TY - GEN
T1 - Continuous closed-loop transonic linear cascade for aero-thermal performance studies in micro-turbomachinery
AU - Yakirevich, E.
AU - Miezner, R.
AU - Leizeronok, B.
AU - Cukurel, B.
N1 - Publisher Copyright: Copyright © 2017 ASME.
PY - 2017
Y1 - 2017
N2 - The present work summarizes the design process of a new continuous closed-loop hot transonic linear cascade. The facility features fully modular design which is intended to serve as a test bench for axial micro-turbomachinery components in independently varying Mach and Reynolds numbers ranges of 0-1.3 and 2.104 - 6.105 respectively. Moreover, for preserving heat transfer characteristics of the hot gas section, the gas to solid temperature ratio (up to 2) is retained. This operational environment has not been sufficiently addressed in prior art, although it is critical for the future development of ultraefficient high power or thrust devices. In order to alleviate the dimension specific challenges associated with micro-turbomachinery, the facility is designed in a highly versatile manner, and can easily accommodate different geometric configurations (pitch, ±20° stagger angle, ±20° incidence angle), absent of any alterations to the test section. Owing to the quick swap design, the vane geometry can be easily replaced without manufacturing or re-assembly of other components. Flow periodicity is achieved by the inlet boundary layer suction and independently adjustable tailboard mechanisms. Enabling test-aided design capability for micro gas turbine manufacturers, aero-thermal performance of various advanced geometries can be assessed in engine relevant environments.
AB - The present work summarizes the design process of a new continuous closed-loop hot transonic linear cascade. The facility features fully modular design which is intended to serve as a test bench for axial micro-turbomachinery components in independently varying Mach and Reynolds numbers ranges of 0-1.3 and 2.104 - 6.105 respectively. Moreover, for preserving heat transfer characteristics of the hot gas section, the gas to solid temperature ratio (up to 2) is retained. This operational environment has not been sufficiently addressed in prior art, although it is critical for the future development of ultraefficient high power or thrust devices. In order to alleviate the dimension specific challenges associated with micro-turbomachinery, the facility is designed in a highly versatile manner, and can easily accommodate different geometric configurations (pitch, ±20° stagger angle, ±20° incidence angle), absent of any alterations to the test section. Owing to the quick swap design, the vane geometry can be easily replaced without manufacturing or re-assembly of other components. Flow periodicity is achieved by the inlet boundary layer suction and independently adjustable tailboard mechanisms. Enabling test-aided design capability for micro gas turbine manufacturers, aero-thermal performance of various advanced geometries can be assessed in engine relevant environments.
KW - Aero-thermal performance assessment
KW - Incidence and stagger angle variation
KW - Independent Reynolds Mach simulation
KW - Micro-turbomachinery
KW - Transonic turbine cascade design
UR - http://www.scopus.com/inward/record.url?scp=85028995846&partnerID=8YFLogxK
U2 - https://doi.org/10.1115/GT2017-64562
DO - https://doi.org/10.1115/GT2017-64562
M3 - منشور من مؤتمر
T3 - Proceedings of the ASME Turbo Expo
BT - Microturbines, Turbochargers and Small Turbomachines; Steam Turbines
T2 - ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
Y2 - 26 June 2017 through 30 June 2017
ER -