scholarly journals Design Method of the Axial-Flow Blade Row on Modified Isolated Aerofoil Theory with Interference Coefficient : Part 2, The Influence of the Aerodynamic Parameter on the Fan Performance at Low Rate

1973 ◽  
Vol 16 (96) ◽  
pp. 971-980
Author(s):  
Yukitoshi NAKASHIMA ◽  
Kazuaki SHIRAMOTO
Keyword(s):  
Design Method ◽  
Axial Flow ◽  
Aerodynamic Parameter ◽  
Fan Performance ◽  
Blade Row ◽  
Low Rate

Presentation of a Blade-Design Method for Axial-Flow Turbines, Including Design and Test Results of a Typical Axial-Flow Stage

1960 ◽  
Vol 82 (1) ◽  
pp. 19-26
Author(s):  
F. Baumgartner ◽  
R. Amsler
Keyword(s):  
Design Method ◽  
Axial Flow ◽  
Rate Of Change ◽  
Rotor Blades ◽  
Test Results ◽  
Blade Loading ◽  
Blade Row ◽  
Consistent Manner ◽  
The Mean ◽  
Typical Design

A method is presented to determine the shape of stationary nozzle blades and rotor blades for an axial-flow-type turbine in a generally consistent manner based on the concept of aerodynamic blade loading. The mean blade load is a typical design parameter which predominantly determines the blade curvature. It depends in particular on the rate of change of momentum across the blade row. By applying the design method, airfoil shapes are obtained which satisfy the momentum requirements regardless of what blade-load distribution is assumed as long as the mean blade load remains constant. A specific application of the design method is described and test data are presented which show that good agreement between design goal and test results was achieved.

An integrated study of the design method for small axial-flow fans, based on the airfoil theory

2011 ◽  
Vol 225 (4) ◽  
pp. 885-895 ◽  
Author(s):  
S-C Lin ◽  
M-L Tsai
Keyword(s):  
Design Method ◽  
Three Dimensional ◽  
Integrated Design ◽  
Axial Flow ◽  
Aerodynamic Characteristics ◽  
Inverse Design ◽  
Performance Curve ◽  
Performance Requirement ◽  
Fan Performance ◽  
Design Program

This research is aimed to establish an integrated design scheme through combining the cascade theory and inverse design method for the small axial-flow fans. At first, a reliable set of low-Reynolds-number aerodynamic characteristics for National Advisory Committee for Aeronautics airfoils is constructed to serve as the fan design database via the computational fluid dynamics (CFD) calculation incorporated with a dependable turbulent model. Then, with the inputs of design conditions and few geometric settings, this design program can generate a fan configuration to meet with the desired performance requirement. Furthermore, by changing the operating flowrate for this fan geometry, this design approach can also yield the axial velocity and the pressure distributions for various operating points over the entire performance curve. Consequently, this feature enables the design engineer to foresee the actual fan performance delivered under different system resistances. Thereafter, a computer numerically controlled fabricated prototype and a three-dimensional numerical model are chosen to validate the design prediction of fan performance via both test and CFD approaches. As a result, a slight deviation among the designed, experimental, and numerical outcomes is observed throughout the P Q performance curve. In conclusion, this systematic and user-friendly inverse design program not only provides the fan engineer's design ability to meet with the performance requirement at the on-design point, but also the predicting capability on the off-design characteristics.

Inverse Design of Axial-Flow Compressor Blades Using Elastic Surface Algorithm in Subsonic and Transonic Flow Regimes With Separation

2016 ◽  
Author(s):  
M. H. Noorsalehi ◽  
M. Nili-Ahamadabadi ◽  
E. Shirani ◽  
M. Safari
Keyword(s):  
Pressure Distribution ◽  
Transonic Flow ◽  
Design Method ◽  
Axial Flow ◽  
Flow Regimes ◽  
Inverse Design ◽  
Elastic Surface ◽  
Axial Flow Compressor ◽  
Inverse Design Method ◽  
Flow Compressor

In this study, a new inverse design method called Elastic Surface Algorithm (ESA) is developed and enhanced for axial-flow compressor blade design in subsonic and transonic flow regimes with separation. ESA is a physically based iterative inverse design method that uses a 2D flow analysis code to estimate the pressure distribution on the solid structure, i.e. airfoil, and a 2D solid beam finite element code to calculate the deflections due to the difference between the calculated and target pressure distributions. In order to enhance the ESA, the wall shear stress distribution, besides pressure distribution, is applied to deflect the shape of the airfoil. The enhanced method is validated through the inverse design of the rotor blade of the first stage of an axial-flow compressor in transonic viscous flow regime. In addition, some design examples are presented to prove the effectiveness and robustness of the method. The results of this study show that the enhanced Elastic Surface Algorithm is an effective inverse design method in flow regimes with separation and normal shock.

Development of a New Front Stage for an Industrial Axial Flow Compressor

1994 ◽  
Vol 116 (4) ◽  
pp. 597-604 ◽  
Author(s):  
B. Eisenberg
Keyword(s):  
Design Method ◽  
Guide Vane ◽  
Theoretical Calculations ◽  
Axial Flow ◽  
Operating Range ◽  
Performance Curves ◽  
Front Stage ◽  
Inverse Design Method ◽  
Flow Compressor ◽  
High Degree

Industrial axial flow compressors are specially designed to achieve a wide operating range. The analysis of an existing six-stage axial flow research compressor indicated that the front stage could be improved significantly using modern design technique. To demonstrate the advantages of such a technique a redesign of the current front stage was conducted. By controlling the diffusion inside the blade sections with an inverse design method, loading was enlarged. Higher loading normally results in a reduction of profile incidence range. For compensation a wide chord application was chosen. Compared to the original compressor version, experiments resulted in steeper characteristic curves together with larger usable operating range. Keeping the same outer and inner diameter, mass flow was increased by 6 percent. Measurements of performance curves with variable speed and for guide vane control are presented. Theoretical calculations achieve a high degree of agreement with measured performance.

Discrete Frequency Noise Generation From an Axial Flow Fan Blade Row

1970 ◽  
Vol 92 (1) ◽  
pp. 37-43 ◽  
Author(s):  
Ramani Mani
Keyword(s):  
Three Dimensional ◽  
Axial Flow ◽  
Acoustic Energy ◽  
Frequency Noise ◽  
Noise Generation ◽  
Two Dimensional ◽  
Axial Flow Fan ◽  
Fan Noise ◽  
Blade Row ◽  
Fan Blade

An analysis is presented which treats the noise generation from an axial flow fan row by given forces including the effects of a moving medium. The linearization of Euler’s equations to yield tractable problems for fan noise is discussed. The three-dimensional problem is decomposed into several two-dimensional problems. Finally, full details are given of a two-dimensional analysis to predict the amounts of acoustic energy, at the blade passing frequency and its harmonics, radiated up and downstream of a blade row due to its interaction with a neighboring row.

scholarly journals Study on the Secondary Flow in the Downstream of a Moving Blade Row in an Axial Flow Fan

1981 ◽  
Vol 24 (188) ◽  
pp. 332-339 ◽  
Author(s):  
Tsutomu ADACHI ◽  
Hiroshi SASHIKUMA ◽  
Tatsuo KAWAI
Keyword(s):  
Secondary Flow ◽  
Axial Flow ◽  
Axial Flow Fan ◽  
Blade Row

Influence of Rain Ingestion on the Endwall Treatment in an Axial Flow Compressor

2018 ◽  
Vol 140 (8) ◽  
Author(s):  
Jichao Li ◽  
Juan Du ◽  
Mingzhen Li ◽  
Feng Lin ◽  
Hongwu Zhang ◽  
...  
Keyword(s):  
Rotor Blade ◽  
Axial Flow ◽  
Pressure Rise ◽  
Water Film ◽  
Stall Margin ◽  
Axial Flow Compressor ◽  
Water Ingestion ◽  
Blade Row ◽  
Flow Compressor ◽  
The Stability

The effects of water ingestion on the performance of an axial flow compressor are experimentally studied with and without endwall treatment. The background to the work is derived from the assessment of airworthiness for an aero-engine. The stability-enhancing effects with endwall treatments under rain ingestion are not previously known. Moreover, all the endwall treatments are designed under dry air conditions in the compressor. Water ingestion at 3% and 5% relative to the design mass flow proposed in the airworthiness standard are applied to initially investigate the effects on the performance under smooth casing (SC). Results show that the water ingestions are mainly located near the casing wall after they move through the rotor blade row. The pressure rise coefficient increases, efficiency declines, and torque increases under the proposed water ingestion. The increase of the inlet water increases the thickness of the water film downstream the rotor blade row and aggravates the adverse effects on the performances. Subsequently, three endwall treatments, namely circumferential grooves, axial slots, and hybrid slots–grooves, are tested with and without water ingestion. Compared with no water ingestion, the circumferential grooves basically have no resistance to the water ingestion. The axial slots best prevent the drop of the pressure rise coefficient induced by water ingestion, and hybrid slots–grooves are the second-best place owing to the contribution of the front axial slots. Therefore, the hybrid slots–grooves can not only extend the stall margin with less efficiency penalty compared with axial slots, but also prevent rain ingestion from worsening the compressor performance.

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