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Research Papers: Gas Turbines: Microturbines and Small Turbomachinery

Continuous Closed-Loop Transonic Linear Cascade for Aerothermal Performance Studies in Microturbomachinery

[+] Author and Article Information
Eli Yakirevich

Turbomachinery and Heat Transfer Laboratory,
Aerospace Engineering Department,
Technion—Israel Institute of Technology,
Technion City,
Haifa 3200003, Israel
e-mail: eliyakir@campus.technion.ac.il

Ron Miezner

Turbomachinery and Heat Transfer Laboratory,
Aerospace Engineering Department,
Technion—Israel Institute of Technology,
Technion City,
Haifa 3200003, Israel
e-mail: ronmi@technion.ac.il

Boris Leizeronok

Turbomachinery and Heat Transfer Laboratory,
Aerospace Engineering Department,
Technion—Israel Institute of Technology,
Technion City,
Haifa 3200003, Israel
e-mail: borisl@technion.ac.il

Beni Cukurel

Turbomachinery and Heat Transfer Laboratory,
Aerospace Engineering Department,
Technion—Israel Institute of Technology,
Technion City,
Haifa 3200003, Israel
e-mail: beni@cukurel.org

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 3, 2017; final manuscript received July 4, 2017; published online September 19, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(1), 012301 (Sep 19, 2017) (9 pages) Paper No: GTP-17-1265; doi: 10.1115/1.4037611 History: Received July 03, 2017; Revised July 04, 2017

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 microturbomachinery 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 ultra-efficient high power or thrust devices. In order to alleviate the dimension specific challenges associated with microturbomachinery, the facility is designed in a highly versatile manner and can easily accommodate different geometric configurations (pitch, ±20 deg stagger angle, and ±20 deg incidence angle), absence 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 microgas turbine manufacturers, aerothermal performance of various advanced geometries can be assessed in engine relevant environments.

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Figures

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Fig. 1

Closed-loop TTLC facility layout

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Fig. 2

Technion transonic linear cascade test section layout and reference frame

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Fig. 3

Flow lines across the inlet XY (top) and XZ (bottom) cross sections

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Fig. 4

Turbulence grid design (mm)

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Fig. 5

Main frame assembly

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Fig. 6

Disks rotation mechanism set to ± 20 deg

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Fig. 7

Frontboards sealing and support mechanisms

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Fig. 8

Frontboard XY flow simulation: mesh and results for straight frontboards (left) and bellmouth shaped frontboards (right)

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Fig. 9

Frontboard three-dimensional flow simulation: mesh and results for bellmouth shaped frontboards

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Fig. 10

Test section window frame

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Fig. 11

Vane mounting and friction bearings setup

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Fig. 12

Stagger control mechanism set to ±20 deg

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Fig. 13

Tailboards design features

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Fig. 14

Tailboards angle control mechanism

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Fig. 15

Mach (top) and total pressure (bottom) distribution in the streamlines

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Fig. 16

Outlet configuration for compressor and turbine stators

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Fig. 17

Static probes arrangement

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Fig. 18

Cascade assembly in basic operation

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Fig. 19

Technion transonic linear cascade open-loop operational envelope

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Fig. 20

Closed-loop operational envelope manipulation

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