Analysis of the exit flow angle and characteristics of flow in axial turbine cascades
(2020) 2C: Turbomachinery. p.2020-14605- Abstract
- Despite a wealth of sophisticated CFD-methods, most designs are still based on one-dimensional and two-dimensional inviscid analytical tools. In such methods, realistic loss and angle assessment are indeed critical in order to arrive at correct loading, flow coefficient and reaction. The selected values are normally retained through the detailed design sequence for each iteration. This means that the throat sizing and hence the gauge angle is largely based on the early design work within the through-flow environment. Even one-degree error in angle estimation will turn into a rather large capacity error. For most designs, the exchange rate between capacity and gauge angle is on the order of 3–5 percent, per degree exit angle.
In a... (More) - Despite a wealth of sophisticated CFD-methods, most designs are still based on one-dimensional and two-dimensional inviscid analytical tools. In such methods, realistic loss and angle assessment are indeed critical in order to arrive at correct loading, flow coefficient and reaction. The selected values are normally retained through the detailed design sequence for each iteration. This means that the throat sizing and hence the gauge angle is largely based on the early design work within the through-flow environment. Even one-degree error in angle estimation will turn into a rather large capacity error. For most designs, the exchange rate between capacity and gauge angle is on the order of 3–5 percent, per degree exit angle.
In a previous publication, a methodology and equations were presented to assess the exit flow in an axial turbine blade row by Mamaev in Russian nomenclature and the tangential coordinate system. The approach, provided a unified and flow-physics based method for assessing exit angles from the geometry features like gauge angle, uncovered turning and flow features like Laval number, etc. Analysis of those formulas showed good agreement with physical flow pattern in real cascades for sub and transonic blade cascades. In this work, the same basic principal procedure is followed by employing the more international agreed nomenclature of blades such as an axial reference plane and Mach number.
In the current work, the one-dimensional analysis results were compared with the three dimensional numerical modelling of a full annulus two-stage turbine. Analysis of the results showed the inherent unsteadiness specially outside the rotor blade cascades, however, comparison of the mass averaged exit angle with the one dimensional analysis showed satisfactory agreement. (Less)
Please use this url to cite or link to this publication:
https://lup.lub.lu.se/record/11682524-88c0-4c81-88d7-cb12c63414f6
- author
- Hushmandi, Narmin LU ; Askebjer, Per and Genrup, Magnus LU
- organization
- publishing date
- 2020
- type
- Chapter in Book/Report/Conference proceeding
- publication status
- published
- subject
- host publication
- ASME turbo expo 2020 : Turbomachinery Technical Conference and Exposition - Turbomachinery Technical Conference and Exposition
- volume
- 2C: Turbomachinery
- pages
- 2020 - 14605
- external identifiers
-
- scopus:85099783699
- ISBN
- 978-0-7918-8408-9
- DOI
- 10.1115/GT2020-14605
- language
- English
- LU publication?
- yes
- id
- 11682524-88c0-4c81-88d7-cb12c63414f6
- date added to LUP
- 2026-02-24 09:25:28
- date last changed
- 2026-03-13 14:02:08
@inproceedings{11682524-88c0-4c81-88d7-cb12c63414f6,
abstract = {{Despite a wealth of sophisticated CFD-methods, most designs are still based on one-dimensional and two-dimensional inviscid analytical tools. In such methods, realistic loss and angle assessment are indeed critical in order to arrive at correct loading, flow coefficient and reaction. The selected values are normally retained through the detailed design sequence for each iteration. This means that the throat sizing and hence the gauge angle is largely based on the early design work within the through-flow environment. Even one-degree error in angle estimation will turn into a rather large capacity error. For most designs, the exchange rate between capacity and gauge angle is on the order of 3–5 percent, per degree exit angle.<br/><br/>In a previous publication, a methodology and equations were presented to assess the exit flow in an axial turbine blade row by Mamaev in Russian nomenclature and the tangential coordinate system. The approach, provided a unified and flow-physics based method for assessing exit angles from the geometry features like gauge angle, uncovered turning and flow features like Laval number, etc. Analysis of those formulas showed good agreement with physical flow pattern in real cascades for sub and transonic blade cascades. In this work, the same basic principal procedure is followed by employing the more international agreed nomenclature of blades such as an axial reference plane and Mach number.<br/><br/>In the current work, the one-dimensional analysis results were compared with the three dimensional numerical modelling of a full annulus two-stage turbine. Analysis of the results showed the inherent unsteadiness specially outside the rotor blade cascades, however, comparison of the mass averaged exit angle with the one dimensional analysis showed satisfactory agreement.}},
author = {{Hushmandi, Narmin and Askebjer, Per and Genrup, Magnus}},
booktitle = {{ASME turbo expo 2020 : Turbomachinery Technical Conference and Exposition}},
isbn = {{978-0-7918-8408-9}},
language = {{eng}},
pages = {{2020--14605}},
title = {{Analysis of the exit flow angle and characteristics of flow in axial turbine cascades}},
url = {{http://dx.doi.org/10.1115/GT2020-14605}},
doi = {{10.1115/GT2020-14605}},
volume = {{2C: Turbomachinery}},
year = {{2020}},
}