Preliminary design and simulation of an axial flow compressor with experimental verification

Dissertant

Ali, Anwar Nadhom Muhammad

Thesis advisor

al-Tai, Arkan Kh.
Abd al-Wahid, Samira A.

University

University of Technology

Faculty

-

Department

Department of Electromechanical Engineering

University Country

Iraq

Degree

Ph.D.

Degree Date

2011

English Abstract

-The research is devoted to study the parameters which affect the performance of single and multi stage axial flow compressor.

Analytical, numerical, and experimental investigation were made for comprehensively studying behavior of axial flow compressor.

In the analytical approach two computer programs were constructed for single and multi stage to calculate stage pressure ratio, stage temperature ratio, stage efficiency, flow coefficients, stage loading coefficient, flow velocity to wheel speed ratio, inlet and outlet flow angle, and Mach number.

To study the effect of the airfoil shape and the flow characteristics between the compressor blades, the flow field between two blades was analyzed numerically by solving the steady, two dimensional and incompressible (timemass averaged Navier- Stokes equations).

The (κ-ε) turbulent model was used to simulate the condition of the momentum equation and to obtain the eddy viscosity.

The Cartesian velocity component and pressure on collocated (nonstaggered) grid arrangement were used as dependent variables in the momentum equation, which was discretized by finite volume method.

Body fitted coordinate system was used to represent the complex blade geometry and algebraic method was employed to make the grid generation.

The SIMPLE algorithm is used to satisfy velocity-pressure coupling method and to satisfy the conservation of mass.

The experimental investigation was carried out on three real twisted blades.

Which taken from a power plant south of Baghdad.

These blades have span of (240 mm) and tip chord of (106 mm) and hub chord of (123 mm).

The airfoil is a compressor blade NACA 65_(12) 10, A five-hole probe, made of hypodermic tubes, was used to measure the flow direction and the stagnation pressure at any point at the cascade passage.

It was designed such that the outer tube cut with an apex angle of 70o while the central tube remains uncut.

It was also calibrated before the measurements.

The primary object of the experimental work was the measurement of pressures and velocities between cascade blades.

The study showed that the optimum range of inlet flow angle is 30o-50o.

Inlet flow Mach 0.2-0.5.

While the values of diffusion factor ~0.5 and that of solidity factor around 1.

The values of incidence angle 0o to 15o.

A computer training program was build up for user benefits, using Dick and Carey model and simulating the axial flow compressor.

It's containing studying the performance, the compressor parameters and the cascade aerodynamic characteristics.

This program is useful in addition interactive.

Main Subjects

Mechanical Engineering

• APA
• MLA
• AMA

Language

English

Data Type

Arab Theses

Record ID

BIM-305100