RADIAL-INFLOW TURBINE ONE AND TRI-DIMENSIONAL DESIGN ANALYSIS OF...

RADIAL-INFLOW TURBINE ONE AND

TRI-DIMENSIONAL DESIGN ANALYSIS OF

600 KW SIMPLE CYCLE GAS ENGINE

MSc Rubén Alexis Miranda Carrillo

Grupo de Estudos em Tecnologias de Conversão de Energia – GETEC

About Us

• The Study Group on Energy Conversion Technologies – GETEC

of Federal University of Itajubá – UNIFEI, was created in 2009.

• In the area of energy conversion, GETEC has experience in

analysis and simulation of gas turbine cycles and CFD

simulations of compressors, turbines, combustion chambers and

compact heat exchangers recuperators, as well as laboratory

experiments.

• GETEC offers training courses in gas turbines engine, centrifugal

and reciprocating compressors, internal combustion engines,

among others.

3

A compact micro-turbine schematic.

Radial-inflow

rotor Nozzle

Introduction

Radial-inflow turbine assemble.

Objective

This work presents the numerical meanline investigationson the aerothermodynamic design of the nozzle and theradial-inflow rotor for a 600 kW simple cycle gas turbineengine using a One-dimensional computer FORTRANCode (OFC), for the design and analysis of radial-inflowturbine components.

Aerothermodynamic Model

6

One-dimensional FORTRAN Code: TurbinaDP

Preliminary design.

r2

LZ

b3

r3h

r3s

Radial-inflow rotor

r

r0

r1

b0

Nozzle

The meanline method.

The Meanline Method

Validation Results

* Glassman, A.J., (1976), “Computer program for design

analysis of radial-inflow turbines”, NASA TN D-8164, Report

N° E-8394, Lewis Research Center, National Aeronautics

and Space Administration, Cleveland, Ohio, USA, 64 p.

The Gate Cycle Simulation

Stream

Temperature

(K)

Pressure

(kPa)

Mass flow rate

(kg/s)

S1 288 101.32 4.288

S2 461 405.28 4.288

S3 288 500.00 0.212

S4 1123 396 4.5

S5 846 101.32 4.5

Gas Turbine Assemble: Simulations regions

Computational Mesh

Radial-Inflow Rotor

Nozzle

Boundary Conditions

• Average total pressure and total temperature are imposed

at the inlet area.

• Average static pressure imposed at the outlet area.

• Heat transfer model = Total energy.

• Turbulence model = SST.

• Turbulent wall functions = Automatic.

• Rotor domain motion = Rotating.

• Nozzle domain = Stationary.

Simulations Results: Nozzle

14

Simulations Results: Radial-Inflow Rotor

Recirculation in the inlet region of a

radial turbine rotor passage.

2 2C U 2 2C U

TurbinaDP Literature

IInc = -29.767Moustapha, (2003):

IInc = -20 to -40

Comparison Results: CFD - FORTRAN

Conclusions

• The OFC method for radial turbines design has been developed,

being capable of predicting the efficiency of most “well designed”

radial turbines with good accuracy. No knowledge of the turbine

geometry beyond basic overall dimensions is required, therefore, the

method regarded suitable for preliminary design.

• The most differences were found when comparing the OFC method

results and the NASA TN D-8164 showing discrepancies lower than

10% between the values calculated by each computer program and

when comparing the OFC method and the ANSYS CFX 12.0

simulations results, with discrepancies lower than 13% between the

values calculated for each simulations program.

Acknowledgments

• Petrobras Research and Development Center (CENPES)

• National Council of Technological and Scientific Development

(CNPq)

• Foundation for Research Support of Minas Gerais (FAPEMIG)

Thank you for your attention!

More information: ruben.miranda@unifei.edu.br