that do not occur in compressor design or are infeasible. Pdf numerical study of the stagger angle effects in forward. For example, it includes airfoils with low stagger angles at supersonic inlet mach numbers. At constant blade angle, an increase in flow coefficient is equivalent to increas. Numerical predictions of rotating stall in an axial multi. An examination of the flow and pressure losses in bfade. Effect of circumferential grooves on the aerodynamic. Mar 10, 2012 it is demonstrated that the dsp designed can well adjust the stagger angle of igv online, the efficiency under different conditions can be optimized. Multiobjective optimum stator and rotor stagger angle. This compressor was used by other researchers like inoue et al. Elder abstract in this paper an attempt was made at studying multisage axial flow compressor offdesign performance based on two existing. It forms the basic block for the design and development of turbo machinery, particularly the axial compressor and axial turbine. Air angle is defined as an angle between the axial direction and the flow direction.
Design and development of a multi stage contra rotating mini axial compressor. Structural and conceptual design analysis of an axial. Automatic efficiency optimization of an axial compressor. Tolerance using asymmetric inlet guide vane stagger by andreas schulmeyer b. The cascade is used to divert a flow stream with a minimal loss. Stagger angle is the angle between the chord line and axial direction. Experimental investigation on the plasma flow control of axial compressor rotating stall is implemented in this paper. Pitch, chord and stagger angle generate blade coordinates for stator and rotor for all stages study its compressibility effects check weather all requirements are satisfied. The generation of the blade coordinates is performed on the basis of naca65 profile with circular mean camber line. They studied the stagger angle of both of blades, axial overlap and vertical overlap.
Pdf in the present numerical work, an axial compressor rotorstator stage is studied for three rotor sweep configurations unswept, 20 tip. A repeated stage calculation is made to calculate the above parameters along compressor stages. Another benefit of counterrotation is that it offers a much larger change. An axial momentum budget analysis has been presented that explains the increase in stall margin with the radial transport of axial momentum across the groove. Considering the first stage, the rotor blade angle at inlet 1. Stagger angle iv, applied mechanics, masters thesis 2011. Algorithm development for aerodynamic preliminary design. Exploring a database of optimal airfoils for axial compressor. Stagger is defined as the angle between the blade chord line and the axial direction. A computer program, written in fortran, was developed and is able to design an axial. Tip clearance, however, gives inversely correlation with output power.
The stage performance prediction uses the meanline flow properties. Design and analysis of stator, rotor and blades of axial flow compressor issn. The researchers have tried to interpret the mechanism of ri. Effect of blade stagger angle on performance of a transonic. Aerodynamic test of fixedgeometry and adjustable additional. A modified stagestacking method for multistage axial. Geometric specifications of this rotor blade row are listed in table 1 26. The blade angle is an angle between the axial direction and the tangent to the camber line. The original stagger angle distribution is constant for the stator blades and. Development of a preliminary design method for subsonic. Based on analysis results, axial gap and stagger angle are positively correlated with output power up to a certain point at which the power decreases.
Results and discussion the values tabulated below are the geometrical parameters. The compressor is comprised of 12 blades designed based on naca65 airfoil series. Pdf influence of flow coefficient, stagger angle, and. Design and development of a multi stage contra rotating. The aerodynamic principles are applied to the compressor design to increase axial compressor ef. Two dimensional design of axial compressor main characteristics page 10 when the inlet flow is reduced, the output pressure reaches its maximum, if the flow is reduced more, the pressure developed by the compressor became lower than the pressure in. Design and development of a multi stage contra rotating mini. Nishioka, takahiro, kuroda, shuuji, and kozu, tadashi. The stage target performance calls for an overall total pressure radio of 3.
The design pitchchord ratio is defined by the blade count, the axial chord and the stagger angle. The operating points of individual stages of the compressor are strongly influenced by the change in axial matching of the flow field at offdesign conditions 5. This goal has been reached improving a pre existent matlabtm code based on a. Stagestacking is used to analyse a multistage compressor. Request pdf on mar 5, 2007, boris dobrzynski and others published influence of the rotor tip stagger angle on axial compressor stall inception find, read and cite all the research you need on. Aerodynamic performance of an axial compressor stage with. Accordingly, additional constraints are imposed to ensure that a feasible airfoil exists for each set of requirements. To measure the design and the off design performance compressor stage and the rotor blade static pressures. Influence of the rotor tip stagger angle on axial compressor. The present numerical work studies the flow field in subsonic axial compressor stator passages for. They varied stagger angle and vertical overlap while airfoil shapes were fixed. Turner in general, conventional compressor stages are designed by the cascads method, while high stagger low solidity ductcd fans are designed on modified isolated aerofoil theory.
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