[PANTONE STIRLING GEET SPAD] Thesis_Simple gas turbine engine design.pdf

A Design Study of Single-Rotor Turbomachinery Cycles


by


Manoharan Thiagarajan

A thesis submitted to the faculty of the Virginia Polytechnic Institute and State University in partial
fulfillment of the requirements for the degree of

Master of Science

in

Mechanical Engineering



Committee

Dr. Peter King, Chairman
Dr. Walter O’Brien, Committee Member
Dr. Clint Dancey, Committee Member






August 12, 2004
Blacksburg, Virginia

Keywords: Auxiliary power unit, single radial rotor, specific power takeoff, compressor, burner, turbine
A Design Study of Single-Rotor Turbomachinery Cycles
by
Manoharan Thiagarajan

Dr. Peter King, Chairman
Dr. Walter O’Brien, Committee Member
Dr. Clint Dancey, Committee Member

(ABSTRACT)

Gas turbine engines provide thrust for aircraft engines and supply shaft power for various
applications. They consist of three ponents. That is, pressor followed by bustion
chamber (burner) and a turbine. Both turbine ponents are either axial or centrifugal
(radial) in design. bustion chamber is stationary on the engine casing. The type of engine that is
of interest here is the gas turbine auxiliary power unit (APU). A typical APU has a centrifugal
compressor, burner and an axial turbine. APUs generate mechanical shaft power to drive equipments such
as small generators and hydraulic pumps. In airplanes, they provide cabin pressurization and ventilation.
They can also supply electrical power to certain airplane systems such as navigation. parison to
thrust engines, APUs are usually much smaller in design.
The purpose of this research was to investigate the possibility bining the ponents
of an APU into a single centrifugal rotor. To do this, a set of equations were chosen that would describe
the new turbomachinery cycle. They either were provided or derived using quasi-one-dimensional
compressible flow equations. A Math