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New supersonic loss model for the preliminary design of transonic turbine blades and the influence of pitch

Teia, Luis LU (2020) In Journal of Turbomachinery 142(4).
Abstract

In order to produce a more efficient design of a compact turbine driving a cryogenic engine turbo-pump for a satellite delivering rocket, a new supersonic loss model is proposed. The new model was constructed based on high-quality published data, composed of Schlieren photographs and experimental measurements, that combined provided a unique insight into the mechanisms driving supersonic losses. Using this as a cornerstone, model equations were formulated that predict the critical Mach number and shock loss and shock-induced mixing loss as functions of geometrical (i.e., blade outlet and uncovered turning angle and trailing edge thickness) and operational parameters (i.e., exit Mach number). A series of highly resolved CFD numerical... (More)

In order to produce a more efficient design of a compact turbine driving a cryogenic engine turbo-pump for a satellite delivering rocket, a new supersonic loss model is proposed. The new model was constructed based on high-quality published data, composed of Schlieren photographs and experimental measurements, that combined provided a unique insight into the mechanisms driving supersonic losses. Using this as a cornerstone, model equations were formulated that predict the critical Mach number and shock loss and shock-induced mixing loss as functions of geometrical (i.e., blade outlet and uncovered turning angle and trailing edge thickness) and operational parameters (i.e., exit Mach number). A series of highly resolved CFD numerical simulations were conducted on an in-house designed state-of-the-art transonic turbine rotor row (around unity aspect ratio (AR)) to better understand changes in the shock system for varying parameters. The main outcome showed that pitch to chord ratio has a powerful impact on the shock system, and thus on the manner by which shock loss and shock-induced mixing loss is distributed to compose the overall supersonic losses. The numerical loss estimates for two pitch to chord ratios—t/c = 0.70 and t/c = 0.98—were compared with absolute loss data of a previously published similar blade with satisfactory agreement. Calibrated equations are provided to allow hands-on integration into existing overall turbine loss models, where supersonic losses play a key role, for further enhancement of preliminary turbine design.

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Please use this url to cite or link to this publication:
author
organization
publishing date
type
Contribution to journal
publication status
published
subject
keywords
Computational fluid dynamics (CFD), Fluid dynamics and heat transfer phenomena in turbine components of gas turbine engines, Supersonic flow, Turbine aerodynamic design, Turbine loss models, Turbomachinery blading design
in
Journal of Turbomachinery
volume
142
issue
4
article number
041008-1
publisher
American Society Of Mechanical Engineers (ASME)
external identifiers
  • scopus:85087786076
ISSN
0889-504X
DOI
10.1115/1.4045983
language
English
LU publication?
yes
id
772ba2f7-1ac2-4917-9d55-1398e8efa11b
date added to LUP
2020-07-22 12:29:28
date last changed
2022-04-18 23:46:50
@article{772ba2f7-1ac2-4917-9d55-1398e8efa11b,
  abstract     = {{<p>In order to produce a more efficient design of a compact turbine driving a cryogenic engine turbo-pump for a satellite delivering rocket, a new supersonic loss model is proposed. The new model was constructed based on high-quality published data, composed of Schlieren photographs and experimental measurements, that combined provided a unique insight into the mechanisms driving supersonic losses. Using this as a cornerstone, model equations were formulated that predict the critical Mach number and shock loss and shock-induced mixing loss as functions of geometrical (i.e., blade outlet and uncovered turning angle and trailing edge thickness) and operational parameters (i.e., exit Mach number). A series of highly resolved CFD numerical simulations were conducted on an in-house designed state-of-the-art transonic turbine rotor row (around unity aspect ratio (AR)) to better understand changes in the shock system for varying parameters. The main outcome showed that pitch to chord ratio has a powerful impact on the shock system, and thus on the manner by which shock loss and shock-induced mixing loss is distributed to compose the overall supersonic losses. The numerical loss estimates for two pitch to chord ratios—t/c = 0.70 and t/c = 0.98—were compared with absolute loss data of a previously published similar blade with satisfactory agreement. Calibrated equations are provided to allow hands-on integration into existing overall turbine loss models, where supersonic losses play a key role, for further enhancement of preliminary turbine design.</p>}},
  author       = {{Teia, Luis}},
  issn         = {{0889-504X}},
  keywords     = {{Computational fluid dynamics (CFD); Fluid dynamics and heat transfer phenomena in turbine components of gas turbine engines; Supersonic flow; Turbine aerodynamic design; Turbine loss models; Turbomachinery blading design}},
  language     = {{eng}},
  month        = {{04}},
  number       = {{4}},
  publisher    = {{American Society Of Mechanical Engineers (ASME)}},
  series       = {{Journal of Turbomachinery}},
  title        = {{New supersonic loss model for the preliminary design of transonic turbine blades and the influence of pitch}},
  url          = {{http://dx.doi.org/10.1115/1.4045983}},
  doi          = {{10.1115/1.4045983}},
  volume       = {{142}},
  year         = {{2020}},
}