TUSAS Engine Industries TEI

Eskişehir, Turkey

TUSAS Engine Industries TEI

Eskişehir, Turkey

Time filter

Source Type

Aydin H.,TUSAS Engine Industries TEI | Turan O.,Anadolu University | Karakoc T.H.,Anadolu University | Midilli A.,Recep Tayyip Erdoğan University
International Journal of Exergy | Year: 2012

In this paper, component-based exergetic assessment is presented for an experimental turboprop=turboshaft engine, including comparisons and exergetic performance such as their efficiencies, improvement potentials, exergy destruction rates, relative exergy destructions, fuel depletion ratios, productivity lacks, and fuel and product exergy factors with different power settings and torques. The exergetic assessment of the engine components provided here should be helpful for designing shaft-power aero engines. Results from this study also evaluate effects of the operating parameters on the exergetic performance of the engine components commonly used in regional propeller aircrafts and helicopters. Copyright © 2012 Inderscience Enterprises Lt.


Aydin H.,TUSAS Engine Industries TEI | Turan O.,Anadolu University | Midilli A.,Recep Tayyip Erdoğan University | Karakoc T.H.,Anadolu University
International Journal of Exergy | Year: 2013

It is necessary to understand the mechanisms that have enabled improvements of performance parameters such as thermodynamics efficiencies, thrust or power, specific fuel consumption and specific power in aero engines, thus reducing environmental impact. In this study, a thermodynamic analysis of a turboprop engine is performed at full and partial load conditions. The maximum overall and exergy efficiencies of the turboprop are found to be 30.7 and 29.2%, respectively. The minimum specific fuel consumption and maximum shaft power are found to be 0.2704 kg (kWh)-1 and 1948 shp at maximum load, respectively. More important, the optimum functional load conditions of the engine are observed at higher loads. The results from this study are expected to assist propeller aero-engine design work, where the first and second laws provide a more comprehensive assessment of performance, allowing the turboprop engine concept to be better tailored to specific types of regional transport aircraft. Copyright © 2013 Inderscience Enterprises Ltd.


Aydin H.,TUSAS Engine Industries TEI | Turan O.,Anadolu University | Karakoc T.H.,Anadolu University | Midilli A.,Recep Tayyip Erdoğan University
International Journal of Exergy | Year: 2014

In this paper, theory, methodology and example application are developed and shown for a PW6000 high-bypass turbofan engine in terms of exergo-sustainable perspective. To obtain exergetic sustainability indicators, first, detailed exergy analysis is performed for the engine. The investigated exergetic sustainability indicators are exergy efficiency, waste exergy ratio, exergy destruction factor, environmental effect factor and exergetic sustainability index. These parameters are obtained as 29.7%, 70.3%, 59.4%, 2.367 and 0.423 for the engine at maximum take-off flight condition, respectively. Finally, these parameters are also expected to help understand the linkage between propulsion system design parameters and global aspects in terms of environmental impact and sustainable development and hence make the engine more environmentally benign and more sustainable. Copyright © 2014 Inderscience Enterprises Ltd.


Topal A.,TUSAS Engine Industries TEI | Turan O.,Anadolu University | Uslu S.,TOBB University of Economics and Technology | Sogut M.Z.,Bursa Orhangazi University
International Journal of Exergy | Year: 2016

Combustion of fuel finds its importance in heating, power production and transportation. The main objective of this study is to assess the performance of an air-blasted combustor using the exergy at different combustor exit temperatures (T4). Exergetic metrics of the combustor in a test rig were made between 1,100 < T4 ≤ 1500 K. JP8 kerosene-type fuel was used for analysis. For the combustor, exergy efficiency was calculated to be between 49.3% and 59.4%. Furthermore, greatest exergy destruction is found at highest combustor exit temperature (138.7 kW at 1500 K), while the lower exergy destructions are found at 1102 K with the value of 90.7 kW. The methodology and the results of this study can be beneficial for further improvement, and development of similar combustor systems for designers. © 2016 Inderscience Enterprises Ltd.


Kivilcim E.,TUSAS Engine Industries TEI | Banu B.,TUSAS Engine Industries TEI
Applied Mechanics and Materials | Year: 2014

This paper demonstrates how to establish the system level requirement set for an aviation piston engine, which is intended to be used for a MALE class UAV and for a Part 23 Normal category airplane. Here, it will be demonstrated, which requirements should be taken into account to construct the system level requirement set. This work is aimed to depict a methodology to create the system level requirement set. © (2014) Trans Tech Publications, Switzerland.

Loading TUSAS Engine Industries TEI collaborators
Loading TUSAS Engine Industries TEI collaborators