Aerospace Knowledge and Technology Journal

Aerospace Knowledge and Technology Journal

A method for the primary design and matching of aerial and non-aerial recuperated micro-turbines

Document Type : Research Paper

Authors
Fariborz Azari Barzandigh 1
Mehrdad Bazazzadeh 2
Mahmood Rostami 3
Kiarash Charlangh 4
1 PhD Student, Faculty of Aerospace, Malek Ashtar University of Technology, Iran
2 Assistant Professor, Faculty of Aerospace, Malek Ashtar University of Technology, Iran
3 Assistant Professor, Faculty of Aerospace, Malek Ashtar University of Technology, Iran.
4 Research and Development of Sepehr Turbine Industry, Iran.
Abstract
The multiplicity of performance parameters and their interactions, as well as the matching issue of the heat exchanger and the engine, are the most challenging issues in the first phase of designing a recuperated microturbine. Here, using the experimental considerations and the thermodynamic, various performance charts will be produced and the relationship between the variables and their intervals will be determined. It was shown that, the optimum thermal performance can be achieved for compression ratios between 3.5-5.0, and 2.75-4.0 for the aerial and non-aerial recuperated engines, respectively. For the aerial types, the desired turbine-inlet-temperature varies in the range of 1100-1250, while the range 950-1250 is optimal for the non-aerial engines. In the aerial types, the thermal efficiency is more affected by the pressure drop, therefore the use of laminar flow recuperators is inevitable for such applications. For the non-aerial types, the thermal performance and PSFC drastically reduces for pressure ratios less than 3.5.
Keywords
Micro-turbine
Recupeator
Cycle analysis
Brayton cycle
Thermal efficiency
Subjects
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