Details
| Original language | English |
|---|---|
| Number of pages | 8 |
| Journal | International Journal of Gas Turbine, Propulsion and Power Systems |
| Volume | 10 |
| Issue number | 2 |
| Publication status | Published - 2019 |
Abstract
Power output and efficiency of gas turbines depend strongly upon the achievable pressure rise in the subsequent diffuser. In combination with the requirement to keep diffuser length to a minimum, ever steeper opening angles are sought, while avoiding diffuser stall. In terms of diffuser pressure rise, the boundaries of what is achievable can be pushed further if the tip leakage vortices from the last stage are used to re-accelerate the diffuser boundary layer, thus delaying separation onset. Such measures have been shown to decrease total pressure losses as well. In this paper, we show that the benefit of total pressure loss reduction in vortex-stabilised diffusers becomes more pronounced for steeper opening angles by means of a numerically and experimentally validated approach. In extension, we provide evidence that the loss production in highly loaded vortex-stabilised diffusers, which would stall otherwise, can be brought down to the level of non-stalling diffusers. Furthermore, we present a detailed analysis of the different loss mechanisms and their response to vortex-stabilisation of the diffuser.
ASJC Scopus subject areas
- Engineering(all)
- Mechanical Engineering
Cite this
- Standard
- Harvard
- Apa
- Vancouver
- BibTeX
- RIS
In: International Journal of Gas Turbine, Propulsion and Power Systems, Vol. 10, No. 2, 2019.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Total Pressure Loss Reduction in Annular Diffusers
AU - Mimic, Dajan
AU - Jätz, Christoph
AU - Sauer, Philipp
AU - Herbst, Florian
PY - 2019
Y1 - 2019
N2 - Power output and efficiency of gas turbines depend strongly upon the achievable pressure rise in the subsequent diffuser. In combination with the requirement to keep diffuser length to a minimum, ever steeper opening angles are sought, while avoiding diffuser stall. In terms of diffuser pressure rise, the boundaries of what is achievable can be pushed further if the tip leakage vortices from the last stage are used to re-accelerate the diffuser boundary layer, thus delaying separation onset. Such measures have been shown to decrease total pressure losses as well. In this paper, we show that the benefit of total pressure loss reduction in vortex-stabilised diffusers becomes more pronounced for steeper opening angles by means of a numerically and experimentally validated approach. In extension, we provide evidence that the loss production in highly loaded vortex-stabilised diffusers, which would stall otherwise, can be brought down to the level of non-stalling diffusers. Furthermore, we present a detailed analysis of the different loss mechanisms and their response to vortex-stabilisation of the diffuser.
AB - Power output and efficiency of gas turbines depend strongly upon the achievable pressure rise in the subsequent diffuser. In combination with the requirement to keep diffuser length to a minimum, ever steeper opening angles are sought, while avoiding diffuser stall. In terms of diffuser pressure rise, the boundaries of what is achievable can be pushed further if the tip leakage vortices from the last stage are used to re-accelerate the diffuser boundary layer, thus delaying separation onset. Such measures have been shown to decrease total pressure losses as well. In this paper, we show that the benefit of total pressure loss reduction in vortex-stabilised diffusers becomes more pronounced for steeper opening angles by means of a numerically and experimentally validated approach. In extension, we provide evidence that the loss production in highly loaded vortex-stabilised diffusers, which would stall otherwise, can be brought down to the level of non-stalling diffusers. Furthermore, we present a detailed analysis of the different loss mechanisms and their response to vortex-stabilisation of the diffuser.
UR - http://www.scopus.com/inward/record.url?scp=85097577504&partnerID=8YFLogxK
U2 - 10.38036/JGPP.10.2_1
DO - 10.38036/JGPP.10.2_1
M3 - Article
AN - SCOPUS:85097577504
VL - 10
JO - International Journal of Gas Turbine, Propulsion and Power Systems
JF - International Journal of Gas Turbine, Propulsion and Power Systems
IS - 2
ER -