Super Aggressive S-Ducts for Air Breathing Rocket EnginesSource: Journal of Turbomachinery:;2021:;volume( 143 ):;issue: 006::page 061015-1DOI: 10.1115/1.4050596Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Air breathing rocket engines require turbomachinery and ducting that is substantially lighter than that used in ground-based or aerospace gas turbines. In order to reduce the weight of the axial compressor, the design of the inter-spool swan neck duct is targeted. In this paper, a circumferential splitter blade is used to reduce loading and diffusion on the duct endwalls. The splitter and duct geometry are coupled and optimized together using 2D CFD. A design is selected that is 30% shorter than ducts that are currently used in aerospace gas turbines, and the 3D flow features are investigated in further detail using an experimental rig and 3D CFD. This paper shows that the “splittered” duct has three benefits over a conventional duct design: first, separation of the endwalls is prevented even at short duct lengths, this will reduce distortion into the downstream compressor. Second, losses generated by corner separations on structural struts can be reduced by 20%, enabling short ducts to achieve high performance. Third, splittered ducts are shown to be twice as robust to uncertain inlet flow conditions as conventional ducts. This allows a designer to target high-performance short designs with reduced risk.
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contributor author | Taylor, J. V. | |
contributor author | Flanagan, F. | |
contributor author | Dunlop, A. | |
contributor author | Grimshaw, S. D. | |
contributor author | Miller, R. J. | |
date accessioned | 2022-02-06T05:52:50Z | |
date available | 2022-02-06T05:52:50Z | |
date copyright | 4/27/2021 12:00:00 AM | |
date issued | 2021 | |
identifier issn | 0889-504X | |
identifier other | turbo_143_6_061015.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl1/handle/yetl/4278967 | |
description abstract | Air breathing rocket engines require turbomachinery and ducting that is substantially lighter than that used in ground-based or aerospace gas turbines. In order to reduce the weight of the axial compressor, the design of the inter-spool swan neck duct is targeted. In this paper, a circumferential splitter blade is used to reduce loading and diffusion on the duct endwalls. The splitter and duct geometry are coupled and optimized together using 2D CFD. A design is selected that is 30% shorter than ducts that are currently used in aerospace gas turbines, and the 3D flow features are investigated in further detail using an experimental rig and 3D CFD. This paper shows that the “splittered” duct has three benefits over a conventional duct design: first, separation of the endwalls is prevented even at short duct lengths, this will reduce distortion into the downstream compressor. Second, losses generated by corner separations on structural struts can be reduced by 20%, enabling short ducts to achieve high performance. Third, splittered ducts are shown to be twice as robust to uncertain inlet flow conditions as conventional ducts. This allows a designer to target high-performance short designs with reduced risk. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Super Aggressive S-Ducts for Air Breathing Rocket Engines | |
type | Journal Paper | |
journal volume | 143 | |
journal issue | 6 | |
journal title | Journal of Turbomachinery | |
identifier doi | 10.1115/1.4050596 | |
journal fristpage | 061015-1 | |
journal lastpage | 061015-8 | |
page | 8 | |
tree | Journal of Turbomachinery:;2021:;volume( 143 ):;issue: 006 | |
contenttype | Fulltext |