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research-article

A propeller model for steady-state and transient performance prediction of turboprop and counter-rotating open rotor engines

[+] Author and Article Information
Vinícius Tavares Silva

Aeronautics Institute of Technology, São José dos Campos, São Paulo, 12228-900, Brazil
viniciustasil@gmail.com

Cleverson Bringhenti

Aeronautics Institute of Technology, São José dos Campos, São Paulo, 12228-900, Brazil
cleverson@ita.br

Jesuino T. Tomita

Aeronautics Institute of Technology, São José dos Campos, São Paulo, 12228-900, Brazil
jtakachi@ita.br

Anderson Frasson Fontes

Aeronautics Institute of Technology, São José dos Campos, São Paulo, 12228-900, Brazil
andersonffontes@gmail.com

1Corresponding author.

ASME doi:10.1115/1.4038814 History: Received August 09, 2017; Revised November 16, 2017

Abstract

This paper describes a methodology used for propeller performance estimation which was implemented in an in-house modular program for gas turbine performance prediction. A model based on subsonic generic propeller maps and corrected for compressibility effects, under high subsonic speeds, was proposed and implemented. Considering this methodology, it is possible to simulate conventional turboprop architectures and counter-rotating open rotor (CROR) engines in both steady-state and transient operating conditions. Two simulation scenarios are available: variable pitch angle propeller with constant speed; or variable speed propeller with constant pitch angle. The simulations results were compared with test bench data and two gas turbine performance commercial software were used to fulfill the model validation for conventional turboprop configurations. Furthermore, a direct drive CROR engine was simulated using a variable inlet guide vanes (VIGV) control strategy during transient operation. The model has shown to be able to provide several information about propeller-based engine performance using few input data and a comprehensive understanding on steady-state and transient performance behavior was achieved in the obtained results.

Copyright (c) 2017 by ASME
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